Class / Patent application number | Description | Number of patent applications / Date published |
416221000 |
Resilient or deformable
| 22 |
416220000 |
Non-turbo machine | 4 |
20080199320 | Detachable leading edge for airfoils - A replaceable leading edge insert for an: integrally bladed rotor disk in which the insert includes an enlarged base portion that can be inserted into a dovetail shaped slot formed in the rotor disk to secure the insert to the rotor disk against centrifugal loads during the operation of the blade. The blade on the rotor disk is formed without a leading edge and the leading edge insert includes an aft edge of similar shape to the fore edge n the blade such that the insert can be bonded or fastened to the blade along the entire length of the insert from the blade root to the tip. The rotor disk and the insert include a an annular groove formed on the front side in which a retaining ring is inserted to lock the inserts to the rotor disk. The inserts can be made of a different material from the rotor disk and can be formed with a sweep to form a more :aerodynamic and efficient blade. | 08-21-2008 |
20080226458 | TURBOMACHINE FAN - A turbomachine fan ( | 09-18-2008 |
20080253895 | BLADE RETENTION SYSTEM FOR USE IN A GAS TURBINE ENGINE - The blade retention system comprises an annular sealing plate and a plurality of spaced-apart blade retention tabs having opposite first and second ends and a radially-orientated corrugated profile. The first ends of the tabs are connected to a first side face of the annular sealing plate. Each tab is configured and disposed to be inserted through a bottom portion of a respective one of the blade retention slots when the first side face of the sealing plate is positioned against one of the side faces of the rotor disc and covers an end side of the blade retention slots. The second end of each tab extends beyond the other of the side faces of the rotor disc and is bent to secure the annular sealing plate with reference to the rotor disc. | 10-16-2008 |
20080267781 | Turbo-Engine and Rotor for a Turbo-Engine - The invention relates to a rotor for a non-positive-displacement machine, particularly a rotor for a compressor of a gas turbine, on which at least one shaft collar with an outer periphery and with two radially extending faces are placed. The rotor also comprises a multitude of retaining grooves for moving blades, said retaining grooves being provided on the outer periphery and extending transversal to the peripheral direction and each retaining groove has a groove bottom. In order to provide a rotor for a non-positive-displacement machine that makes it possible to reduce flow losses while having a simple geometrical design of the attachment of moving blades, the invention provides that an annual groove, which extends in an axial direction and which is coaxial to the rotation axis of the rotor, is provided at least on one face of the shaft collar. This annular groove is joined to the groove bottom of the retaining grooves whereby enabling material of the foot of the moving blade to be plastically forced into the annular groove. | 10-30-2008 |
20080273982 | BLADE ATTACHMENT RETENTION DEVICE - A component for a gas turbine engine includes a rotor disk, a plurality of blade attachments, a plurality of retention flanges, and a plurality of retention tabs. The rotor disk has a plurality of slots formed in an outer surface thereof. Each blade attachment has an attachment region configured to be partially disposed within one of the slots. The plurality of retention flanges extend from the rotor disk outer surface, to thereby at least inhibit axial movement of the blade attachment, when the attachment region is fitted inside its corresponding slot. A retention tab extends from each attachment region and engages one of the retention flanges. | 11-06-2008 |
20090022592 | Clamped plate seal - A seal for a dovetail joint in a turbomachine is provided. The seal includes an arcuate member having a first end, a middle portion and a second end. The seal also includes sealing means, which include at least one sealing member. The sealing member can comprise a first sealing member connected to the first end and/or a second sealing member connected to the second end. The dovetail joint is the interface between a bucket dovetail and a rotor dovetail groove, and the seal reduces the amount of cooling flow leakage from the dovetail joint. | 01-22-2009 |
20090022593 | FAN BLADE RETAINING STRUCTURE | 01-22-2009 |
20090028712 | TURBOMACHINE HAVING AXIAL ROTOR BLADE SECURING - A rotor of a turbine machine having several rotor blade rings positioned in succession in the axial direction, is disclosed. Each rotor blade ring has a rotor base body with several rotor blades anchored by blade footings in axial grooves of the rotor base body that extend essentially in the axial direction and, in their anchored position in the rotor base body, are secured against displacement in the axial direction. The rotor blades of at least one rotor blade ring have hook-like securing elements, which, in the anchored position on a low-pressure side of the rotor blade ring, abut the rotor base body. The hook-like securing elements, between the rotor base body and a sealing element, which extends between the rotor base body and a rotor base body of a rotor blade ring that connects on the low-pressure side, are fixed in the axial direction on both sides. | 01-29-2009 |
20090035144 | QUICK ASSEMBLY BLADE FOR A CEILING FAN (3) - A quick assembly blade for a ceiling fan includes a blade frame, a blade and a press board. The blade frame is fixed with three studs and an engage position-limiting unit located among the three studs, with the engage pin able to be shifted up and down at the top end of the position-limiting unit. The blade is bored with a through hole at a location matching with the position-limiting unit of the blade frame. The press board is pressed and fixed on the blade, provided with a position-limiting portion. When the press board is pushed to move horizontally to the rear end of the blade, the engage pin will automatically be inserted in the position-limiting portion to keep the press board in position and prevent it from disengaging from the blade, able to quickly assemble the blade on the blade frame. | 02-05-2009 |
20090053065 | FAN BLADE RETAINING STRUCTURE | 02-26-2009 |
20090092497 | Securing element for fastening moving blades - A securing element for securing the position of moving blades in slots, running at least mainly in the axial direction, of a rotor parent body of a turbomachine rotor is described, comprising a plate-shaped parent body, wherein the parent body has an approximately central recess which is formed between two end sections of the parent body and defines a center section, running between the two end sections, of the parent body, wherein the two end sections have bearing surfaces running parallel to one another. | 04-09-2009 |
20090116965 | Arrangement for axially securing rotating blades in a rotor, sealing element for such an arangement, and use of such an arrangement - An arrangement is presented for axially securing rotating blades in a rotor, having a shaft collar on whose external circumference rotating blade securing grooves which extend in the axial direction of the rotor are provided. At one end side face of the shaft a projection is arranged in the region of the securing grooves, in which projection a circumferential groove which is open radially towards the outside is provided and said projection having securing grooves which are arranged in each rotating bade, sheet-metal-shaped sealing elements which each engage in the circumferential groove and in the securing groove and form an end side sealing ring in the circumferential direction being provided for axially securing the rotating blades, and at least one of the sealing elements comprising a sheet metal strip which is attached to said sealing ring in order to secure the sealing elements against displacement in the circumferential direction. | 05-07-2009 |
20090175729 | Fan rotor assembly - A fan rotor assembly has an inner rotor, an outer rotor, a central retainer and a central shaft. The inner rotor has multiple first blades. The outer rotor is stacked on the inner rotor and has multiple second blades. The central retainer is mounted through the inner and outer retainers. The central shaft is mounted in the central retainer under the inner rotor. The fan rotor assembly with first and second blades provides excellent airflow. | 07-09-2009 |
20090185909 | Self-assembly micro blade - The present invention relates to a self-assembly micro blade applied to a micro fan. The micro fan combines at least a self-assembly micro blade and a motor using an actuator as the main body of the micro fan. The self-assembly micro blade includes at least a movable part of a microstructure, at least an elastic joint provided between an outer ring of the micro fan and the movable part. The elastic joint is composed of a polyimide film, which is heated to contract and generate surface tension by using a reflow process so as to lift up the movable part of the microstructure; moreover, the movable part is bent in a curved form through the elastic link exhibits a multi-layer shape by serially connecting at least two movable parts so as to complete the self assembly of the micro blade, thereby increasing air flow rate and improving air flow length. | 07-23-2009 |
20090220345 | Closing Assembly for a Blade Ring of Turbomachinery - The invention relates to a closing assembly for closing the gap remaining between the first and last blade of a blade ring that is inserted into a peripheral groove of turbomachinery. Said assembly comprises at least two parts each of which can be hooked onto projections that form an undercut in said peripheral groove and comprises a securing element, which secures the parts from becoming detached from the peripheral groove. To provide a closing assembly for closing the remaining gap, which can be simply and cost-effectively detached and which reliably withstands high mechanical stress, the securing element is mounted to rotate about its longitudinal axis between the two parts and has a key head and a web. The web of the securing element can be positioned by rotation is such a way that to fit the parts in the peripheral groove, said parts can be displaced in relation to one another and to secure the parts from being detached from said groove, the web of the securing element can be placed against at least one lateral face of one of the parts. | 09-03-2009 |
20090226321 | LOCKING OF THE BLADES IN A FAN ROTOR - A fan rotor is provided. Each blade of the fan rotor is held by a bolt. Each blade includes a blade root engaged in a groove of the rim and held by a bolt. The bolt includes a concave plate with its curve directed upstream. | 09-10-2009 |
20090252610 | Turbine blade retention system and method - A retention system retains a turbine blade dovetail in a retention ring dovetail slot. The retention system includes a retention opening formed in the blade dovetail. A through hole is formed in the retention ring, wherein the through hole is positioned such that it is aligned with the retention opening when the dovetail is assembled in the dovetail slot. A connector is disposed in the through hole and engages the retention opening. In this manner, undesirable relative movement of parts can be reduced or eliminated, thereby preventing excessive wear. | 10-08-2009 |
20090252611 | Axial compressor blade retention - An axial retention system for restraining axial movement of a machine component having a dovetail within a complimentary-shaped dovetail slot includes: a first substantially T-shaped groove formed in a bottom surface of the dovetail slot; a second substantially T-shaped groove formed in a bottom surface of the dovetail, the first and second grooves in alignment when the dovetail is located within the dovetail slot to thereby form a closed periphery substantially T-shaped slot having a stem portion and a lateral cross portion at one end of the stem component, wherein the other end of the stem is open; and a compressible locking clip adapted for insertion within the substantially T-shaped slot, the locking clip having a pair of oppositely extending lugs receivable in opposite ends of the lateral cross portion. | 10-08-2009 |
20090269202 | FAN ROTOR FOR A TURBOMACHINE OR A TEST ENGINE - A fan rotor, in particular for a turbomachine, the rotor comprising a disk carrying blades having roots engaged in substantially axial grooves in the outer periphery of the disk, a substantially frustoconical annular spinner mounted on the disk upstream from the blades, and axial retention means for retaining the blades on the disk in the upstream direction, which retention means are formed integrally with the spinner. | 10-29-2009 |
20090324414 | BLADE FASTENING MEANS OF A TURBINE - A turbine-blade locking device having a wedge movable in an axial direction is disclosed. The wedge is movable in the axial direction by a tensioning device, as a result of which a force is produced in the axial direction. The force in the axial direction causes the turbine blade to be pressed against the blade holder. | 12-31-2009 |
20100008783 | Gas Assisted Turbine Seal - A dovetail seal assembly for sealing a gap between a bucket dovetail and a rotor. The dovetail seal assembly may include a sealing slot positioned about the dovetail, a high-pressure supply hole in communication with the sealing slot, and a deformable seal positioned about the sealing slot and into the gap. | 01-14-2010 |
20100014978 | Turbine rotor with locking plates and corresponding assembly method - A turbine rotor with a rotor disc, a plurality of slots arranged on the rotor disc, a plurality of blades having blade roots and arranged in the slots, and a plurality of locking plates fitted in a position between the rotor disc and the blades are provided. The first gaps on radially outside edges and second gaps on radially inside edges, relative to an axis of rotation of the rotor disc, are formed between neighboring locking plates. At least one of the first gaps is smaller than the corresponding second gap, wherein at least one first gap and corresponding second gaps are intentionally introduced. | 01-21-2010 |
20100047073 | TURBINE BLADE ASSEMBLY - A turbine blade assembly, in particular of a gas turbine, is provided. The turbine blade assembly includes a turbine disc with rotor blades inserted into notches of the turbine disc and locking plates that are placed inside circular grooves with rims in the turbine disc and in the rotor blade. The edges of the locking plates that are oriented towards the center of the turbine disc are castellated by providing teeth and accordingly a part of the rim of the circular groove of the turbine disc is also castellated by providing gaps and whereby the gaps of the rim match the teeth of the locking plates. The locking plates have a spring-back force to provide both locking and sealing capabilities during engine operation. | 02-25-2010 |
20100086409 | WIND TURBINE ROTOR - A wind turbine rotor comprising a hub and a plurality of blades. The hub comprises a plurality of sites, each having a pair of spaced apart annular bearings for receiving a respective wind turbine blade. Each blade has a spar extending along a substantial portion of the length of the blade and protrudes from the proximal end of the blade. The spar protrudes into and is rotatably received within the respective spaced apart bearings and is fixed to the hub. | 04-08-2010 |
20100150726 | ARTICLE AND ULTRASONIC INSPECTION METHOD AND SYSTEM THEREFOR - A method, system and article adapted for ultrasonic inspection of the article. The article is disk-shaped and has axially-oriented slots circumferentially spaced from each other at a periphery of the article, with members secured at the periphery of the article such that each member has a retention feature that extends into and engages a corresponding one of the slots so as to secure the members to the slots. Cavities are defined by and between the slots and radially-inward extremities of the retention features within the slots. The inspection method and system entail the use of at least one ultrasonic transducer placed within at least a first of the cavities defined by a first of the slots. The transducer is configured and oriented to perform a diagnostic technique on the article by emitting an ultrasonic signal that intersects an interior surface of a second of the slots immediately adjacent the first slot. | 06-17-2010 |
20100183444 | FAN BLADE PRELOADING ARRANGEMENT AND METHOD - The fan blade includes a blade root at one end thereof configured for sliding insertion into a substantially axially extending slot defined in a periphery of a fan rotor hub. The blade comprises a first passageway extending at least partially through the blade root, in a direction generally parallel to an axial direction of the slot. It also comprises a second passageway extending at least partially through the blade root to intersect with the first passageway. A first member is provided in the first passageway, the first member configured to be retained in the first passageway once inserted therein, and a second member is provided in the second passageway, the second member having one end in cooperating engagement with the end of the first member. The second member has a portion projecting out of the bottom face of the blade root a distance sufficient to contact an inner surface of the slot and thereby force the blade outwardly in the slot. | 07-22-2010 |
20100196164 | Turbine Coverplate Systems - In one embodiment, a coverplate may be configured to axially overlay a plurality of blade retaining slots within a wheel post of a rotor wheel. The coverplate may include a tab for radially securing the coverplate within a complementary groove of the rotor wheel and an aperture configured to align with a corresponding aperture of the turbine wheel to receive a fastener for axially securing the coverplate to the rotor wheel. | 08-05-2010 |
20100221115 | RETENTION STRUCTURES AND EXIT GUIDE VANE ASSEMBLIES - A retention structure includes a center body including an outer surface, an enclosed end, an open end, and a contact section, the outer surface adapted to define a first portion of a flowpath, and the contact section extending radially outwardly from a centerline and located on the enclosed end and configured to reduce a radial and a torsional component of a first load that exceeds a first threshold applied to the contact section, when the turbine rotates and applies the first load to the contact section and an energy absorber coupled to the center body, disposed adjacent to the contact section, and having an outer surface adapted to define a second portion of the flowpath, the energy absorber further adapted to collapse, when the turbine rotates and contacts the energy absorber and applies a second load that exceeds a second threshold to the energy absorber. | 09-02-2010 |
20100284814 | Machine component retention - An axial retention system for restraining axial movement of a first machine component having a dovetail within a complimentary-shaped dovetail slot in a second machine component that includes a first curved groove formed in a bottom surface of the dovetail slot and a second curved groove formed in a bottom surface of the dovetail. The first and second grooves are in alignment when the dovetail is located within the dovetail slot to thereby form a closed periphery aperture. A curved locking clip is received within the closed periphery aperture. An optional cover plate may be placed over the ends of the locking clip, with ends of the locking clip deformed by, for example, swaging. | 11-11-2010 |
20100329873 | RETAINING AND SEALING RING ASSEMBLY - A fan blade retaining and sealing ring assembly for an aft side of a bladed disk assembly is disclosed herein. The ring assembly includes an inner ring operable to prevent aft movement of a fan blade positioned in a slot formed in the blade disk. The ring assembly also includes an outer ring operable to seal against a platform of the fan blade. The inner ring and the outer ring are formed from different materials. | 12-30-2010 |
20110002787 | Blade Retention at a Compressor Rectifier Stage for Impact Resistance - A rectifier stage of an axial turbine engine compressor is placed directly downstream of the input blower of a turbo-reactor or turboshaft engine compressor. The blade roots of the rectifier stage are housed inside the inner shroud by insertion into respective slots. The blade roots include at least one opening protruding from the slot of the shroud, so as to receive a spiral ring having at least two loops so as to prevent the blade roots from escaping from the respective slots of the inner shroud, and so as to form a connection between the blade roots. A method for retaining blades of a rectifier stage of an axial turbine engine compressor on an inner shroud, in particular a rectifier stage placed directly downstream of the input blower of a turbo-reactor or turboshaft engine compressor, includes positioning a spiral ring having at least two loops inside the openings of the blade roots by threading one end of the ring successively into the openings until all of the spirals of the ring are housed inside the openings. | 01-06-2011 |
20110008173 | TURBINE ROTOR BLADE ASSEMBLY AND STEAM TURBINE - In a turbine rotor blade assembly | 01-13-2011 |
20110014053 | TURBINE BUCKET LOCKWIRE ROTATION PREVENTION - A retention system for a plurality of turbine buckets located in respective mating slots in a turbine rotor wheel includes a plurality of first retention slots formed in outer peripheral portions of the turbine wheel, and a plurality of second retention slots formed in wheel mounting portions of the buckets. The first and second retention slots are aligned to form an annular retention slot extending about a peripheral portion of the rotor wheel. A lockwire is located within the annular retention slot, the lockwire having engaged free ends. A plurality of axially-oriented retaining pins are fixed in the rotor wheel to hold the lockwire in the annular retention slot, and various techniques are employed for at least limiting or substantially preventing circumferential rotation of the lockwire within the annular slot. | 01-20-2011 |
20110014054 | GUIDE VANE OF A GAS TURBINE AND METHOD FOR REPLACING A COVER PLATE OF A GUIDE VANE OF A GAS TURBINE - The guide vane of a gas turbine comprises a blade having an outer platform connectable to a guide vane carrier or gas turbine casing, and at the opposite end an inner platform that carries a cover plate. The inner platform has a dovetail housing to which the cover plate is connected. The method for replacing the cover plate consists in separating the cover plate from the inner platform by cutting along the profile of the dovetail housing, then making the cover plate to slide out of the dovetail housing, thus inserting a new or refurbished cover plate into the dovetail housing. | 01-20-2011 |
20110020125 | Arrangement for axially securing blades in a rotor of a gas turbine - An arrangement for axially securing blades of a rotor of a gas turbine is provided. The arrangement includes a sealing element arranged on the end side surface of the rotor, which may be particularly reliably attached to the rotor by means of a sheet metal strip, the sheet metal strip including a shape-memory alloy. | 01-27-2011 |
20110027092 | ARRANGEMENT FOR AXIALLY SECURING ROTATING BLADES IN AROTOR, AND GAS TURBINE HAVING SUCH AN ARRANGEMENT - An arrangement for axial locking of rotating blades in a rotor is provided. The arrangement includes a shaft collar, a projection, plate-like sealing elements, and a blocking element. The sealing elements are provided for axially securing the rotating blades. At least one sealing element has an opening for securing the sealing elements against displacement in the circumferential direction. The blocking element is inserted in a recess from the end side of the shaft collar and blocks the displacement path of the sealing element. In order for the blocking element to be secured against unintentional releasing, the blocking element is fastened on the rotor disk using plastic deformation. | 02-03-2011 |
20110027093 | ANTI-WEAR DEVICE OF A TURBOMACHINE ROTOR - The present invention relates to an anti-wear device of a turbomachine rotor comprising a disk ( | 02-03-2011 |
20110038731 | ROTOR ASSEMBLY FOR A GAS TURBINE - A rotor assembly, for a gas turbine, has a plurality of rotor discs interconnected by an axially extending rim. The outside of the rim has a circumferential array of dovetail slots and the underside of the rim has a circumferential channel which extends radially part way into the slots, the respective discs thus being interconnected axially across the channel by an array of circumferentially spaced connecting portions. There is an array of blades, each blade having a blade root secured in a respective one of the dovetail slots. | 02-17-2011 |
20110052399 | AEROFOIL BLADE ASSEMBLY - An aerofoil blade assembly having a rotor disc having a radially outer surface provided with an axial slot and a radially inner surface provided with a circumferential slot, wherein the lower region of the axial slot intersects the upper region of the circumferential slot; an aerofoil blade having a blade root which is received by the axial slot and which is provided with a locating slot which corresponds to the circumferential slot; a retention key which engages with the circumferential slot and the locating slot to restrict axial displacement of the aerofoil blade with respect to the rotor disc, the retention key being provided with socket which, when the retention key is engaged in the circumferential slot and the locating slot, is substantially aligned with the axial slot. | 03-03-2011 |
20110123341 | DEVICE FOR AXIAL RETENTION OF MOBILE VANES MOUNTED ON A ROTOR DISC - A device for axial retention of mobile vanes mounted on a rotor disc includes two open rings, superimposed. At least one of the rings includes a rotating stop mechanism configured to cooperate with at least one hook of the disc. The two open rings are mounted in a discontinuous groove formed in the hooks, at the end of teeth situated on the periphery of the rotor disc, such that the rotating stop mechanism of the first ring is placed in the opening of the second ring. The significance of contact surfaces between the two rings allows a damping of vibrations during operation. | 05-26-2011 |
20110135481 | SYSTEMS AND METHODS FOR ASSEMBLING A ROTOR LOCK ASSEMBLY FOR USE IN A WIND TURBINE - A method of assembling a rotor lock assembly for use in a wind turbine. The wind turbine includes a rotor rotatably coupled to a generator by the rotor shaft. The generator and the rotor shaft are supported from a bedplate frame. The rotor shaft includes a rotor lock disk. The method includes coupling a support frame to the bedplate frame. The support frame is positioned adjacent to the rotor lock disk. A plurality of lock pin housings are coupled to the support frame. Each lock pin housing of the plurality of lock pin housings is positioned with respect to the rotor lock disk. A plurality of lock pins is provided. Each lock pin of the plurality of lock pins is configured to engage the rotor lock disk. Each lock pin is coupled between a corresponding lock pin housing of the plurality of lock pin housings and the rotor lock disk to facilitate limiting a rotation of the rotor shaft. | 06-09-2011 |
20110164983 | Locking Spacer Assembly - The present application describes a locking spacer assembly for use with a groove in a rotating disk. The locking spacer assembly may include a locking spacer with a leg and a wedge tool in contact with the leg so as to pull the leg inward and into the groove. | 07-07-2011 |
20110171031 | Turbomachine Rotor Comprising a Pretensioning Device for Pretensioning a Guide Vane - A turbomachine rotor, a rotor blade and a method for assembling a turbomachine rotor are provided. The turbomachine rotor includes a rotor blade with a blade root, a wheel disk with a groove in which the blade root engages such that the rotor blade is maintained in the groove in a positive fit in a radial direction. Further, a pretensioning device is provided, which is supported on the wheel disk as well as on the blade root and which exerts a pretensioning force on the blade root in the radial direction. The pretensioning device is designed such that the pretensioning force can be adjusted when assembling the turbomachine rotor. | 07-14-2011 |
20110176923 | SEAL PLATE AND BUCKET RETENTION PIN ASSEMBLY - A disk for a machine rotor includes a disk body having an outer periphery formed with a plurality of axially-oriented slots; a plurality of buckets, each bucket having an airfoil portion and an attachment portion, the attachment portion loaded axially into a respective one of the plurality of axially-oriented slots. A plurality of arcuate seal plate segments arranged about the outer periphery of the disk body, each covering at least two of the plurality of axially-oriented slots and respective attachment portions of the plurality of buckets. A retention pin extends axially through each of the plurality of arcuate seal plate segments and into an axially oriented bore in the disk body. The retention pin has an inner end engageable with a locking key and adapted to move the locking key into a locking position which prevents axial movement of a pair of adjacent ones of the plurality of buckets. | 07-21-2011 |
20110176924 | DEVICE ADAPTED TO BE FITTED WITH PROPELLER BLADES - A device adapted to be fitted with propeller blades includes a first retention ring including over a periphery thereof a plurality of radial bores; and a second retention ring including over a periphery thereof a plurality of radial bores, the first and second retention rings being mounted one on top of the other in the radial direction, each bore in the first retention ring being positioned opposite a bore in the second retention ring, a bore in the first retention ring arranged opposite a bore in the second retention ring forming a bore pair adapted to receive a foot of a blade. | 07-21-2011 |
20110229328 | Turbomachine Blade Locking Structure Including Shape Memory Alloy - A system for locking blades to a rotor of a turbomachine including adjacent pairs of generally axially extending grooves for receiving blades inserted in an axial direction. A circumferential slot is disposed around the periphery of the rotor and a locking device assembly is located in the circumferential slot between an adjacent pair of grooves. The assembly includes a last locking device, a spacer and key member formed of a shape memory alloy. The key member is located in a gap between the last locking device and the spacer. The shape memory alloy key member is heated to cause a transition from a martensite to an austenite phase to cause the key member to engage and press against opposing faces of the last locking device and the spacer to increase a force applied to a respective pair of blades in the adjacent pair of grooves. | 09-22-2011 |
20110250071 | TURBINE WHEEL WITH AN AXIAL RETENTION SYSTEM FOR VANES - A turbine wheel includes: a plurality of blades, a rotor including a disk having the blades mounted at a periphery thereof, each blade including an airfoil with a foot secured to a platform carrying an attachment member engaged in a housing that opens into the periphery of the disk and that extends axially between two opposite side faces of the disk, the housings being spaced apart from one another by portions of the disk that form teeth, and an axial retention plate retaining the blades on the disk and including a retention plate situated on one side of the disk. On the other side of the disk, the teeth of the disk present portions in relief that project radially and that form abutments pressing axially against the portions in relief that are formed under the platforms of the blades and that are set back relative to side faces of the attachment members situated beside a second side face of the disk, and side faces of the attachment members of the blade and of the disk at its periphery are situated in substantially a same plane on each side of the disk. | 10-13-2011 |
20110255982 | TURBINE BLADE RETENTION DEVICE - A turbine blade assembly has a turbine blade with a root section and an airfoil section. The root section has one of a radially extending groove or flange, and a retainer element has the other of the groove and the flange. The groove receives the flange to hold the retainer element and the blade together. The retainer element has axial ends extending radially inwardly to secure a turbine blade assembly within a disk slot in a turbine rotor disk. A method is also disclosed. | 10-20-2011 |
20110255983 | DEVICE FOR ATTACHING HAMMER CLAMP BLADES, ASSOCIATED COMPRESSOR HUB, COMPRESSOR AND TURBINE ENGINE - The invention relates to a locking device for enabling the circular locking of a set of blades provided with a hammer base ( | 10-20-2011 |
20110262278 | FAN BLADE RETENTION SYSTEM - A fan comprises a rotatable hub assembly having an inner anchor assembly, a plurality of fan blades, a motor assembly, and a plurality of cables. The outer ends of the cables are coupled to the outer ends of the fan blades, and the inner ends of the cables are coupled to the inner anchor assembly. The inner anchor assembly may further include a disc-shaped plate and a plurality of inner anchor members to which the cables may be coupled. The inner anchor members may include a rear anchor portion and fore anchor portion, and these anchor portions may be angularly offset. A plurality of winglets and/or outer anchor members may be coupled to the outer ends of the fan blades to which the outer ends of the cables may be coupled. The outer ends of the cables may further comprise swaged tips outboard of the winglets and/or outer anchor members. | 10-27-2011 |
20110305576 | GAS TURBINE ENGINE BLADE MOUNTING ARRANGEMENT - A mounting arrangement for a gas turbine engine blade having a root employs a lightweight, simple and economical leaf spring spacer which biases the blade root in a radially outward direction to minimize unwanted movement of the root within a conforming slot in a blade hub under conditions such as windmilling when centrifugal force alone is inadequate to tightly seal the root within the slot. | 12-15-2011 |
20110311366 | TURBINE WHEEL PROVIDED WITH AN AXIAL RETENTION DEVICE THAT LOCKS BLADES IN RELATION TO A DISK - A turbine wheel including a plurality of blades, each of the blades presenting an airfoil, a platform, and an attachment member, a disk having the blades mounted at the periphery thereof, the attachment member of each blade being engaged in a housing that opens into a periphery of the disk and extending axially between two opposite faces of the disk, the housings being separated by teeth, and an axial retention device for retaining the blades. The disk includes a first stop member, and the platform of the blade includes a projection projecting axially beyond one of the faces of the disk. The projection includes a second stop member. The axial projection, the second stop member, and the face of the disk together form a groove facing towards the axis of the disk, the groove serving to receive the axial retention device. | 12-22-2011 |
20110318187 | SEALING DEVICE - A sealing device for sealing a gap between a dovetail of a bucket assembly and a rotor wheel is disclosed. The sealing device includes a cover plate configured to cover the gap and a retention member protruding from the cover plate and configured to engage the dovetail. The sealing device provides a seal against the gap when the bucket assembly is subjected to a centrifugal force. | 12-29-2011 |
20120027605 | TURBOMACHINE BLADE, A ROTOR, A LOW PRESSURE TURBINE, AND A TURBOMACHINE FITTED WITH SUCH A BLADE - The invention relates to a turbomachine blade made of composite material and presenting a root with a bulb-shaped end suitable for engaging in a slot of a rotor disk. In characteristic manner, the end of the root of the blade is provided, beside one of its front faces, with a projecting portion having two symmetrical fins about the axial midplane of the root, each fin having a bearing face suitable for limiting tilting of the blade relative to the rotor disk about the axial direction. | 02-02-2012 |
20120034088 | Method for Connecting a Tension-Torsion Strap - An apparatus may comprise a housing, a first member, and a second member. The housing may have a first end, a second end, a first side, a second side, an opening located in the first end, and a passage extending from the opening. The first member may extend from the first side. The first member may have a first channel in communication with the passage and the channel has a first center axis. The second member may extend from the first side. The second member may have a second channel in communication with the passage and the second channel has a second center axis substantially aligned with the center axis of the channel in the first member. | 02-09-2012 |
20120039719 | Rotor section for a rotor of a turbomachine, and rotor blade for a turbomachine - A rotor section for a rotor of a gas turbine, a rotor blade, and a blocking element are provided. The rotor section includes a rotor disk including rotor blades that are inserted thereon in holding grooves and that are secured against sliding along the holding grooves by means of a sealing element arranged at the end face. In order to specify a reliable, simple, and easy-to-design construction for the circumferential fixing of the sealing elements, it is proposed that each sealing element be secured by one blocking element, which engages in a hole arranged at the end face in the rotor blade root. | 02-16-2012 |
20120045340 | ROTOR LOCKING DEVICE AND METHOD FOR LOCKING A ROTOR OF A WIND TURBINE - The invention relates to a mobile rotor locking device for locking a rotor of a wind turbine, the rotor locking device being designed to lock a rotor in such a way that it is prevented from rotating about a horizontal axis, and that a longitudinal axis of a rotor blade is fixed in a vertical plane. The invention also relates to a kit and a locking member for a mobile rotor locking device and to a method for locking a rotor of a wind turbine. According to the invention, the rotor locking device is characterized in that the rotor locking device is designed to fix a main shaft, on which a rotor is disposed torsionally stiffly, so that it is prevented from rotating about its longitudinal axis. | 02-23-2012 |
20120045341 | FAN ROTOR FOR AN AIRPLANE TURBOJET - A fan rotor for an airplane turbojet including locking blade roots in the respective grooves of an airplane turbojet fan rotor. Each blade root is housed in a groove that is closed by a main latch and by an additional latch that is distinct from the main latch and that is spaced apart therefrom by a predetermined distance. | 02-23-2012 |
20120057980 | AXIAL LOCKING SEALS FOR AFT REMOVABLE TURBINE BLADE - A turbine blade rotor assembly provides sealing for the rotor components and bi-direction axially locking of the blades on the rotor using a seal plate on the aft exhaust side without axial locking on the forward intake side of the rotor and blade array. As a result, the blades can be removed from the aft direction without moving the turbine casing cover. | 03-08-2012 |
20120063907 | CIRCUMFERENTIAL BLOCKING DEVICE OF CLAMP VANES FOR TURBINE ENGINE, WITH IMPROVED RADIAL DEPLOYMENT - The invention relates to a device ( | 03-15-2012 |
20120087798 | TURBINE BUCKET LOCKWIRE ROTATION PREVENTION - A retention system for a plurality of turbine buckets located in respective mating slots in a turbine rotor wheel includes a plurality of first circumferentially-oriented retention slots formed in outer peripheral portions of the turbine wheel; a plurality of second circumferentially-oriented retention slots formed in wheel mounting portions of said buckets, the first and second circumferentially-oriented retention slots aligned to form an annular lockwire retention slot; and a lockwire located within the annular lockwire retention slot. A first surface feature on one or both of the turbine rotor wheel and one or more of said plurality of turbine buckets is adapted to engage a second surface feature on the lockwire for preventing rotation of the lockwire beyond predetermined limits. | 04-12-2012 |
20120087799 | AXIAL RETENTION DEVICE FOR TURBINE SYSTEM - An axial retention device for a turbine is disclosed. The axial retention device includes a latch associated with a mating surface of one of a turbine component and a support structure. The latch has an outward bias and includes an axial load surface. The axial retention device further includes a pocket defined in a mating surface of the other of the turbine component and the support structure. The pocket is configured to accept the latch therein and includes a mating axial load surface. Engagement of the latch and the pocket allows the axial load surface and the mating axial load surface to interact, preventing axial movement of the turbine component with respect to the support structure in at least one direction. | 04-12-2012 |
20120107124 | AIRFOIL ATTACHMENT ARRANGEMENT - An example airfoil retention arrangement includes a retention assembly having a first retention segment and a second retention segment. Each of the retention segments is separately moveable to an installed position relative to an airfoil assembly and a support structure. The retention segments each have a portion position between a lip of the airfoil assembly and a collar of the support structure when the retention segments are in the installed position. The retention assembly is configured to limit radial movement of an airfoil relative to the support structure when in the installed position. | 05-03-2012 |
20120107125 | REINFORCED FAN BLADE SHIM - A shim configured to be inserted between a fan blade root of a turbojet and a bottom of a compartment in which this root is housed, the compartment being delimited by a fan disk. The shim includes a metal stiffener including at least one external element made of an elastomer material, and including a support surface of the external element. The support surface includes at least one corrugated zone. | 05-03-2012 |
20120114490 | TURBINE ASSEMBLY AND METHOD FOR SECURING A CLOSURE BUCKET - According to one aspect of the invention, a turbine assembly is provided, wherein the turbine assembly includes a drum rotor comprising a slot and a closure bucket configured to be placed in the slot, the closure bucket including a lock pin disposed in a base member of the closure bucket. In addition, a portion of the lock pin is configured to rotatably extend into a cavity in the slot thereby securing the closure bucket within the slot. | 05-10-2012 |
20120121428 | BLADE RETENTION DISK - A blade retention disk includes, on its external surface, a peripheral annular groove configured to receive a plurality of blade roots of the hammer attachment type, the peripheral annular groove including a loading orifice intended for the introduction of blade roots inside the peripheral annular groove. The retention disk also includes: a crown covering the peripheral annular groove; a crown centering device to center the crown, the crown centering device and the crown forming an air supply enclosure from the bottom of the peripheral annular groove; at least one orifice opening in the air supply enclosure, the orifice being configured to introduce cooling air into the air supply enclosure. The blade retention disk finds a direct application in the field of low pressure turbines for aircraft turbine engines. | 05-17-2012 |
20120128498 | BLADED DISK ASSEMBLY - A bladed disk assembly is disclosed herein. The bladed disk assembly includes a disk centered on an axis. The disk has at least one groove extending along the axis. The bladed disk assembly also includes a blade received in the groove. The bladed disk assembly also includes a retaining clip contacting the blade and limiting movement of the blade along the axis. The retaining clip is engaged with the disk through a snap-fit. | 05-24-2012 |
20120171040 | DAMPER COVERPLATE AND SEALING ARRANGEMENT FOR TURBINE BUCKET SHANK - A bucket pair in a turbomachine includes a first bucket having an airfoil and a shank; a second adjacent bucket having a second airfoil and a second shank adjacent the first shank; a first axial slot in the first shank; and an elongated, straight damper pin adapted to seat in the first axial slot, the damper pin formed with slanted forward and aft end faces. | 07-05-2012 |
20120177498 | AXIAL RETENTION DEVICE FOR TURBINE SYSTEM - An axial retention device for a turbine system is disclosed. The axial retention device includes a pocket defined in a mating surface of one of a turbine component and a support structure. The pocket includes a first axial load surface. The axial retention device further includes a latch comprising a base member and a pivotal member. The base member is associated with a mating surface of the other of the turbine component and the support structure. The pivotal member is configured to engage the pocket and includes a first mating axial load surface. Engagement of the pivotal member and the pocket allows the first axial load surface and the first mating axial load surface to interact, preventing axial movement of the turbine component with respect to the support structure in the at least one direction. | 07-12-2012 |
20120177499 | BLADE FASTENING HAVING SAFETY DEVICE FOR TURBINE BLADES - A safety device for a turbine blade is provided. The safety device includes a shear pin, a clamping piece and a securing element, wherein the shear pin is arranged in a corresponding bore in the turbine blade foot and the clamping piece is designed having an upper limb and a lower limb, wherein the clamping piece exerts a radial force on the turbine blade foot for radial safeguarding. | 07-12-2012 |
20120189453 | MECHANICAL JOINT - A mechanical joint for joining two components, the joint having a male part on one component and a corresponding female part on the other component. The male and female parts have respective castellations which intercalate on insertion of the male part into the female part along a direction of insertion. Respective abutment surfaces are formed on the projections of the castellations. The castellations are configured such that, after the insertion of the male part into the female part, the male and female parts can be rotated relative to each other around the direction of insertion to bring: (i) the abutment surfaces into facing alignment and thereby prevent the parts from being pulled apart, and (ii) the indentations of the castellations into facing alignment. The joint has one or more locking members which are insertable into the facing indentations to prevent further relative rotation of the male and female parts. | 07-26-2012 |
20120201685 | JOINING MECHANISM AND METHOD FOR INTERLOCKING MODULAR TURBINE ENGINE COMPONENT WITH A SPLIT RING - A modular airfoil assembly ( | 08-09-2012 |
20120237350 | TURBINE BLADE WITH MATE FACE COOLING AIR FLOW - A gas turbine engine blade comprises a dovetail, a shank extending from the dovetail, an airfoil, and a platform between the shank and the airfoil. The platform comprises a side wall extending between an upstream side and a downstream side of the platform. A first pin channel extends from the upstream side of the sidewall and a second pin channel, co-axial with the first pin channel, extends from the downstream side of the sidewall. The first channel includes a radial notch at the upstream longitudinal end of the first pin channel. | 09-20-2012 |
20120237351 | RETENTION FOR BONDED HOLLOW FAN BLADE COVER - A two part airfoil has a suction side, a pressure side, a rib extending from one of the pressure side or the second side, the rib having a groove therein, and a riblet extending from an other of the pressure side or the suction side, the riblet fitting within the groove. | 09-20-2012 |
20120244004 | COMPONENT LOCK FOR A GAS TURBINE ENGINE - A lock assembly includes a lock body with an undercut slot which receives a retaining wire of a polygon shape. | 09-27-2012 |
20120251329 | ROTOR STRUCTURE - The rotor structure is provided with a rotation shaft body in which a blade groove is formed at an outer circumference part, and extends in a circumferential direction of the axis line, and a plurality of blade bodies which are arrayed in the circumferential direction at the outer circumference part of the rotation shaft body, wherein a blade fixing piece is installed so as to be a positioned between at least one set of adjacent two blade bodies in the circumferential direction inside the blade groove, a projected part is formed at where either an opening wall part or the groove opening side of the blade groove and the blade fixing piece, and a recessed part which is fitted into the projected part is formed at where the other one of them. | 10-04-2012 |
20120257976 | LOCKING DEVICE ARRANGEMENT FOR A ROTATING BLADED STAGE - A locking device arrangement for a rotating bladed stage is provided and includes a wheel formed to define a substantially circumferential slot and three slot sections, one of the slot sections including one radial slot and two lock slots to permit blade and blade lock installation along the circumferential slot, respectively, the other slot sections including a lock slot to permit blade lock installation along the circumferential slot, and the three slot sections being separated from one another with angular offsets such that the wheel is mass balanced substantially evenly about a desired center of rotation with the blade locks installed and to reduce accumulation of flowpath gaps. | 10-11-2012 |
20120301308 | GAS TURBINE COMPRESSOR LAST STAGE ROTOR BLADES WITH AXIAL RETENTION - A rotor blade and blade retention key assembly includes: a radially outer airfoil, a shank and a radially inner attachment dovetail. The attachment dovetail has a radially innermost surface formed with a notch at one axial end thereof, and a retention key is received in the notch, and rotatable from a retracted position where a retention key portion is substantially flush with the radially innermost surface, to an extended position where the retention key portion projects inwardly from said radially innermost surface and into a recess or pocket formed in a rotor wheel slot to prevent axial movement of the blade within the slot. | 11-29-2012 |
20120315144 | TURBOMACHINE BLADE LOCKING SYSTEM - Systems are disclosed herein for enhancing the longevity of turbomachine components. Such systems include a turbomachine blade that has a blade portion extending from a base portion. The base portion includes an axial rail configured to extend into an axial groove disposed in a rotor of a turbomachine. The axial rail includes a first locking recess configured to align with a second locking recess along the axial groove. The system also includes a blade locking assembly having a first locking insert and a second locking insert. The first locking insert is configured to be inserted in both the first and second locking recesses. The second locking insert is configured to be inserted in the first or second locking recess adjacent the first locking insert. | 12-13-2012 |
20120321476 | RETENTION DEVICE FOR A ROTATING BLADE - A blade assembly including: a hub which is rotatable about an axis; at least one blade having an aerofoil portion and a root, wherein the root is coupled to the hub using a primary retention device which prevents radial separation of the root and hub in normal use; and, a secondary retention device having a root part and a hub part, the root part being located radially inwards of the hub part in a retention cavity in use, wherein at least a portion of the root part enters the retention cavity via an interlock which prevents radial separation of the root and hub in the event of a primary retention device failure. | 12-20-2012 |
20120321477 | Rotor device for a jet engine with a disk wheel and several rotor blades - The present invention proposes a rotor device for a jet engine with a disk wheel and several rotor blades connected to said disk wheel, with the rotor blades being arranged in each case via a blade root substantially in the axial direction inside recesses of the disk wheel. Several locking segments are provided in the recesses of the disk wheel for axially locking the rotor blades, said locking segments interacting on the one hand with grooves of the rotor blades and on the other hand with at least one groove of the disk wheel. In the area of the groove of at least one of the rotor blades between the groove of the rotor blade and a locking segment there is a positive fit preventing a relative movement between the rotor blades and the locking segments. | 12-20-2012 |
20130022469 | Turbine Rotor Non-Metallic Blade Attachment - In an engine disk and blade combination, the metallic disk has a plurality of first blade attachment slots and a plurality of second blade attachment slots circumferentially interspersed with each other. There is a circumferential array of a plurality of first blades. Each first blade has an airfoil and an attachment root. The attachment roots are respectively received in associated said first attachment slots. There is a circumferential array of second blades. Each second blade has an airfoil and an attachment root. The attachment roots are respectively received in associated said second slots. The first blades and second blades are non-metallic. The first blades are radially longer than the second blades. The first slots are radially deeper than the second slots. | 01-24-2013 |
20130028743 | Systems, Methods, and Apparatus for Sealing a Bucket Dovetail in a Turbine - Certain embodiments of the invention may include systems methods, and apparatus for sealing a bucket dovetail in a turbine. According to an example embodiment of the invention, a method is provided for sealing a gap between a bucket dovetail and a rotor wheel slot. The method can include modifying a bucket tab associated with the bucket dovetail to accept a seal tab, wherein the seal tab is configured to expand as a function of temperature; maintaining the seal tab in contact with the modified bucket tab; sealing a gap between the bucket dovetail and the rotor wheel slot with the seal tab; and modifying at least a portion of the seal tab as a function of temperature for further sealing gap between the bucket dovetail and the rotor wheel slot. | 01-31-2013 |
20130039770 | GAS TURBINE ROTOR WITH PURGE BLADES - A rotor for a gas turbine engine includes a plurality of turbine blades extending radially outwardly of a rotor body. A plurality of purge blades are positioned to rotate with the rotor body, and to drive air radially outwardly toward the turbine blades. | 02-14-2013 |
20130052024 | Turbine Nozzle Vane Retention System - The present application provides a turbine nozzle vane retention system. The turbine nozzle vane retention system may include a number of nozzles with a platform, a slot extending into the platform, and a pin extending between the slot of a first nozzle and the slot of a second nozzle, | 02-28-2013 |
20130052025 | REPLACEABLE STAKING INSERT ASSEMBLY AND METHOD - A rotor assembly. The rotor assembly may include a rotor, at least one axial slot positioned about the rim of the rotor having a first staking recess positioned therein, a blade positioned within each of the axial slots having a second staking recess positioned therein, a staking insert having a base portion and a projection extending therefrom with the base portion being disposed within the first staking recess and the projection being disposed within the second staking recess, and a shim positioned within the first staking recess adjacent to the base portion, opposite the projection, of the staking insert. The first staking recess retains the staking insert while the projection of the staking insert retains the blade in both the aft and forward directions. | 02-28-2013 |
20130052026 | AXIAL RETENTION SYSTEM FOR A BLADED ROTOR WITH MULTIPLE BLADE TYPES - A bladed rotor includes a blade lock mountable to a rotor hub adjacent to a multiple of blade slots. The blade lock includes at least one interface feature adjacent to a first of the multiple of blade slots. A first rotor blade includes a blade feature which interfaces with the interface feature to permit the first rotor blade to be axially mounted within the first of the multiple of blade slots but not within a remainder of the multiple of blade slots. | 02-28-2013 |
20130121836 | BLADE CONNECTION FOR A ROTOR BLADE OF A WIND TURBINE - A blade connection for a rotor blade of a wind turbine having a plurality of receptacles which extend in the longitudinal direction of the rotor blade and can each receive a longitudinal bolt and are in contact with a component having an inner thread for the longitudinal bolt. The rotor blade is manufactured from two materials, at least in the region of the blade connection, wherein a first material is a composite material, and a second material is a composite material provided with at least one reinforcement layer made of metal and/or ceramic. The receptacles are composed of the first material and the second material is bonded to the first material. | 05-16-2013 |
20130136605 | DEVICE FOR LOCKING A ROOT OF A ROTOR BLADE - A device for locking a root of a rotor blade in a groove in a rotor disk of a turbomachine including: a circular ring sector configured to be mounted, transversely to the axis of the turbomachine, in a groove in the rotor disk; at least one locking wedge, which is rigidly secured and perpendicular to the ring sector, and extends parallel to the axis of the ring sector so as to hold the root of the blade radially in the groove; and at least one locking tooth extending from the ring sector radially with respect to the axis of the ring sector, so as to prevent the root of the blade from moving axially in the groove. | 05-30-2013 |
20130149159 | GAS TURBINE ENGINE PART RETENTION - A gas turbine engine includes an engine casing structure and a retention block assembly. The engine casing structure includes a pocket which receives the retention block assembly. The retention block assembly includes a stop block and a pin that retains the stop block within the pocket. The stop block is loose relative to the pin. | 06-13-2013 |
20130156588 | ELECTRICAL GROUNDING FOR FAN BLADES - A fan rotor includes a fan blade for use in a gas turbine engine includes a sheath formed of a material that is more conductive than a main fan blade body. A grounding element provides a grounding path from the sheath into a rotor receiving the fan blade. A gas turbine engine incorporating the fan blade is also disclosed. | 06-20-2013 |
20130156589 | TURBINE ROTOR RETAINING SYSTEM - A rotor retaining system for a rotor assembly of a gas turbine engine includes a washer interlocking multiple retaining nuts to prevent relative rotation. The retaining nuts retain a rotor disc and a cover plate in position, respectively. A wire is provided to retain the washer in position and which may dampen vibration during engine operation. | 06-20-2013 |
20130156590 | GAS TURBINE ENGINE ROTOR WHEEL HAVING COMPOSITE MATERIAL BLADES WITH BLADE-ROOT TO DISK CONNECTION BEING OBTAINED BY CLAMPING - A rotor wheel for a gas turbine engine, the wheel including: a metal holder disk including a plurality of teeth at its periphery, the teeth extending radially outwards from the disk; a plurality of composite material blades, each blade including a root engaged between two adjacent teeth of the holder disk and that is held against the teeth by a pivot connection; a clamp disk including a plurality of teeth at its periphery extending in an axial direction, the clamp disk being fastened against the holder disk and on the same axis, with each of its teeth taking up a circumferential position between a blade root and a tooth of the holder disk; and a mechanism exerting a clamping force in a circumferential direction urging the teeth of the clamp disk against the blade roots. | 06-20-2013 |
20130177429 | SYSTEM FOR AXIAL RETENTION OF ROTATING SEGMENTS OF A TURBINE - A turbomachine system includes a turbomachine that includes a rotor that includes a rotational axis, a first rotating segment having a first mating axial mount coupled to a first axial mount of the rotor in a first installed position and a first pin configured to insert into a first inserted position in both a first slot in the rotor and a first mating slot in the first rotating segment. The first pin in the first inserted position is configured to block axial movement of the first mating axial mount relative to the first axial mount. The turbomachine also includes a second rotating segment having a second mating axial mount coupled to a second axial mount of the rotor in a second installed position. The second rotating segment in the second installed position is configured to block removal of the first pin. | 07-11-2013 |
20130189111 | ROTOR FOR A TURBOMACHINE - A rotor for a turbomachine, in particular for a jet engine, having a blade ring which includes multiple differently designed rotor blades ( | 07-25-2013 |
20130216387 | SYSTEM AND METHOD FOR BLADE RETENTION - A system and method for securing a blade within a disk so as to eliminate the need for permanently deforming materials associated with the blade disk is disclosed. A recess is formed generally within each slot used to secure a blade within the disk. A retaining insert is positioned within the recess and a wedge insert is positioned within a slot of the retaining insert, such that a pressure is applied to the retaining insert thereby deflecting the retaining insert into a pre-set radial position to prevent axial movement of the blade within the slot of the disk. | 08-22-2013 |
20130224030 | TURBINE-BLADE RETAINING STRUCTURE AND ROTARY MACHINE HAVING THE SAME - Deformation of end portions of locking pieces exposed through an insertion window portion in the axial direction is prevented, and the occurrence of a crack in a welded portion is prevented. At least one of the end portions of adjacent locking pieces exposed through the insertion window portion is provided with a thick-plate portion that expands in the disc-thickness direction so as to be inside the insertion window portion. | 08-29-2013 |
20130236317 | BLADE CLIP - A clip to connect a blade to a rotor disk, the blade with a root and a tip in a spanwise direction, and a leading edge and a trailing edge in a chordwise direction, the root with a bottom surface, includes a locking mechanism shaped to engage a complementary slot extending into the bottom surface of the blade root in the spanwise direction; a support connected to the locking mechanism extending the length of the bottom surface of the root in the chordwise direction; and first and second arms extending radially inward converging in an axial direction so that the arms are closer at their distal ends to engage the rotor disk. | 09-12-2013 |
20130243601 | CONNECTING SYSTEM FOR METAL COMPONENTS AND CMC COMPONENTS, A TURBINE BLADE RETAINING SYSTEM AND A ROTATING COMPONENT RETAINING SYSTEM - A connecting system for metal component and CMC components, a turbine blade retaining system and rotating component retaining system are provided. The connecting system includes a retaining pin, a metal foam bushing, a first aperture disposed in the metal component, and a second aperture disposed in the ceramic matrix composite component. The first aperture and the second aperture are configured to form a through-hole when the metal component and the ceramic matrix composite component are engaged. The retaining pin and the metal foam bushing are operably arranged within the through-hole to connect the metal component and the ceramic matrix composite component. | 09-19-2013 |
20130251532 | SECURING DEVICE FOR AXIALLY SECURING A BLADE ROOT OF A TURBOMACHINE BLADE - A securing device ( | 09-26-2013 |
20130272886 | SYSTEM AND METHOD FOR COVERING A BLADE MOUNTING REGION OF TURBINE BLADES - A system includes a cover segment set configured to mount in first and second grooves circumferentially along a blade mounting region of a turbine rotor. The cover segment set includes a seal segment and a cover segment. The seal segment has a seal body with a lock feature, wherein the seal segment is configured to mount circumferentially along the second groove. The cover segment includes first and second lips extending along first and second circumferential portions of a cover body. The first and second lips are at an offset from one another. The first lip is configured to mount circumferentially along the first groove, the second lip is configured to mount circumferentially along the second groove adjacent the seal segment, and the second lip includes a mating lock feature configured to couple with the lock feature of the seal body. | 10-17-2013 |
20130302171 | DEVICE FOR ATTACHING BLADES TO A TURBINE ENGINE ROTOR DISK - The invention provides a device for attaching blades to a rotor disk of a turbine engine, comprising: a rotor disk provided at its outer periphery with a plurality of slots, each formed between two adjacent disk teeth and extending axially between front and rear faces of the disk; a plurality of blades, each having a respective root mounted in a slot of the disk; and at least one pin mounted in the rotor disk to pass through the roots of at least two adjacent blades and extending between the front and rear faces of the rotor disk so as to attach the blades to the rotor disk. | 11-14-2013 |
20130315744 | FAN ROTOR AND ASSOCIATED TURBOJET ENGINE - A fan rotor including a disk carrying blades including roots engaged in slots in the disk, a frustoconical cap mounted on the disk upstream from the blades, and a retaining mechanism axially retaining the blades on the disk and including a ring mounted in an annular groove of the disk and forming an abutment for the roots of the blades, the ring being festooned or crenellated and co-operating with a festooned radial annular bead of the annular groove of the disk, and a mechanism preventing the ring from moving in rotation, which includes an annulus carrying at least one axial tooth inserted in hollow portions of the bead of the disk and of the ring, the annulus being fastened by bolts on an upstream radial face of the disk. | 11-28-2013 |
20130330198 | Turbine Rotor and Blade Assembly with Blind Holes - The present application provides a turbine rotor and blade assembly for a steam turbine. The turbine rotor and blade assembly may include a rotor, a number of buckets positioned about the rotor, a locking blade positioned about the rotor, and a blind hole positioned about the rotor adjacent to the locking blade. | 12-12-2013 |
20130343896 | CATCHER RING ARRANGEMENT - This invention relates to a blade assembly comprising: a hub which is rotatable about an axis; at least one blade having an aerofoil portion and a root, wherein the root is coupled to the hub using a primary retention device which prevents radial separation of the root and hub in normal use; and, a secondary retention device which comprises an annular catcher having a restriction through which the root portion cannot radially pass, the restriction being located radially outwardly and radially spaced from the root part during use. | 12-26-2013 |
20140044550 | Restraint Mechanism for Rotor Blades of a Turbo Engine, an Assembly Method and a Turbo Engine - A restraint mechanism for rotor blades of a turbo engine on a rotor disk having blade root receptacles for radial guidance of the rotor blades is disclosed. The restraint mechanism has a plurality of axial securing elements, each having at least one web for positioning in a blade root receptacle, such that each web has a retaining section at one end for establishing a form-fitting design to a mating brace of another axial securing element. A method for axially securing rotor blades on a rotor disk and a turbo engine are also disclosed. | 02-13-2014 |
20140064977 | TURBINE ROTOR BLADE ROOT ATTACHMENTS - A pinned root fixing arrangement of axial flow steam turbine rotor discs made of a low alloy that is less susceptible to stress corrosion cracking (SCC). Such an arrangement has a first ratio, which is defined as ratio of the axial breadth of the disc fingers and the sum of the axial breath and the axial breadth G of the gap between adjacent disc fingers, in the range of about 0.4 to about 0.6 and further has a second ratio, which is defined as the ratio of the length of the disc fingers and the blade fingers to the diameter, between 4 and 6. | 03-06-2014 |
20140072437 | TURBOMACHINE ROTOR WITH A MEANS FOR AXIAL RETENTION OF THE BLADES - A rotor of a turbomachine, such as a multi-flow turbojet engine fan, has a disc including, on the rim thereof, substantially axial slots with a dovetailed cross-section, and blades mounted individually in the slots, an axial wedge positioned between the root of the blades and the bottom of the slots, and a transverse lock providing upstream axial immobilization of the blades in the slot thereof. The lock is guided in radial notches formed in the flanks of the slots and radially supported against the wedge. The axial wedge is immobilised in the upstream direction, butting up against a transverse annular component secured to the disc. | 03-13-2014 |
20140127026 | LOCKING BLADE FOR A ROTOR - A locking blade for a rotor can include an airfoil portion with a root from which a tongue extends. Opposed bucket segments can engage the tongue and can be retained in a longitudinal direction of the blade by a fastener, such as a pin, that can extend through holes in the segments and tongue. Tines parallel to and on opposite sides of the tongue can extend from the root and include holes through which the fastener can extend, the bucket segments extending between respective tines and the tongue. The structure can eliminate an assembly gate in a rotor. | 05-08-2014 |
20140127027 | TURBINE ROTOR FOR A THERMAL ELECTRIC POWER STATION - The technical field of the invention is that of turbine rotors for a thermal electric power station and the subject of the invention is, more particularly, a rotor of a turbine for a thermal electric power station, said rotor comprising a plurality of blades, each comprising at least one root and a vane; and at least one rotor disk secured to a shaft able to be in rotation about a reference axis, the rotor disk comprising on its periphery outgrowths in which to fit the blades, so that the vanes of the blades are arranged radially with respect to the reference axis; said rotor being one wherein: the rotor disk comprises a groove opening axially and having a lower face and an upper face, the lower face of the groove of the rotor disk being situated on the periphery of said rotor disk and the upper face of the groove of the rotor disk being situated on the outgrowths and facing the lower face; each of the blades comprises, at its root, a lateral projection directed axially, said lateral projection having, in its lower part, a groove portion having an upper face situated in the continuation of the upper face of the groove of the rotor disk; at least one locking means for locking the blades is positioned in the groove of the rotor disk. | 05-08-2014 |
20140133991 | GAS TURBINE ENGINE FAN BLADE LOCK ASSEMBLY - A gas turbine engine fan blade lock assembly includes a fan hub that has blade slots each configured to receive a root of a fan blade. The fan hub includes circumferentially spaced first slots. A lock ring is configured to move between unlocked and locked positions. The lock ring includes circumferentially spaced second slots aligned with the first slots in the locked position, and multiple discrete pins. Each pin is configured to be slidably received in paired first and second slots in the locked position to prevent rotational movement of the lock ring relative the fan hub. | 05-15-2014 |
20140133992 | CONNECTION MECHANISM FOR MOUNTING BLADES FOR A WIND TURBINE - A variety of wind turbine assemblies are described herein. The wind turbine assemblies each include a plurality of blades that have a sidable connection member to secure the wind blades to a shaft member. In some configurations, recesses are provided on the shaft to secure the blades. Other configurations include separate mounting members that secure around the shaft to operatively connect the blades to the shaft. | 05-15-2014 |
20140205460 | METHOD AND SYSTEM FOR SELF-LOCKING A CLOSURE BUCKET IN A ROTARY MACHINE - A system includes a turbomachine that includes at least one rotor disk or stage having a peripheral portion disposed about a rotational axis of the rotor disk or stage. The peripheral portion includes a groove that extends circumferentially about the peripheral portion. The groove has a first groove surface and a second surface disposed opposite the first groove surface. The turbomachine also includes a closure bucket disposed adjacent at least one bucket within the groove. The closure bucket has a first surface that interfaces with the first groove surface and a second groove surface disposed opposite the first surface. The closure bucket blocks circumferential movement of the at least one bucket within the groove relative to the rotor disk or stage. The turbomachine further includes a single wedge disposed between and contacting the second surface of the closure bucket and the second groove surface to secure the closure bucket within the groove. | 07-24-2014 |
20140219807 | UNDER-ROOT SPACER FOR GAS TURBINE ENGINE FAN BLADE - A gas turbine engine rotor includes a hub having a slot. A blade includes a root received in the slot. An under-root area is provided between the root and the fan hub in the slot. A spacer includes first and second portions that cooperate with one another to provide an adjustment feature with discrete height settings. The adjustment feature provides different radial heights of the spacer. The spacer is arranged in the under-root area beneath the root. | 08-07-2014 |
20140234111 | BLADE ARRANGEMENT - A blade arrangement is provided having a blade carrier and a retaining groove arranged therein, which retaining groove has projections extending along side walls thereof forming undercuts and into which a number of blades are inserted forming a blade ring of a turbomachine. Each blade has a blade root which engages into the undercuts, and each blade is pressed against the projections by an element arranged between a blade root underside and a groove base of the retaining groove. It is further provided that each element is of plate-like form and has, in the projection of the blade airfoil in the direction of the groove base, at least one bead, arranged beneath the blade airfoil, for imparting a pressing action, and in the longitudinal direction of the retaining groove, only part of the blade root which the element presses against is covered. | 08-21-2014 |
20140241893 | SYSTEM FOR SPECIFYING AN INSTALLATION POSITION OF ROTOR BLADES, SECURING ELEMENT, ROTOR BLADE, TURBOMACHINE, AND METHOD - A system for specifying an installation position of adjacent rotor blades of a blade row of a turbomachine is disclosed. The system has a plurality of axial securing elements, which have at least two sections with different profile areas for the arrangement in each case between a groove base of a rotor shaft and a blade root, which are joined together by a connecting web at a groove distance from one another, and which have counter-contours on the blade root side for forming in each case a positive-fit pair with the profile areas. Also disclosed are a securing element and a rotor blade for this type of system, a turbomachine having a rotor which has this type of system, and a method for manufacturing this type of rotor. | 08-28-2014 |
20140286782 | TURBINE BLADE STAKING PIN - A staking pin for a gas turbine engine is disclosed. The staking pin may include a solid portion extending part of a length of the staking pin, and a hollow portion extending an additional part of the length of the staking pin. The staking pin may be constructed of Alloy X material having an average grain diameter of between about 0.0449 and 0.1270 mm. | 09-25-2014 |
20140314576 | WIND TURBINE BLADE HOLDING ARRANGEMENT - A wind turbine blade holding arrangement is described comprising a root frame for securing to a root portion of a blade; an airfoil clamp for arranging about an airfoil portion of the blade; and an airfoil frame for supporting the airfoil clamp wherein the root frame and tip clamp are realized for use in a first blade orientation in a first storage and transport stage of the blade and also for use in a second blade orientation in a second storage and transport stage of the blade, wherein the first and second blade orientations are essentially at right angles to each other. A method of handling a number of wind turbine blades is also described. | 10-23-2014 |
20140314577 | PROPELLOR BLADE RETENTION - A propeller blade retention arrangement having a propeller blade comprising in radial sequence an aerofoil portion, a shank portion and a root portion. The root portion having first cross-sectional area close to the shank portion and second cross-sectional area at the end distal to the aerofoil portion, wherein the second cross-sectional area is greater than the first cross-sectional area. At least two cheeks each having an inner surface arranged to abut the root portion, an outer surface that is threaded and edge surfaces that abut another of the at least two cheeks; wherein the at least two cheeks are arranged to surround the root portion in circumferential abutment. A collar having a threaded inner surface arranged to threadingly engage the outer surfaces of the at least two cheeks. | 10-23-2014 |
20140314578 | SECURING SEGMENT FOR THE VIBRATION DAMPING OF TURBINE BLADES AND ROTOR DEVICE - A retaining segment for axially securing at least one rotor blade on a disk wheel of a rotor device of a jet engine is operatively connectable to at least one rotor blade and to a disk wheel. In a first peripheral area of the retaining segment that is laterally disposed in the circumferential direction in the installed state, a projecting region is provided, and in a second lateral peripheral area facing away from the first peripheral area, a receiving region is provided. The projecting region at least partially overlaps a receiving region of a retaining segment that is identical in design and arranged adjacently in the circumferential direction, and for performing frictional work with the receiving region. A rotor device has rotor blades arranged via blade roots substantially in the axial direction inside recesses of a disk wheel and secured by several such retaining segments. | 10-23-2014 |
20140356177 | TURBINE SEGMENTED COVER PLATE RETENTION METHOD - An improved gas turbine cover plate assembly is disclosed for use in connection with segmented cover plates in turbine configurations where it is not possible to stagger the blades to create assembly clearance. The improved turbine assembly also avoids cover plate loading slots in the disc which can cause high stress features. The improved system also includes a method to axially retain segmented cover plates in relation to a turbine disc using a segmented retainer ring. | 12-04-2014 |
20140356178 | BLADE OF A TURBINE - The present invention relates to a blade of turbine having an aerofoil, a platform and a root portion configured to be slidingly received in mounting slots of a rotor disc. The blade further includes a locking member disposed on the root portion and engaged with the rotor disc to make axial fixation of the blade to the rotor disc. With the technical solution of the present invention, it provides a blade with simple and cost effective axial locking system to make axial fixation of the blade relative to the rotor disc, and also a fail-safe solution during assembly process. | 12-04-2014 |
20140377074 | FAN BLADE AND ATTACHING MEANS THEREFOR - In order to disclose attaching means ( | 12-25-2014 |
20150010404 | TURBINE OR COMPRESSOR STAGE INCLUDING AN INTERFACE PART MADE OF CERAMIC MATERIAL - A turbine or compressor stage suitable for being included in airplane turbojets. According to the invention, the stage comprises a disk ( | 01-08-2015 |
20150023796 | EXPANDING LOCK PIN FOR TURBINE SIDE ENTRY BLADE - An expanding lock pin for side entry turbine blades for turbines, including steam turbines compensates for worn or oversize mating pin grooves formed in rotor steeples and blade roots. The expanding pin expands circumferentially to fill the oversize mating groove. In one embodiment of the expanding lock pin a tapered plug mates with a mating tapered aperture formed in the pin. As the plug is driven into the pin its circumference increases. The expanding lock pin eliminates the need to re-machine worn or oversize pin grooves or machine new grooves. | 01-22-2015 |
20150030456 | IMPELLER FOR A ROTOR OF A TURBOMACHINE, AND ROTOR AND TURBOMACHINE HAVING AN IMPELLER OF SAID TYPE - An impeller for a rotor of a turbomachine includes: a wheel disc mounted on the rotor, the wheel disc having plural grooves arranged along a circumference of the wheel disc and extending in the thickness direction of the wheel disc. A toothed profile is formed on two sides of each groove. A plurality of impeller blades each have one root with two sides on each of which one toothed profile is formed. Each blade is inserted into a groove so as to form a blade-groove combination with the toothed profiles of the root and of the groove in engagement. Each combination having a fixing device that fixes the blade in the groove in the thickness direction and in the radial direction of the wheel disc. Each fixing device has a recess movably received in the groove base. | 01-29-2015 |
20150037162 | MECHANICAL JOINING USING ADDITIVE MANUFACTURING PROCESS - A method of manufacturing an assembly ( | 02-05-2015 |
20150044054 | COMPOSITE RETENTION FEATURE - A retention feature for use in a gas turbine engine is disclosed herein. The retention feature includes a ceramic post, an insert, and a braze layer coupling the insert to the ceramic post. The ceramic post includes a body adapted to be coupled to a turbine engine component and a head coupled to the body. The insert is arranged in a space formed in the head and the braze layer extends from the ceramic post to the insert to bond the insert to the ceramic post. | 02-12-2015 |
20150071785 | TURBINE BLADE AND NON-INTEGRAL PLATFORM WITH PIN ATTACHMENT - Platforms ( | 03-12-2015 |
20150078907 | TURBOMACHINE INCLUDING A NON-DESTRUCTIVE FASTENER ELEMENT FOR JOINING COMPONENTS - A turbomachine includes a first component including a first surface and a second surface spaced from the first surface by a gap. One of the first and second surfaces includes a non-destructive fastener element receiving opening and a wire retention feature. A second component extends into the gap between the first and second surfaces. A non-destructive fastener element is detachably mounted to the first component. The non-destructive fastener element includes a post member and a wire member operatively connected to the post member. The post member extends into the non-destructive fastener element receiving opening preventing removal of the second component and the wire member engages with the wire retention feature to secure the non-destructive fastener element to the first component. | 03-19-2015 |
20150086374 | PROPELLER ASSEMBLY AND PROPELLER BLADE RETENTION ASSEMBLY - A propeller assembly having a hub having at least one receiver opening, a receiver located within the receiver opening and having a first collar defining a blade opening, a blade having a second collar and a protrusion with the second collar abutting the first collar and the protrusion received within the blade opening, and a first retainer, and a second retainer. | 03-26-2015 |
20150086375 | CEILING FAN - A ceiling fan includes blade ( | 03-26-2015 |
20150093248 | RETAINER PLATE - A retainer plate is provided for retaining a dovetail root of a fan blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a fan disc. In use, the plate locates in a cavity formed at an end of the slot such that a first side of the plate is arranged for contact with an axial end face of the dovetail root and an opposite second side of the plate is arranged for contact with an abutment surface of the cavity to limit axial movement of the root along the slot. The retainer plate is a unitary component and has a layered structure including a first layer at the first side of the plate, a second layer at the second side of the plate, and an intermediate layer between the first and the second layers. | 04-02-2015 |
20150104320 | TURBINE WITH BUCKET FIXING MEANS - There is provided a turbine including a rotor wheel including a plurality of dovetail grooves and at least one insertion groove, the dovetail grooves and the insertion groove arranged in a circumferential direction of the rotor wheel; a plurality of first buckets, each of the first buckets including a vane, a platform provided at a first end portion of the vane, and a dovetail provided at the platform and having a shape corresponding to a corresponding dovetail groove; at least one second bucket including a vane, a platform provided at a first end portion of the vane, and at least one protrusion portion provided at the platform and configured to be inserted into a corresponding insertion groove of the insertion groove; and a fixing member configured to be inserted through the protrusion portion and the rotor wheel and configured to restrict radial movement of the second bucket. | 04-16-2015 |
20150110634 | RETAINER PLATE - A retainer plate is provided for retaining a dovetail root of a fan blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a fan disc. In use, the plate locates in a cavity formed at an end of the slot such that a first side of the plate is arranged for contact with an axial end face of the dovetail root and an opposite second side of the plate is arranged for contact with an abutment surface of the cavity to limit axial movement of the root along the slot. The retainer plate is formed from fibre-reinforced composite material, at least a portion of the composite material being reinforced by 3D-woven fibre tows. | 04-23-2015 |
20150118056 | ROTOR TURNING SYSTEM AND METHOD - A rotor turning system includes a fixture plate configured for attachment to a gearbox, a locking mechanism configured for attachment to the fixture plate, and a reaction fixture configured for attachment to the locking mechanism. The rotor turning system is configured to permit rotation of the rotor only when rotational torque is applied to the locking mechanism, and this rotation is in only one rotational direction. | 04-30-2015 |
20150361813 | ROTOR ASSEMBLY FOR GAS TURBINE - The present invention relates to a rotor assembly for a rotary machine such as a gas turbine. The present solution provides a sealing wire located inside a groove engraved in the rotor body. The sealing wire is responsive to radial centrifugal forces acting during normal operation of the machine, and moves radially in the groove until a sealing configuration is achieved such to prevent damaging hot leakage towards machine components. | 12-17-2015 |
20150369057 | DAMPER MASS DISTRIBUTION TO PREVENT DAMPER ROTATION - A damper seal for a gas turbine engine rotor assembly has an axially elongated body with a leading edge, a trailing edge, a pressure side, and a suction side. The elongated body includes a first enlarged portion formed on the pressure side at the leading edge and a second enlarged portion formed on the suction side adjacent the trailing edge. | 12-24-2015 |
20150369063 | BLADE WHEEL AND METHOD FOR PRODUCING A BLADE THEREFOR - A turbine blade wheel includes a wheel disk with a disk element ( | 12-24-2015 |
20160040542 | COVER PLATE FOR A ROTOR ASSEMBLY OF A GAS TURBINE ENGINE - A cover plate according to an exemplary aspect of the present disclosure includes, among other things, a body, a first tab near a bore of the body, and a second tab circumferentially spaced from the first tab. A slot is defined between the first tab and the second tab, the first tab, the second tab and the slot extending at an angle relative to a slot axis that extends through the bore. In another embodiment, the cover plate includes a bumper that limits deflection of the body. | 02-11-2016 |
20160090854 | BLADED ROTOR ARRANGEMENT - A bladed rotor arrangement comprising a rotor, a plurality of rotor blades, at least one seal plate and a plurality of lock plates. Each rotor blade locates in a corresponding axially extending slot in the rotor. A plurality of lock plates are arranged at a first axial end of the rotor, the radially outer ends of the lock plates engage grooves on the platforms of the rotor blades, and the radially inner ends of the lock plates engage a circumferentially extending groove. The seal plate is arranged at the first axial end of the rotor, the radially inner ends of the lock plates engage the circumferentially extending groove defined by the seal plate. The seal plate has at least one projection extending axially from the seal plate and arranged to locate in a slot in a first axial end of the root of a rotor blade. | 03-31-2016 |
20160097287 | FAN - Fan for gas turbine engine includes hub and annular array of fan blades mounted to hub and extending radially outwardly from hub, each fan blade includes blade root. The hub includes plurality of hub grooves having shape complimentary to shape of blade root and each hub groove receives and radially retains one blade root. A slot is provided on the suction side and on the pressure side of each blade root. Plurality of keys is provided, each key engages with slots in one blade root and with corresponding hub groove so as to axially retain fan blade. The key includes two arms and joining member, two arms are received in slots provided on blade root and joining member extends between the arms. Interface is defined between key arms and slots in blade root, and greater or equal percentage of interface is curved than is planar. | 04-07-2016 |
20160097289 | SLIDER - A slider for chocking a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc. The slider, in use, is slidingly inserted in an axially-extending cavity formed in the base of the root and in the disc at the base of the slot to urge the blade radially outwardly and thereby mate flanks of the root to flanks of the slot. The slider is arc-shaped and the cavity is correspondingly arc-shaped. The normal to the plane of the arc of the arc-shaped cavity is substantially perpendicular to the engine axis such that, when inserted in the cavity, the slider also retains the root axially in the slot. | 04-07-2016 |
20160138406 | COMPOSITE COMPONENTS FOR GAS TURBINE ENGINES - A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed as a composite structure including a number of plies of ceramic-containing material. The blades each include a root to fit within dovetail slots of the rotor disk to couple the blades to the rotor disk. | 05-19-2016 |
20160177748 | TURBINE WHEEL WITH COMPOSITE BLADED RING | 06-23-2016 |
20160177750 | ARRANGEMENT OF A ROTOR AND AT LEAST A BLADE | 06-23-2016 |
20160186573 | Radial Lock for Fan Blade Sheath - A turbojet fan blade adapted for securement to an engine rotor includes a titanium sheath that extends continuously over its leading edge from blade tip to blade root. The sheath provides impact protection over the leading edge of the blade, and also incorporates enhanced radial securement of the sheath to the rotor. As such, a radial lock system for the sheath is disclosed that includes a fully integrated sheath portion that extends completely over the frontal face of a fan blade dovetail, providing a radial lock of the sheath to the rotor in the event of failure of any adhesive used to attach the sheath to the leading edge. Because the sheath extends continuously from blade tip to the blade root, lightning strike protection is enhanced by avoidance of any discontinuities otherwise associated with related art sheaths that typically extend over only a flow path portion of the leading edge. | 06-30-2016 |
20160201483 | TURBINE WHEEL WITH CLAMPED BLADE ATTACHMENT | 07-14-2016 |
20160201484 | TURBINE WHEEL WITH CLAMPED BLADE ATTACHMENT | 07-14-2016 |
20160252103 | FAN ROTOR WITH INTEGRATED PLATFORM ATTACHMENT | 09-01-2016 |
20180023394 | ROTOR WITH A LOCKING PLATE FOR SECURING AN ANTIROTATION LOCK AGAINST UNSCREWING | 01-25-2018 |
20180023401 | WHEEL DISK ASSEMBLY HAVING SIMPLIFIED SEALING-PLATE MOUNTING | 01-25-2018 |
20120087797 | ROTOR BLADE WITH CONTROL TUBE - A system comprising a rotor blade ( | 04-12-2012 |
20120134835 | CONNECTION MEANS - A connection means ( | 05-31-2012 |
20130164139 | FAN WITH REPLACABLE VANES - A fan includes a frame, a rotor rotatably mounted in the frame, and a vane. The rotor includes a slot defined in the circumference of the rotor. The slot extends through an end surface of the rotor. The vane forms an installing portion to be inserted into the slot through the end surface. A first base and a second base are formed on the end surface at opposite sides of the slot. A blocking member is pivotably mounted to the first base with a first end, and is detachably engaged with the second base with a second end, to fix the installing portion in the slot. | 06-27-2013 |
20190145424 | FAN WITH ENGAGEMENT STRUCTURE | 05-16-2019 |
Entries |
Document | Title | Date |
20080199320 | Detachable leading edge for airfoils - A replaceable leading edge insert for an: integrally bladed rotor disk in which the insert includes an enlarged base portion that can be inserted into a dovetail shaped slot formed in the rotor disk to secure the insert to the rotor disk against centrifugal loads during the operation of the blade. The blade on the rotor disk is formed without a leading edge and the leading edge insert includes an aft edge of similar shape to the fore edge n the blade such that the insert can be bonded or fastened to the blade along the entire length of the insert from the blade root to the tip. The rotor disk and the insert include a an annular groove formed on the front side in which a retaining ring is inserted to lock the inserts to the rotor disk. The inserts can be made of a different material from the rotor disk and can be formed with a sweep to form a more :aerodynamic and efficient blade. | 08-21-2008 |
20080226458 | TURBOMACHINE FAN - A turbomachine fan ( | 09-18-2008 |
20080253895 | BLADE RETENTION SYSTEM FOR USE IN A GAS TURBINE ENGINE - The blade retention system comprises an annular sealing plate and a plurality of spaced-apart blade retention tabs having opposite first and second ends and a radially-orientated corrugated profile. The first ends of the tabs are connected to a first side face of the annular sealing plate. Each tab is configured and disposed to be inserted through a bottom portion of a respective one of the blade retention slots when the first side face of the sealing plate is positioned against one of the side faces of the rotor disc and covers an end side of the blade retention slots. The second end of each tab extends beyond the other of the side faces of the rotor disc and is bent to secure the annular sealing plate with reference to the rotor disc. | 10-16-2008 |
20080267781 | Turbo-Engine and Rotor for a Turbo-Engine - The invention relates to a rotor for a non-positive-displacement machine, particularly a rotor for a compressor of a gas turbine, on which at least one shaft collar with an outer periphery and with two radially extending faces are placed. The rotor also comprises a multitude of retaining grooves for moving blades, said retaining grooves being provided on the outer periphery and extending transversal to the peripheral direction and each retaining groove has a groove bottom. In order to provide a rotor for a non-positive-displacement machine that makes it possible to reduce flow losses while having a simple geometrical design of the attachment of moving blades, the invention provides that an annual groove, which extends in an axial direction and which is coaxial to the rotation axis of the rotor, is provided at least on one face of the shaft collar. This annular groove is joined to the groove bottom of the retaining grooves whereby enabling material of the foot of the moving blade to be plastically forced into the annular groove. | 10-30-2008 |
20080273982 | BLADE ATTACHMENT RETENTION DEVICE - A component for a gas turbine engine includes a rotor disk, a plurality of blade attachments, a plurality of retention flanges, and a plurality of retention tabs. The rotor disk has a plurality of slots formed in an outer surface thereof. Each blade attachment has an attachment region configured to be partially disposed within one of the slots. The plurality of retention flanges extend from the rotor disk outer surface, to thereby at least inhibit axial movement of the blade attachment, when the attachment region is fitted inside its corresponding slot. A retention tab extends from each attachment region and engages one of the retention flanges. | 11-06-2008 |
20090022592 | Clamped plate seal - A seal for a dovetail joint in a turbomachine is provided. The seal includes an arcuate member having a first end, a middle portion and a second end. The seal also includes sealing means, which include at least one sealing member. The sealing member can comprise a first sealing member connected to the first end and/or a second sealing member connected to the second end. The dovetail joint is the interface between a bucket dovetail and a rotor dovetail groove, and the seal reduces the amount of cooling flow leakage from the dovetail joint. | 01-22-2009 |
20090022593 | FAN BLADE RETAINING STRUCTURE | 01-22-2009 |
20090028712 | TURBOMACHINE HAVING AXIAL ROTOR BLADE SECURING - A rotor of a turbine machine having several rotor blade rings positioned in succession in the axial direction, is disclosed. Each rotor blade ring has a rotor base body with several rotor blades anchored by blade footings in axial grooves of the rotor base body that extend essentially in the axial direction and, in their anchored position in the rotor base body, are secured against displacement in the axial direction. The rotor blades of at least one rotor blade ring have hook-like securing elements, which, in the anchored position on a low-pressure side of the rotor blade ring, abut the rotor base body. The hook-like securing elements, between the rotor base body and a sealing element, which extends between the rotor base body and a rotor base body of a rotor blade ring that connects on the low-pressure side, are fixed in the axial direction on both sides. | 01-29-2009 |
20090035144 | QUICK ASSEMBLY BLADE FOR A CEILING FAN (3) - A quick assembly blade for a ceiling fan includes a blade frame, a blade and a press board. The blade frame is fixed with three studs and an engage position-limiting unit located among the three studs, with the engage pin able to be shifted up and down at the top end of the position-limiting unit. The blade is bored with a through hole at a location matching with the position-limiting unit of the blade frame. The press board is pressed and fixed on the blade, provided with a position-limiting portion. When the press board is pushed to move horizontally to the rear end of the blade, the engage pin will automatically be inserted in the position-limiting portion to keep the press board in position and prevent it from disengaging from the blade, able to quickly assemble the blade on the blade frame. | 02-05-2009 |
20090053065 | FAN BLADE RETAINING STRUCTURE | 02-26-2009 |
20090092497 | Securing element for fastening moving blades - A securing element for securing the position of moving blades in slots, running at least mainly in the axial direction, of a rotor parent body of a turbomachine rotor is described, comprising a plate-shaped parent body, wherein the parent body has an approximately central recess which is formed between two end sections of the parent body and defines a center section, running between the two end sections, of the parent body, wherein the two end sections have bearing surfaces running parallel to one another. | 04-09-2009 |
20090116965 | Arrangement for axially securing rotating blades in a rotor, sealing element for such an arangement, and use of such an arrangement - An arrangement is presented for axially securing rotating blades in a rotor, having a shaft collar on whose external circumference rotating blade securing grooves which extend in the axial direction of the rotor are provided. At one end side face of the shaft a projection is arranged in the region of the securing grooves, in which projection a circumferential groove which is open radially towards the outside is provided and said projection having securing grooves which are arranged in each rotating bade, sheet-metal-shaped sealing elements which each engage in the circumferential groove and in the securing groove and form an end side sealing ring in the circumferential direction being provided for axially securing the rotating blades, and at least one of the sealing elements comprising a sheet metal strip which is attached to said sealing ring in order to secure the sealing elements against displacement in the circumferential direction. | 05-07-2009 |
20090175729 | Fan rotor assembly - A fan rotor assembly has an inner rotor, an outer rotor, a central retainer and a central shaft. The inner rotor has multiple first blades. The outer rotor is stacked on the inner rotor and has multiple second blades. The central retainer is mounted through the inner and outer retainers. The central shaft is mounted in the central retainer under the inner rotor. The fan rotor assembly with first and second blades provides excellent airflow. | 07-09-2009 |
20090185909 | Self-assembly micro blade - The present invention relates to a self-assembly micro blade applied to a micro fan. The micro fan combines at least a self-assembly micro blade and a motor using an actuator as the main body of the micro fan. The self-assembly micro blade includes at least a movable part of a microstructure, at least an elastic joint provided between an outer ring of the micro fan and the movable part. The elastic joint is composed of a polyimide film, which is heated to contract and generate surface tension by using a reflow process so as to lift up the movable part of the microstructure; moreover, the movable part is bent in a curved form through the elastic link exhibits a multi-layer shape by serially connecting at least two movable parts so as to complete the self assembly of the micro blade, thereby increasing air flow rate and improving air flow length. | 07-23-2009 |
20090220345 | Closing Assembly for a Blade Ring of Turbomachinery - The invention relates to a closing assembly for closing the gap remaining between the first and last blade of a blade ring that is inserted into a peripheral groove of turbomachinery. Said assembly comprises at least two parts each of which can be hooked onto projections that form an undercut in said peripheral groove and comprises a securing element, which secures the parts from becoming detached from the peripheral groove. To provide a closing assembly for closing the remaining gap, which can be simply and cost-effectively detached and which reliably withstands high mechanical stress, the securing element is mounted to rotate about its longitudinal axis between the two parts and has a key head and a web. The web of the securing element can be positioned by rotation is such a way that to fit the parts in the peripheral groove, said parts can be displaced in relation to one another and to secure the parts from being detached from said groove, the web of the securing element can be placed against at least one lateral face of one of the parts. | 09-03-2009 |
20090226321 | LOCKING OF THE BLADES IN A FAN ROTOR - A fan rotor is provided. Each blade of the fan rotor is held by a bolt. Each blade includes a blade root engaged in a groove of the rim and held by a bolt. The bolt includes a concave plate with its curve directed upstream. | 09-10-2009 |
20090252610 | Turbine blade retention system and method - A retention system retains a turbine blade dovetail in a retention ring dovetail slot. The retention system includes a retention opening formed in the blade dovetail. A through hole is formed in the retention ring, wherein the through hole is positioned such that it is aligned with the retention opening when the dovetail is assembled in the dovetail slot. A connector is disposed in the through hole and engages the retention opening. In this manner, undesirable relative movement of parts can be reduced or eliminated, thereby preventing excessive wear. | 10-08-2009 |
20090252611 | Axial compressor blade retention - An axial retention system for restraining axial movement of a machine component having a dovetail within a complimentary-shaped dovetail slot includes: a first substantially T-shaped groove formed in a bottom surface of the dovetail slot; a second substantially T-shaped groove formed in a bottom surface of the dovetail, the first and second grooves in alignment when the dovetail is located within the dovetail slot to thereby form a closed periphery substantially T-shaped slot having a stem portion and a lateral cross portion at one end of the stem component, wherein the other end of the stem is open; and a compressible locking clip adapted for insertion within the substantially T-shaped slot, the locking clip having a pair of oppositely extending lugs receivable in opposite ends of the lateral cross portion. | 10-08-2009 |
20090269202 | FAN ROTOR FOR A TURBOMACHINE OR A TEST ENGINE - A fan rotor, in particular for a turbomachine, the rotor comprising a disk carrying blades having roots engaged in substantially axial grooves in the outer periphery of the disk, a substantially frustoconical annular spinner mounted on the disk upstream from the blades, and axial retention means for retaining the blades on the disk in the upstream direction, which retention means are formed integrally with the spinner. | 10-29-2009 |
20090324414 | BLADE FASTENING MEANS OF A TURBINE - A turbine-blade locking device having a wedge movable in an axial direction is disclosed. The wedge is movable in the axial direction by a tensioning device, as a result of which a force is produced in the axial direction. The force in the axial direction causes the turbine blade to be pressed against the blade holder. | 12-31-2009 |
20100008783 | Gas Assisted Turbine Seal - A dovetail seal assembly for sealing a gap between a bucket dovetail and a rotor. The dovetail seal assembly may include a sealing slot positioned about the dovetail, a high-pressure supply hole in communication with the sealing slot, and a deformable seal positioned about the sealing slot and into the gap. | 01-14-2010 |
20100014978 | Turbine rotor with locking plates and corresponding assembly method - A turbine rotor with a rotor disc, a plurality of slots arranged on the rotor disc, a plurality of blades having blade roots and arranged in the slots, and a plurality of locking plates fitted in a position between the rotor disc and the blades are provided. The first gaps on radially outside edges and second gaps on radially inside edges, relative to an axis of rotation of the rotor disc, are formed between neighboring locking plates. At least one of the first gaps is smaller than the corresponding second gap, wherein at least one first gap and corresponding second gaps are intentionally introduced. | 01-21-2010 |
20100047073 | TURBINE BLADE ASSEMBLY - A turbine blade assembly, in particular of a gas turbine, is provided. The turbine blade assembly includes a turbine disc with rotor blades inserted into notches of the turbine disc and locking plates that are placed inside circular grooves with rims in the turbine disc and in the rotor blade. The edges of the locking plates that are oriented towards the center of the turbine disc are castellated by providing teeth and accordingly a part of the rim of the circular groove of the turbine disc is also castellated by providing gaps and whereby the gaps of the rim match the teeth of the locking plates. The locking plates have a spring-back force to provide both locking and sealing capabilities during engine operation. | 02-25-2010 |
20100086409 | WIND TURBINE ROTOR - A wind turbine rotor comprising a hub and a plurality of blades. The hub comprises a plurality of sites, each having a pair of spaced apart annular bearings for receiving a respective wind turbine blade. Each blade has a spar extending along a substantial portion of the length of the blade and protrudes from the proximal end of the blade. The spar protrudes into and is rotatably received within the respective spaced apart bearings and is fixed to the hub. | 04-08-2010 |
20100150726 | ARTICLE AND ULTRASONIC INSPECTION METHOD AND SYSTEM THEREFOR - A method, system and article adapted for ultrasonic inspection of the article. The article is disk-shaped and has axially-oriented slots circumferentially spaced from each other at a periphery of the article, with members secured at the periphery of the article such that each member has a retention feature that extends into and engages a corresponding one of the slots so as to secure the members to the slots. Cavities are defined by and between the slots and radially-inward extremities of the retention features within the slots. The inspection method and system entail the use of at least one ultrasonic transducer placed within at least a first of the cavities defined by a first of the slots. The transducer is configured and oriented to perform a diagnostic technique on the article by emitting an ultrasonic signal that intersects an interior surface of a second of the slots immediately adjacent the first slot. | 06-17-2010 |
20100183444 | FAN BLADE PRELOADING ARRANGEMENT AND METHOD - The fan blade includes a blade root at one end thereof configured for sliding insertion into a substantially axially extending slot defined in a periphery of a fan rotor hub. The blade comprises a first passageway extending at least partially through the blade root, in a direction generally parallel to an axial direction of the slot. It also comprises a second passageway extending at least partially through the blade root to intersect with the first passageway. A first member is provided in the first passageway, the first member configured to be retained in the first passageway once inserted therein, and a second member is provided in the second passageway, the second member having one end in cooperating engagement with the end of the first member. The second member has a portion projecting out of the bottom face of the blade root a distance sufficient to contact an inner surface of the slot and thereby force the blade outwardly in the slot. | 07-22-2010 |
20100196164 | Turbine Coverplate Systems - In one embodiment, a coverplate may be configured to axially overlay a plurality of blade retaining slots within a wheel post of a rotor wheel. The coverplate may include a tab for radially securing the coverplate within a complementary groove of the rotor wheel and an aperture configured to align with a corresponding aperture of the turbine wheel to receive a fastener for axially securing the coverplate to the rotor wheel. | 08-05-2010 |
20100221115 | RETENTION STRUCTURES AND EXIT GUIDE VANE ASSEMBLIES - A retention structure includes a center body including an outer surface, an enclosed end, an open end, and a contact section, the outer surface adapted to define a first portion of a flowpath, and the contact section extending radially outwardly from a centerline and located on the enclosed end and configured to reduce a radial and a torsional component of a first load that exceeds a first threshold applied to the contact section, when the turbine rotates and applies the first load to the contact section and an energy absorber coupled to the center body, disposed adjacent to the contact section, and having an outer surface adapted to define a second portion of the flowpath, the energy absorber further adapted to collapse, when the turbine rotates and contacts the energy absorber and applies a second load that exceeds a second threshold to the energy absorber. | 09-02-2010 |
20100284814 | Machine component retention - An axial retention system for restraining axial movement of a first machine component having a dovetail within a complimentary-shaped dovetail slot in a second machine component that includes a first curved groove formed in a bottom surface of the dovetail slot and a second curved groove formed in a bottom surface of the dovetail. The first and second grooves are in alignment when the dovetail is located within the dovetail slot to thereby form a closed periphery aperture. A curved locking clip is received within the closed periphery aperture. An optional cover plate may be placed over the ends of the locking clip, with ends of the locking clip deformed by, for example, swaging. | 11-11-2010 |
20100329873 | RETAINING AND SEALING RING ASSEMBLY - A fan blade retaining and sealing ring assembly for an aft side of a bladed disk assembly is disclosed herein. The ring assembly includes an inner ring operable to prevent aft movement of a fan blade positioned in a slot formed in the blade disk. The ring assembly also includes an outer ring operable to seal against a platform of the fan blade. The inner ring and the outer ring are formed from different materials. | 12-30-2010 |
20110002787 | Blade Retention at a Compressor Rectifier Stage for Impact Resistance - A rectifier stage of an axial turbine engine compressor is placed directly downstream of the input blower of a turbo-reactor or turboshaft engine compressor. The blade roots of the rectifier stage are housed inside the inner shroud by insertion into respective slots. The blade roots include at least one opening protruding from the slot of the shroud, so as to receive a spiral ring having at least two loops so as to prevent the blade roots from escaping from the respective slots of the inner shroud, and so as to form a connection between the blade roots. A method for retaining blades of a rectifier stage of an axial turbine engine compressor on an inner shroud, in particular a rectifier stage placed directly downstream of the input blower of a turbo-reactor or turboshaft engine compressor, includes positioning a spiral ring having at least two loops inside the openings of the blade roots by threading one end of the ring successively into the openings until all of the spirals of the ring are housed inside the openings. | 01-06-2011 |
20110008173 | TURBINE ROTOR BLADE ASSEMBLY AND STEAM TURBINE - In a turbine rotor blade assembly | 01-13-2011 |
20110014053 | TURBINE BUCKET LOCKWIRE ROTATION PREVENTION - A retention system for a plurality of turbine buckets located in respective mating slots in a turbine rotor wheel includes a plurality of first retention slots formed in outer peripheral portions of the turbine wheel, and a plurality of second retention slots formed in wheel mounting portions of the buckets. The first and second retention slots are aligned to form an annular retention slot extending about a peripheral portion of the rotor wheel. A lockwire is located within the annular retention slot, the lockwire having engaged free ends. A plurality of axially-oriented retaining pins are fixed in the rotor wheel to hold the lockwire in the annular retention slot, and various techniques are employed for at least limiting or substantially preventing circumferential rotation of the lockwire within the annular slot. | 01-20-2011 |
20110014054 | GUIDE VANE OF A GAS TURBINE AND METHOD FOR REPLACING A COVER PLATE OF A GUIDE VANE OF A GAS TURBINE - The guide vane of a gas turbine comprises a blade having an outer platform connectable to a guide vane carrier or gas turbine casing, and at the opposite end an inner platform that carries a cover plate. The inner platform has a dovetail housing to which the cover plate is connected. The method for replacing the cover plate consists in separating the cover plate from the inner platform by cutting along the profile of the dovetail housing, then making the cover plate to slide out of the dovetail housing, thus inserting a new or refurbished cover plate into the dovetail housing. | 01-20-2011 |
20110020125 | Arrangement for axially securing blades in a rotor of a gas turbine - An arrangement for axially securing blades of a rotor of a gas turbine is provided. The arrangement includes a sealing element arranged on the end side surface of the rotor, which may be particularly reliably attached to the rotor by means of a sheet metal strip, the sheet metal strip including a shape-memory alloy. | 01-27-2011 |
20110027092 | ARRANGEMENT FOR AXIALLY SECURING ROTATING BLADES IN AROTOR, AND GAS TURBINE HAVING SUCH AN ARRANGEMENT - An arrangement for axial locking of rotating blades in a rotor is provided. The arrangement includes a shaft collar, a projection, plate-like sealing elements, and a blocking element. The sealing elements are provided for axially securing the rotating blades. At least one sealing element has an opening for securing the sealing elements against displacement in the circumferential direction. The blocking element is inserted in a recess from the end side of the shaft collar and blocks the displacement path of the sealing element. In order for the blocking element to be secured against unintentional releasing, the blocking element is fastened on the rotor disk using plastic deformation. | 02-03-2011 |
20110027093 | ANTI-WEAR DEVICE OF A TURBOMACHINE ROTOR - The present invention relates to an anti-wear device of a turbomachine rotor comprising a disk ( | 02-03-2011 |
20110038731 | ROTOR ASSEMBLY FOR A GAS TURBINE - A rotor assembly, for a gas turbine, has a plurality of rotor discs interconnected by an axially extending rim. The outside of the rim has a circumferential array of dovetail slots and the underside of the rim has a circumferential channel which extends radially part way into the slots, the respective discs thus being interconnected axially across the channel by an array of circumferentially spaced connecting portions. There is an array of blades, each blade having a blade root secured in a respective one of the dovetail slots. | 02-17-2011 |
20110052399 | AEROFOIL BLADE ASSEMBLY - An aerofoil blade assembly having a rotor disc having a radially outer surface provided with an axial slot and a radially inner surface provided with a circumferential slot, wherein the lower region of the axial slot intersects the upper region of the circumferential slot; an aerofoil blade having a blade root which is received by the axial slot and which is provided with a locating slot which corresponds to the circumferential slot; a retention key which engages with the circumferential slot and the locating slot to restrict axial displacement of the aerofoil blade with respect to the rotor disc, the retention key being provided with socket which, when the retention key is engaged in the circumferential slot and the locating slot, is substantially aligned with the axial slot. | 03-03-2011 |
20110123341 | DEVICE FOR AXIAL RETENTION OF MOBILE VANES MOUNTED ON A ROTOR DISC - A device for axial retention of mobile vanes mounted on a rotor disc includes two open rings, superimposed. At least one of the rings includes a rotating stop mechanism configured to cooperate with at least one hook of the disc. The two open rings are mounted in a discontinuous groove formed in the hooks, at the end of teeth situated on the periphery of the rotor disc, such that the rotating stop mechanism of the first ring is placed in the opening of the second ring. The significance of contact surfaces between the two rings allows a damping of vibrations during operation. | 05-26-2011 |
20110135481 | SYSTEMS AND METHODS FOR ASSEMBLING A ROTOR LOCK ASSEMBLY FOR USE IN A WIND TURBINE - A method of assembling a rotor lock assembly for use in a wind turbine. The wind turbine includes a rotor rotatably coupled to a generator by the rotor shaft. The generator and the rotor shaft are supported from a bedplate frame. The rotor shaft includes a rotor lock disk. The method includes coupling a support frame to the bedplate frame. The support frame is positioned adjacent to the rotor lock disk. A plurality of lock pin housings are coupled to the support frame. Each lock pin housing of the plurality of lock pin housings is positioned with respect to the rotor lock disk. A plurality of lock pins is provided. Each lock pin of the plurality of lock pins is configured to engage the rotor lock disk. Each lock pin is coupled between a corresponding lock pin housing of the plurality of lock pin housings and the rotor lock disk to facilitate limiting a rotation of the rotor shaft. | 06-09-2011 |
20110164983 | Locking Spacer Assembly - The present application describes a locking spacer assembly for use with a groove in a rotating disk. The locking spacer assembly may include a locking spacer with a leg and a wedge tool in contact with the leg so as to pull the leg inward and into the groove. | 07-07-2011 |
20110171031 | Turbomachine Rotor Comprising a Pretensioning Device for Pretensioning a Guide Vane - A turbomachine rotor, a rotor blade and a method for assembling a turbomachine rotor are provided. The turbomachine rotor includes a rotor blade with a blade root, a wheel disk with a groove in which the blade root engages such that the rotor blade is maintained in the groove in a positive fit in a radial direction. Further, a pretensioning device is provided, which is supported on the wheel disk as well as on the blade root and which exerts a pretensioning force on the blade root in the radial direction. The pretensioning device is designed such that the pretensioning force can be adjusted when assembling the turbomachine rotor. | 07-14-2011 |
20110176923 | SEAL PLATE AND BUCKET RETENTION PIN ASSEMBLY - A disk for a machine rotor includes a disk body having an outer periphery formed with a plurality of axially-oriented slots; a plurality of buckets, each bucket having an airfoil portion and an attachment portion, the attachment portion loaded axially into a respective one of the plurality of axially-oriented slots. A plurality of arcuate seal plate segments arranged about the outer periphery of the disk body, each covering at least two of the plurality of axially-oriented slots and respective attachment portions of the plurality of buckets. A retention pin extends axially through each of the plurality of arcuate seal plate segments and into an axially oriented bore in the disk body. The retention pin has an inner end engageable with a locking key and adapted to move the locking key into a locking position which prevents axial movement of a pair of adjacent ones of the plurality of buckets. | 07-21-2011 |
20110176924 | DEVICE ADAPTED TO BE FITTED WITH PROPELLER BLADES - A device adapted to be fitted with propeller blades includes a first retention ring including over a periphery thereof a plurality of radial bores; and a second retention ring including over a periphery thereof a plurality of radial bores, the first and second retention rings being mounted one on top of the other in the radial direction, each bore in the first retention ring being positioned opposite a bore in the second retention ring, a bore in the first retention ring arranged opposite a bore in the second retention ring forming a bore pair adapted to receive a foot of a blade. | 07-21-2011 |
20110229328 | Turbomachine Blade Locking Structure Including Shape Memory Alloy - A system for locking blades to a rotor of a turbomachine including adjacent pairs of generally axially extending grooves for receiving blades inserted in an axial direction. A circumferential slot is disposed around the periphery of the rotor and a locking device assembly is located in the circumferential slot between an adjacent pair of grooves. The assembly includes a last locking device, a spacer and key member formed of a shape memory alloy. The key member is located in a gap between the last locking device and the spacer. The shape memory alloy key member is heated to cause a transition from a martensite to an austenite phase to cause the key member to engage and press against opposing faces of the last locking device and the spacer to increase a force applied to a respective pair of blades in the adjacent pair of grooves. | 09-22-2011 |
20110250071 | TURBINE WHEEL WITH AN AXIAL RETENTION SYSTEM FOR VANES - A turbine wheel includes: a plurality of blades, a rotor including a disk having the blades mounted at a periphery thereof, each blade including an airfoil with a foot secured to a platform carrying an attachment member engaged in a housing that opens into the periphery of the disk and that extends axially between two opposite side faces of the disk, the housings being spaced apart from one another by portions of the disk that form teeth, and an axial retention plate retaining the blades on the disk and including a retention plate situated on one side of the disk. On the other side of the disk, the teeth of the disk present portions in relief that project radially and that form abutments pressing axially against the portions in relief that are formed under the platforms of the blades and that are set back relative to side faces of the attachment members situated beside a second side face of the disk, and side faces of the attachment members of the blade and of the disk at its periphery are situated in substantially a same plane on each side of the disk. | 10-13-2011 |
20110255982 | TURBINE BLADE RETENTION DEVICE - A turbine blade assembly has a turbine blade with a root section and an airfoil section. The root section has one of a radially extending groove or flange, and a retainer element has the other of the groove and the flange. The groove receives the flange to hold the retainer element and the blade together. The retainer element has axial ends extending radially inwardly to secure a turbine blade assembly within a disk slot in a turbine rotor disk. A method is also disclosed. | 10-20-2011 |
20110255983 | DEVICE FOR ATTACHING HAMMER CLAMP BLADES, ASSOCIATED COMPRESSOR HUB, COMPRESSOR AND TURBINE ENGINE - The invention relates to a locking device for enabling the circular locking of a set of blades provided with a hammer base ( | 10-20-2011 |
20110262278 | FAN BLADE RETENTION SYSTEM - A fan comprises a rotatable hub assembly having an inner anchor assembly, a plurality of fan blades, a motor assembly, and a plurality of cables. The outer ends of the cables are coupled to the outer ends of the fan blades, and the inner ends of the cables are coupled to the inner anchor assembly. The inner anchor assembly may further include a disc-shaped plate and a plurality of inner anchor members to which the cables may be coupled. The inner anchor members may include a rear anchor portion and fore anchor portion, and these anchor portions may be angularly offset. A plurality of winglets and/or outer anchor members may be coupled to the outer ends of the fan blades to which the outer ends of the cables may be coupled. The outer ends of the cables may further comprise swaged tips outboard of the winglets and/or outer anchor members. | 10-27-2011 |
20110305576 | GAS TURBINE ENGINE BLADE MOUNTING ARRANGEMENT - A mounting arrangement for a gas turbine engine blade having a root employs a lightweight, simple and economical leaf spring spacer which biases the blade root in a radially outward direction to minimize unwanted movement of the root within a conforming slot in a blade hub under conditions such as windmilling when centrifugal force alone is inadequate to tightly seal the root within the slot. | 12-15-2011 |
20110311366 | TURBINE WHEEL PROVIDED WITH AN AXIAL RETENTION DEVICE THAT LOCKS BLADES IN RELATION TO A DISK - A turbine wheel including a plurality of blades, each of the blades presenting an airfoil, a platform, and an attachment member, a disk having the blades mounted at the periphery thereof, the attachment member of each blade being engaged in a housing that opens into a periphery of the disk and extending axially between two opposite faces of the disk, the housings being separated by teeth, and an axial retention device for retaining the blades. The disk includes a first stop member, and the platform of the blade includes a projection projecting axially beyond one of the faces of the disk. The projection includes a second stop member. The axial projection, the second stop member, and the face of the disk together form a groove facing towards the axis of the disk, the groove serving to receive the axial retention device. | 12-22-2011 |
20110318187 | SEALING DEVICE - A sealing device for sealing a gap between a dovetail of a bucket assembly and a rotor wheel is disclosed. The sealing device includes a cover plate configured to cover the gap and a retention member protruding from the cover plate and configured to engage the dovetail. The sealing device provides a seal against the gap when the bucket assembly is subjected to a centrifugal force. | 12-29-2011 |
20120027605 | TURBOMACHINE BLADE, A ROTOR, A LOW PRESSURE TURBINE, AND A TURBOMACHINE FITTED WITH SUCH A BLADE - The invention relates to a turbomachine blade made of composite material and presenting a root with a bulb-shaped end suitable for engaging in a slot of a rotor disk. In characteristic manner, the end of the root of the blade is provided, beside one of its front faces, with a projecting portion having two symmetrical fins about the axial midplane of the root, each fin having a bearing face suitable for limiting tilting of the blade relative to the rotor disk about the axial direction. | 02-02-2012 |
20120034088 | Method for Connecting a Tension-Torsion Strap - An apparatus may comprise a housing, a first member, and a second member. The housing may have a first end, a second end, a first side, a second side, an opening located in the first end, and a passage extending from the opening. The first member may extend from the first side. The first member may have a first channel in communication with the passage and the channel has a first center axis. The second member may extend from the first side. The second member may have a second channel in communication with the passage and the second channel has a second center axis substantially aligned with the center axis of the channel in the first member. | 02-09-2012 |
20120039719 | Rotor section for a rotor of a turbomachine, and rotor blade for a turbomachine - A rotor section for a rotor of a gas turbine, a rotor blade, and a blocking element are provided. The rotor section includes a rotor disk including rotor blades that are inserted thereon in holding grooves and that are secured against sliding along the holding grooves by means of a sealing element arranged at the end face. In order to specify a reliable, simple, and easy-to-design construction for the circumferential fixing of the sealing elements, it is proposed that each sealing element be secured by one blocking element, which engages in a hole arranged at the end face in the rotor blade root. | 02-16-2012 |
20120045340 | ROTOR LOCKING DEVICE AND METHOD FOR LOCKING A ROTOR OF A WIND TURBINE - The invention relates to a mobile rotor locking device for locking a rotor of a wind turbine, the rotor locking device being designed to lock a rotor in such a way that it is prevented from rotating about a horizontal axis, and that a longitudinal axis of a rotor blade is fixed in a vertical plane. The invention also relates to a kit and a locking member for a mobile rotor locking device and to a method for locking a rotor of a wind turbine. According to the invention, the rotor locking device is characterized in that the rotor locking device is designed to fix a main shaft, on which a rotor is disposed torsionally stiffly, so that it is prevented from rotating about its longitudinal axis. | 02-23-2012 |
20120045341 | FAN ROTOR FOR AN AIRPLANE TURBOJET - A fan rotor for an airplane turbojet including locking blade roots in the respective grooves of an airplane turbojet fan rotor. Each blade root is housed in a groove that is closed by a main latch and by an additional latch that is distinct from the main latch and that is spaced apart therefrom by a predetermined distance. | 02-23-2012 |
20120057980 | AXIAL LOCKING SEALS FOR AFT REMOVABLE TURBINE BLADE - A turbine blade rotor assembly provides sealing for the rotor components and bi-direction axially locking of the blades on the rotor using a seal plate on the aft exhaust side without axial locking on the forward intake side of the rotor and blade array. As a result, the blades can be removed from the aft direction without moving the turbine casing cover. | 03-08-2012 |
20120063907 | CIRCUMFERENTIAL BLOCKING DEVICE OF CLAMP VANES FOR TURBINE ENGINE, WITH IMPROVED RADIAL DEPLOYMENT - The invention relates to a device ( | 03-15-2012 |
20120087798 | TURBINE BUCKET LOCKWIRE ROTATION PREVENTION - A retention system for a plurality of turbine buckets located in respective mating slots in a turbine rotor wheel includes a plurality of first circumferentially-oriented retention slots formed in outer peripheral portions of the turbine wheel; a plurality of second circumferentially-oriented retention slots formed in wheel mounting portions of said buckets, the first and second circumferentially-oriented retention slots aligned to form an annular lockwire retention slot; and a lockwire located within the annular lockwire retention slot. A first surface feature on one or both of the turbine rotor wheel and one or more of said plurality of turbine buckets is adapted to engage a second surface feature on the lockwire for preventing rotation of the lockwire beyond predetermined limits. | 04-12-2012 |
20120087799 | AXIAL RETENTION DEVICE FOR TURBINE SYSTEM - An axial retention device for a turbine is disclosed. The axial retention device includes a latch associated with a mating surface of one of a turbine component and a support structure. The latch has an outward bias and includes an axial load surface. The axial retention device further includes a pocket defined in a mating surface of the other of the turbine component and the support structure. The pocket is configured to accept the latch therein and includes a mating axial load surface. Engagement of the latch and the pocket allows the axial load surface and the mating axial load surface to interact, preventing axial movement of the turbine component with respect to the support structure in at least one direction. | 04-12-2012 |
20120107124 | AIRFOIL ATTACHMENT ARRANGEMENT - An example airfoil retention arrangement includes a retention assembly having a first retention segment and a second retention segment. Each of the retention segments is separately moveable to an installed position relative to an airfoil assembly and a support structure. The retention segments each have a portion position between a lip of the airfoil assembly and a collar of the support structure when the retention segments are in the installed position. The retention assembly is configured to limit radial movement of an airfoil relative to the support structure when in the installed position. | 05-03-2012 |
20120107125 | REINFORCED FAN BLADE SHIM - A shim configured to be inserted between a fan blade root of a turbojet and a bottom of a compartment in which this root is housed, the compartment being delimited by a fan disk. The shim includes a metal stiffener including at least one external element made of an elastomer material, and including a support surface of the external element. The support surface includes at least one corrugated zone. | 05-03-2012 |
20120114490 | TURBINE ASSEMBLY AND METHOD FOR SECURING A CLOSURE BUCKET - According to one aspect of the invention, a turbine assembly is provided, wherein the turbine assembly includes a drum rotor comprising a slot and a closure bucket configured to be placed in the slot, the closure bucket including a lock pin disposed in a base member of the closure bucket. In addition, a portion of the lock pin is configured to rotatably extend into a cavity in the slot thereby securing the closure bucket within the slot. | 05-10-2012 |
20120121428 | BLADE RETENTION DISK - A blade retention disk includes, on its external surface, a peripheral annular groove configured to receive a plurality of blade roots of the hammer attachment type, the peripheral annular groove including a loading orifice intended for the introduction of blade roots inside the peripheral annular groove. The retention disk also includes: a crown covering the peripheral annular groove; a crown centering device to center the crown, the crown centering device and the crown forming an air supply enclosure from the bottom of the peripheral annular groove; at least one orifice opening in the air supply enclosure, the orifice being configured to introduce cooling air into the air supply enclosure. The blade retention disk finds a direct application in the field of low pressure turbines for aircraft turbine engines. | 05-17-2012 |
20120128498 | BLADED DISK ASSEMBLY - A bladed disk assembly is disclosed herein. The bladed disk assembly includes a disk centered on an axis. The disk has at least one groove extending along the axis. The bladed disk assembly also includes a blade received in the groove. The bladed disk assembly also includes a retaining clip contacting the blade and limiting movement of the blade along the axis. The retaining clip is engaged with the disk through a snap-fit. | 05-24-2012 |
20120171040 | DAMPER COVERPLATE AND SEALING ARRANGEMENT FOR TURBINE BUCKET SHANK - A bucket pair in a turbomachine includes a first bucket having an airfoil and a shank; a second adjacent bucket having a second airfoil and a second shank adjacent the first shank; a first axial slot in the first shank; and an elongated, straight damper pin adapted to seat in the first axial slot, the damper pin formed with slanted forward and aft end faces. | 07-05-2012 |
20120177498 | AXIAL RETENTION DEVICE FOR TURBINE SYSTEM - An axial retention device for a turbine system is disclosed. The axial retention device includes a pocket defined in a mating surface of one of a turbine component and a support structure. The pocket includes a first axial load surface. The axial retention device further includes a latch comprising a base member and a pivotal member. The base member is associated with a mating surface of the other of the turbine component and the support structure. The pivotal member is configured to engage the pocket and includes a first mating axial load surface. Engagement of the pivotal member and the pocket allows the first axial load surface and the first mating axial load surface to interact, preventing axial movement of the turbine component with respect to the support structure in the at least one direction. | 07-12-2012 |
20120177499 | BLADE FASTENING HAVING SAFETY DEVICE FOR TURBINE BLADES - A safety device for a turbine blade is provided. The safety device includes a shear pin, a clamping piece and a securing element, wherein the shear pin is arranged in a corresponding bore in the turbine blade foot and the clamping piece is designed having an upper limb and a lower limb, wherein the clamping piece exerts a radial force on the turbine blade foot for radial safeguarding. | 07-12-2012 |
20120189453 | MECHANICAL JOINT - A mechanical joint for joining two components, the joint having a male part on one component and a corresponding female part on the other component. The male and female parts have respective castellations which intercalate on insertion of the male part into the female part along a direction of insertion. Respective abutment surfaces are formed on the projections of the castellations. The castellations are configured such that, after the insertion of the male part into the female part, the male and female parts can be rotated relative to each other around the direction of insertion to bring: (i) the abutment surfaces into facing alignment and thereby prevent the parts from being pulled apart, and (ii) the indentations of the castellations into facing alignment. The joint has one or more locking members which are insertable into the facing indentations to prevent further relative rotation of the male and female parts. | 07-26-2012 |
20120201685 | JOINING MECHANISM AND METHOD FOR INTERLOCKING MODULAR TURBINE ENGINE COMPONENT WITH A SPLIT RING - A modular airfoil assembly ( | 08-09-2012 |
20120237350 | TURBINE BLADE WITH MATE FACE COOLING AIR FLOW - A gas turbine engine blade comprises a dovetail, a shank extending from the dovetail, an airfoil, and a platform between the shank and the airfoil. The platform comprises a side wall extending between an upstream side and a downstream side of the platform. A first pin channel extends from the upstream side of the sidewall and a second pin channel, co-axial with the first pin channel, extends from the downstream side of the sidewall. The first channel includes a radial notch at the upstream longitudinal end of the first pin channel. | 09-20-2012 |
20120237351 | RETENTION FOR BONDED HOLLOW FAN BLADE COVER - A two part airfoil has a suction side, a pressure side, a rib extending from one of the pressure side or the second side, the rib having a groove therein, and a riblet extending from an other of the pressure side or the suction side, the riblet fitting within the groove. | 09-20-2012 |
20120244004 | COMPONENT LOCK FOR A GAS TURBINE ENGINE - A lock assembly includes a lock body with an undercut slot which receives a retaining wire of a polygon shape. | 09-27-2012 |
20120251329 | ROTOR STRUCTURE - The rotor structure is provided with a rotation shaft body in which a blade groove is formed at an outer circumference part, and extends in a circumferential direction of the axis line, and a plurality of blade bodies which are arrayed in the circumferential direction at the outer circumference part of the rotation shaft body, wherein a blade fixing piece is installed so as to be a positioned between at least one set of adjacent two blade bodies in the circumferential direction inside the blade groove, a projected part is formed at where either an opening wall part or the groove opening side of the blade groove and the blade fixing piece, and a recessed part which is fitted into the projected part is formed at where the other one of them. | 10-04-2012 |
20120257976 | LOCKING DEVICE ARRANGEMENT FOR A ROTATING BLADED STAGE - A locking device arrangement for a rotating bladed stage is provided and includes a wheel formed to define a substantially circumferential slot and three slot sections, one of the slot sections including one radial slot and two lock slots to permit blade and blade lock installation along the circumferential slot, respectively, the other slot sections including a lock slot to permit blade lock installation along the circumferential slot, and the three slot sections being separated from one another with angular offsets such that the wheel is mass balanced substantially evenly about a desired center of rotation with the blade locks installed and to reduce accumulation of flowpath gaps. | 10-11-2012 |
20120301308 | GAS TURBINE COMPRESSOR LAST STAGE ROTOR BLADES WITH AXIAL RETENTION - A rotor blade and blade retention key assembly includes: a radially outer airfoil, a shank and a radially inner attachment dovetail. The attachment dovetail has a radially innermost surface formed with a notch at one axial end thereof, and a retention key is received in the notch, and rotatable from a retracted position where a retention key portion is substantially flush with the radially innermost surface, to an extended position where the retention key portion projects inwardly from said radially innermost surface and into a recess or pocket formed in a rotor wheel slot to prevent axial movement of the blade within the slot. | 11-29-2012 |
20120315144 | TURBOMACHINE BLADE LOCKING SYSTEM - Systems are disclosed herein for enhancing the longevity of turbomachine components. Such systems include a turbomachine blade that has a blade portion extending from a base portion. The base portion includes an axial rail configured to extend into an axial groove disposed in a rotor of a turbomachine. The axial rail includes a first locking recess configured to align with a second locking recess along the axial groove. The system also includes a blade locking assembly having a first locking insert and a second locking insert. The first locking insert is configured to be inserted in both the first and second locking recesses. The second locking insert is configured to be inserted in the first or second locking recess adjacent the first locking insert. | 12-13-2012 |
20120321476 | RETENTION DEVICE FOR A ROTATING BLADE - A blade assembly including: a hub which is rotatable about an axis; at least one blade having an aerofoil portion and a root, wherein the root is coupled to the hub using a primary retention device which prevents radial separation of the root and hub in normal use; and, a secondary retention device having a root part and a hub part, the root part being located radially inwards of the hub part in a retention cavity in use, wherein at least a portion of the root part enters the retention cavity via an interlock which prevents radial separation of the root and hub in the event of a primary retention device failure. | 12-20-2012 |
20120321477 | Rotor device for a jet engine with a disk wheel and several rotor blades - The present invention proposes a rotor device for a jet engine with a disk wheel and several rotor blades connected to said disk wheel, with the rotor blades being arranged in each case via a blade root substantially in the axial direction inside recesses of the disk wheel. Several locking segments are provided in the recesses of the disk wheel for axially locking the rotor blades, said locking segments interacting on the one hand with grooves of the rotor blades and on the other hand with at least one groove of the disk wheel. In the area of the groove of at least one of the rotor blades between the groove of the rotor blade and a locking segment there is a positive fit preventing a relative movement between the rotor blades and the locking segments. | 12-20-2012 |
20130022469 | Turbine Rotor Non-Metallic Blade Attachment - In an engine disk and blade combination, the metallic disk has a plurality of first blade attachment slots and a plurality of second blade attachment slots circumferentially interspersed with each other. There is a circumferential array of a plurality of first blades. Each first blade has an airfoil and an attachment root. The attachment roots are respectively received in associated said first attachment slots. There is a circumferential array of second blades. Each second blade has an airfoil and an attachment root. The attachment roots are respectively received in associated said second slots. The first blades and second blades are non-metallic. The first blades are radially longer than the second blades. The first slots are radially deeper than the second slots. | 01-24-2013 |
20130028743 | Systems, Methods, and Apparatus for Sealing a Bucket Dovetail in a Turbine - Certain embodiments of the invention may include systems methods, and apparatus for sealing a bucket dovetail in a turbine. According to an example embodiment of the invention, a method is provided for sealing a gap between a bucket dovetail and a rotor wheel slot. The method can include modifying a bucket tab associated with the bucket dovetail to accept a seal tab, wherein the seal tab is configured to expand as a function of temperature; maintaining the seal tab in contact with the modified bucket tab; sealing a gap between the bucket dovetail and the rotor wheel slot with the seal tab; and modifying at least a portion of the seal tab as a function of temperature for further sealing gap between the bucket dovetail and the rotor wheel slot. | 01-31-2013 |
20130039770 | GAS TURBINE ROTOR WITH PURGE BLADES - A rotor for a gas turbine engine includes a plurality of turbine blades extending radially outwardly of a rotor body. A plurality of purge blades are positioned to rotate with the rotor body, and to drive air radially outwardly toward the turbine blades. | 02-14-2013 |
20130052024 | Turbine Nozzle Vane Retention System - The present application provides a turbine nozzle vane retention system. The turbine nozzle vane retention system may include a number of nozzles with a platform, a slot extending into the platform, and a pin extending between the slot of a first nozzle and the slot of a second nozzle, | 02-28-2013 |
20130052025 | REPLACEABLE STAKING INSERT ASSEMBLY AND METHOD - A rotor assembly. The rotor assembly may include a rotor, at least one axial slot positioned about the rim of the rotor having a first staking recess positioned therein, a blade positioned within each of the axial slots having a second staking recess positioned therein, a staking insert having a base portion and a projection extending therefrom with the base portion being disposed within the first staking recess and the projection being disposed within the second staking recess, and a shim positioned within the first staking recess adjacent to the base portion, opposite the projection, of the staking insert. The first staking recess retains the staking insert while the projection of the staking insert retains the blade in both the aft and forward directions. | 02-28-2013 |
20130052026 | AXIAL RETENTION SYSTEM FOR A BLADED ROTOR WITH MULTIPLE BLADE TYPES - A bladed rotor includes a blade lock mountable to a rotor hub adjacent to a multiple of blade slots. The blade lock includes at least one interface feature adjacent to a first of the multiple of blade slots. A first rotor blade includes a blade feature which interfaces with the interface feature to permit the first rotor blade to be axially mounted within the first of the multiple of blade slots but not within a remainder of the multiple of blade slots. | 02-28-2013 |
20130121836 | BLADE CONNECTION FOR A ROTOR BLADE OF A WIND TURBINE - A blade connection for a rotor blade of a wind turbine having a plurality of receptacles which extend in the longitudinal direction of the rotor blade and can each receive a longitudinal bolt and are in contact with a component having an inner thread for the longitudinal bolt. The rotor blade is manufactured from two materials, at least in the region of the blade connection, wherein a first material is a composite material, and a second material is a composite material provided with at least one reinforcement layer made of metal and/or ceramic. The receptacles are composed of the first material and the second material is bonded to the first material. | 05-16-2013 |
20130136605 | DEVICE FOR LOCKING A ROOT OF A ROTOR BLADE - A device for locking a root of a rotor blade in a groove in a rotor disk of a turbomachine including: a circular ring sector configured to be mounted, transversely to the axis of the turbomachine, in a groove in the rotor disk; at least one locking wedge, which is rigidly secured and perpendicular to the ring sector, and extends parallel to the axis of the ring sector so as to hold the root of the blade radially in the groove; and at least one locking tooth extending from the ring sector radially with respect to the axis of the ring sector, so as to prevent the root of the blade from moving axially in the groove. | 05-30-2013 |
20130149159 | GAS TURBINE ENGINE PART RETENTION - A gas turbine engine includes an engine casing structure and a retention block assembly. The engine casing structure includes a pocket which receives the retention block assembly. The retention block assembly includes a stop block and a pin that retains the stop block within the pocket. The stop block is loose relative to the pin. | 06-13-2013 |
20130156588 | ELECTRICAL GROUNDING FOR FAN BLADES - A fan rotor includes a fan blade for use in a gas turbine engine includes a sheath formed of a material that is more conductive than a main fan blade body. A grounding element provides a grounding path from the sheath into a rotor receiving the fan blade. A gas turbine engine incorporating the fan blade is also disclosed. | 06-20-2013 |
20130156589 | TURBINE ROTOR RETAINING SYSTEM - A rotor retaining system for a rotor assembly of a gas turbine engine includes a washer interlocking multiple retaining nuts to prevent relative rotation. The retaining nuts retain a rotor disc and a cover plate in position, respectively. A wire is provided to retain the washer in position and which may dampen vibration during engine operation. | 06-20-2013 |
20130156590 | GAS TURBINE ENGINE ROTOR WHEEL HAVING COMPOSITE MATERIAL BLADES WITH BLADE-ROOT TO DISK CONNECTION BEING OBTAINED BY CLAMPING - A rotor wheel for a gas turbine engine, the wheel including: a metal holder disk including a plurality of teeth at its periphery, the teeth extending radially outwards from the disk; a plurality of composite material blades, each blade including a root engaged between two adjacent teeth of the holder disk and that is held against the teeth by a pivot connection; a clamp disk including a plurality of teeth at its periphery extending in an axial direction, the clamp disk being fastened against the holder disk and on the same axis, with each of its teeth taking up a circumferential position between a blade root and a tooth of the holder disk; and a mechanism exerting a clamping force in a circumferential direction urging the teeth of the clamp disk against the blade roots. | 06-20-2013 |
20130177429 | SYSTEM FOR AXIAL RETENTION OF ROTATING SEGMENTS OF A TURBINE - A turbomachine system includes a turbomachine that includes a rotor that includes a rotational axis, a first rotating segment having a first mating axial mount coupled to a first axial mount of the rotor in a first installed position and a first pin configured to insert into a first inserted position in both a first slot in the rotor and a first mating slot in the first rotating segment. The first pin in the first inserted position is configured to block axial movement of the first mating axial mount relative to the first axial mount. The turbomachine also includes a second rotating segment having a second mating axial mount coupled to a second axial mount of the rotor in a second installed position. The second rotating segment in the second installed position is configured to block removal of the first pin. | 07-11-2013 |
20130189111 | ROTOR FOR A TURBOMACHINE - A rotor for a turbomachine, in particular for a jet engine, having a blade ring which includes multiple differently designed rotor blades ( | 07-25-2013 |
20130216387 | SYSTEM AND METHOD FOR BLADE RETENTION - A system and method for securing a blade within a disk so as to eliminate the need for permanently deforming materials associated with the blade disk is disclosed. A recess is formed generally within each slot used to secure a blade within the disk. A retaining insert is positioned within the recess and a wedge insert is positioned within a slot of the retaining insert, such that a pressure is applied to the retaining insert thereby deflecting the retaining insert into a pre-set radial position to prevent axial movement of the blade within the slot of the disk. | 08-22-2013 |
20130224030 | TURBINE-BLADE RETAINING STRUCTURE AND ROTARY MACHINE HAVING THE SAME - Deformation of end portions of locking pieces exposed through an insertion window portion in the axial direction is prevented, and the occurrence of a crack in a welded portion is prevented. At least one of the end portions of adjacent locking pieces exposed through the insertion window portion is provided with a thick-plate portion that expands in the disc-thickness direction so as to be inside the insertion window portion. | 08-29-2013 |
20130236317 | BLADE CLIP - A clip to connect a blade to a rotor disk, the blade with a root and a tip in a spanwise direction, and a leading edge and a trailing edge in a chordwise direction, the root with a bottom surface, includes a locking mechanism shaped to engage a complementary slot extending into the bottom surface of the blade root in the spanwise direction; a support connected to the locking mechanism extending the length of the bottom surface of the root in the chordwise direction; and first and second arms extending radially inward converging in an axial direction so that the arms are closer at their distal ends to engage the rotor disk. | 09-12-2013 |
20130243601 | CONNECTING SYSTEM FOR METAL COMPONENTS AND CMC COMPONENTS, A TURBINE BLADE RETAINING SYSTEM AND A ROTATING COMPONENT RETAINING SYSTEM - A connecting system for metal component and CMC components, a turbine blade retaining system and rotating component retaining system are provided. The connecting system includes a retaining pin, a metal foam bushing, a first aperture disposed in the metal component, and a second aperture disposed in the ceramic matrix composite component. The first aperture and the second aperture are configured to form a through-hole when the metal component and the ceramic matrix composite component are engaged. The retaining pin and the metal foam bushing are operably arranged within the through-hole to connect the metal component and the ceramic matrix composite component. | 09-19-2013 |
20130251532 | SECURING DEVICE FOR AXIALLY SECURING A BLADE ROOT OF A TURBOMACHINE BLADE - A securing device ( | 09-26-2013 |
20130272886 | SYSTEM AND METHOD FOR COVERING A BLADE MOUNTING REGION OF TURBINE BLADES - A system includes a cover segment set configured to mount in first and second grooves circumferentially along a blade mounting region of a turbine rotor. The cover segment set includes a seal segment and a cover segment. The seal segment has a seal body with a lock feature, wherein the seal segment is configured to mount circumferentially along the second groove. The cover segment includes first and second lips extending along first and second circumferential portions of a cover body. The first and second lips are at an offset from one another. The first lip is configured to mount circumferentially along the first groove, the second lip is configured to mount circumferentially along the second groove adjacent the seal segment, and the second lip includes a mating lock feature configured to couple with the lock feature of the seal body. | 10-17-2013 |
20130302171 | DEVICE FOR ATTACHING BLADES TO A TURBINE ENGINE ROTOR DISK - The invention provides a device for attaching blades to a rotor disk of a turbine engine, comprising: a rotor disk provided at its outer periphery with a plurality of slots, each formed between two adjacent disk teeth and extending axially between front and rear faces of the disk; a plurality of blades, each having a respective root mounted in a slot of the disk; and at least one pin mounted in the rotor disk to pass through the roots of at least two adjacent blades and extending between the front and rear faces of the rotor disk so as to attach the blades to the rotor disk. | 11-14-2013 |
20130315744 | FAN ROTOR AND ASSOCIATED TURBOJET ENGINE - A fan rotor including a disk carrying blades including roots engaged in slots in the disk, a frustoconical cap mounted on the disk upstream from the blades, and a retaining mechanism axially retaining the blades on the disk and including a ring mounted in an annular groove of the disk and forming an abutment for the roots of the blades, the ring being festooned or crenellated and co-operating with a festooned radial annular bead of the annular groove of the disk, and a mechanism preventing the ring from moving in rotation, which includes an annulus carrying at least one axial tooth inserted in hollow portions of the bead of the disk and of the ring, the annulus being fastened by bolts on an upstream radial face of the disk. | 11-28-2013 |
20130330198 | Turbine Rotor and Blade Assembly with Blind Holes - The present application provides a turbine rotor and blade assembly for a steam turbine. The turbine rotor and blade assembly may include a rotor, a number of buckets positioned about the rotor, a locking blade positioned about the rotor, and a blind hole positioned about the rotor adjacent to the locking blade. | 12-12-2013 |
20130343896 | CATCHER RING ARRANGEMENT - This invention relates to a blade assembly comprising: a hub which is rotatable about an axis; at least one blade having an aerofoil portion and a root, wherein the root is coupled to the hub using a primary retention device which prevents radial separation of the root and hub in normal use; and, a secondary retention device which comprises an annular catcher having a restriction through which the root portion cannot radially pass, the restriction being located radially outwardly and radially spaced from the root part during use. | 12-26-2013 |
20140044550 | Restraint Mechanism for Rotor Blades of a Turbo Engine, an Assembly Method and a Turbo Engine - A restraint mechanism for rotor blades of a turbo engine on a rotor disk having blade root receptacles for radial guidance of the rotor blades is disclosed. The restraint mechanism has a plurality of axial securing elements, each having at least one web for positioning in a blade root receptacle, such that each web has a retaining section at one end for establishing a form-fitting design to a mating brace of another axial securing element. A method for axially securing rotor blades on a rotor disk and a turbo engine are also disclosed. | 02-13-2014 |
20140064977 | TURBINE ROTOR BLADE ROOT ATTACHMENTS - A pinned root fixing arrangement of axial flow steam turbine rotor discs made of a low alloy that is less susceptible to stress corrosion cracking (SCC). Such an arrangement has a first ratio, which is defined as ratio of the axial breadth of the disc fingers and the sum of the axial breath and the axial breadth G of the gap between adjacent disc fingers, in the range of about 0.4 to about 0.6 and further has a second ratio, which is defined as the ratio of the length of the disc fingers and the blade fingers to the diameter, between 4 and 6. | 03-06-2014 |
20140072437 | TURBOMACHINE ROTOR WITH A MEANS FOR AXIAL RETENTION OF THE BLADES - A rotor of a turbomachine, such as a multi-flow turbojet engine fan, has a disc including, on the rim thereof, substantially axial slots with a dovetailed cross-section, and blades mounted individually in the slots, an axial wedge positioned between the root of the blades and the bottom of the slots, and a transverse lock providing upstream axial immobilization of the blades in the slot thereof. The lock is guided in radial notches formed in the flanks of the slots and radially supported against the wedge. The axial wedge is immobilised in the upstream direction, butting up against a transverse annular component secured to the disc. | 03-13-2014 |
20140127026 | LOCKING BLADE FOR A ROTOR - A locking blade for a rotor can include an airfoil portion with a root from which a tongue extends. Opposed bucket segments can engage the tongue and can be retained in a longitudinal direction of the blade by a fastener, such as a pin, that can extend through holes in the segments and tongue. Tines parallel to and on opposite sides of the tongue can extend from the root and include holes through which the fastener can extend, the bucket segments extending between respective tines and the tongue. The structure can eliminate an assembly gate in a rotor. | 05-08-2014 |
20140127027 | TURBINE ROTOR FOR A THERMAL ELECTRIC POWER STATION - The technical field of the invention is that of turbine rotors for a thermal electric power station and the subject of the invention is, more particularly, a rotor of a turbine for a thermal electric power station, said rotor comprising a plurality of blades, each comprising at least one root and a vane; and at least one rotor disk secured to a shaft able to be in rotation about a reference axis, the rotor disk comprising on its periphery outgrowths in which to fit the blades, so that the vanes of the blades are arranged radially with respect to the reference axis; said rotor being one wherein: the rotor disk comprises a groove opening axially and having a lower face and an upper face, the lower face of the groove of the rotor disk being situated on the periphery of said rotor disk and the upper face of the groove of the rotor disk being situated on the outgrowths and facing the lower face; each of the blades comprises, at its root, a lateral projection directed axially, said lateral projection having, in its lower part, a groove portion having an upper face situated in the continuation of the upper face of the groove of the rotor disk; at least one locking means for locking the blades is positioned in the groove of the rotor disk. | 05-08-2014 |
20140133991 | GAS TURBINE ENGINE FAN BLADE LOCK ASSEMBLY - A gas turbine engine fan blade lock assembly includes a fan hub that has blade slots each configured to receive a root of a fan blade. The fan hub includes circumferentially spaced first slots. A lock ring is configured to move between unlocked and locked positions. The lock ring includes circumferentially spaced second slots aligned with the first slots in the locked position, and multiple discrete pins. Each pin is configured to be slidably received in paired first and second slots in the locked position to prevent rotational movement of the lock ring relative the fan hub. | 05-15-2014 |
20140133992 | CONNECTION MECHANISM FOR MOUNTING BLADES FOR A WIND TURBINE - A variety of wind turbine assemblies are described herein. The wind turbine assemblies each include a plurality of blades that have a sidable connection member to secure the wind blades to a shaft member. In some configurations, recesses are provided on the shaft to secure the blades. Other configurations include separate mounting members that secure around the shaft to operatively connect the blades to the shaft. | 05-15-2014 |
20140205460 | METHOD AND SYSTEM FOR SELF-LOCKING A CLOSURE BUCKET IN A ROTARY MACHINE - A system includes a turbomachine that includes at least one rotor disk or stage having a peripheral portion disposed about a rotational axis of the rotor disk or stage. The peripheral portion includes a groove that extends circumferentially about the peripheral portion. The groove has a first groove surface and a second surface disposed opposite the first groove surface. The turbomachine also includes a closure bucket disposed adjacent at least one bucket within the groove. The closure bucket has a first surface that interfaces with the first groove surface and a second groove surface disposed opposite the first surface. The closure bucket blocks circumferential movement of the at least one bucket within the groove relative to the rotor disk or stage. The turbomachine further includes a single wedge disposed between and contacting the second surface of the closure bucket and the second groove surface to secure the closure bucket within the groove. | 07-24-2014 |
20140219807 | UNDER-ROOT SPACER FOR GAS TURBINE ENGINE FAN BLADE - A gas turbine engine rotor includes a hub having a slot. A blade includes a root received in the slot. An under-root area is provided between the root and the fan hub in the slot. A spacer includes first and second portions that cooperate with one another to provide an adjustment feature with discrete height settings. The adjustment feature provides different radial heights of the spacer. The spacer is arranged in the under-root area beneath the root. | 08-07-2014 |
20140234111 | BLADE ARRANGEMENT - A blade arrangement is provided having a blade carrier and a retaining groove arranged therein, which retaining groove has projections extending along side walls thereof forming undercuts and into which a number of blades are inserted forming a blade ring of a turbomachine. Each blade has a blade root which engages into the undercuts, and each blade is pressed against the projections by an element arranged between a blade root underside and a groove base of the retaining groove. It is further provided that each element is of plate-like form and has, in the projection of the blade airfoil in the direction of the groove base, at least one bead, arranged beneath the blade airfoil, for imparting a pressing action, and in the longitudinal direction of the retaining groove, only part of the blade root which the element presses against is covered. | 08-21-2014 |
20140241893 | SYSTEM FOR SPECIFYING AN INSTALLATION POSITION OF ROTOR BLADES, SECURING ELEMENT, ROTOR BLADE, TURBOMACHINE, AND METHOD - A system for specifying an installation position of adjacent rotor blades of a blade row of a turbomachine is disclosed. The system has a plurality of axial securing elements, which have at least two sections with different profile areas for the arrangement in each case between a groove base of a rotor shaft and a blade root, which are joined together by a connecting web at a groove distance from one another, and which have counter-contours on the blade root side for forming in each case a positive-fit pair with the profile areas. Also disclosed are a securing element and a rotor blade for this type of system, a turbomachine having a rotor which has this type of system, and a method for manufacturing this type of rotor. | 08-28-2014 |
20140286782 | TURBINE BLADE STAKING PIN - A staking pin for a gas turbine engine is disclosed. The staking pin may include a solid portion extending part of a length of the staking pin, and a hollow portion extending an additional part of the length of the staking pin. The staking pin may be constructed of Alloy X material having an average grain diameter of between about 0.0449 and 0.1270 mm. | 09-25-2014 |
20140314576 | WIND TURBINE BLADE HOLDING ARRANGEMENT - A wind turbine blade holding arrangement is described comprising a root frame for securing to a root portion of a blade; an airfoil clamp for arranging about an airfoil portion of the blade; and an airfoil frame for supporting the airfoil clamp wherein the root frame and tip clamp are realized for use in a first blade orientation in a first storage and transport stage of the blade and also for use in a second blade orientation in a second storage and transport stage of the blade, wherein the first and second blade orientations are essentially at right angles to each other. A method of handling a number of wind turbine blades is also described. | 10-23-2014 |
20140314577 | PROPELLOR BLADE RETENTION - A propeller blade retention arrangement having a propeller blade comprising in radial sequence an aerofoil portion, a shank portion and a root portion. The root portion having first cross-sectional area close to the shank portion and second cross-sectional area at the end distal to the aerofoil portion, wherein the second cross-sectional area is greater than the first cross-sectional area. At least two cheeks each having an inner surface arranged to abut the root portion, an outer surface that is threaded and edge surfaces that abut another of the at least two cheeks; wherein the at least two cheeks are arranged to surround the root portion in circumferential abutment. A collar having a threaded inner surface arranged to threadingly engage the outer surfaces of the at least two cheeks. | 10-23-2014 |
20140314578 | SECURING SEGMENT FOR THE VIBRATION DAMPING OF TURBINE BLADES AND ROTOR DEVICE - A retaining segment for axially securing at least one rotor blade on a disk wheel of a rotor device of a jet engine is operatively connectable to at least one rotor blade and to a disk wheel. In a first peripheral area of the retaining segment that is laterally disposed in the circumferential direction in the installed state, a projecting region is provided, and in a second lateral peripheral area facing away from the first peripheral area, a receiving region is provided. The projecting region at least partially overlaps a receiving region of a retaining segment that is identical in design and arranged adjacently in the circumferential direction, and for performing frictional work with the receiving region. A rotor device has rotor blades arranged via blade roots substantially in the axial direction inside recesses of a disk wheel and secured by several such retaining segments. | 10-23-2014 |
20140356177 | TURBINE SEGMENTED COVER PLATE RETENTION METHOD - An improved gas turbine cover plate assembly is disclosed for use in connection with segmented cover plates in turbine configurations where it is not possible to stagger the blades to create assembly clearance. The improved turbine assembly also avoids cover plate loading slots in the disc which can cause high stress features. The improved system also includes a method to axially retain segmented cover plates in relation to a turbine disc using a segmented retainer ring. | 12-04-2014 |
20140356178 | BLADE OF A TURBINE - The present invention relates to a blade of turbine having an aerofoil, a platform and a root portion configured to be slidingly received in mounting slots of a rotor disc. The blade further includes a locking member disposed on the root portion and engaged with the rotor disc to make axial fixation of the blade to the rotor disc. With the technical solution of the present invention, it provides a blade with simple and cost effective axial locking system to make axial fixation of the blade relative to the rotor disc, and also a fail-safe solution during assembly process. | 12-04-2014 |
20140377074 | FAN BLADE AND ATTACHING MEANS THEREFOR - In order to disclose attaching means ( | 12-25-2014 |
20150010404 | TURBINE OR COMPRESSOR STAGE INCLUDING AN INTERFACE PART MADE OF CERAMIC MATERIAL - A turbine or compressor stage suitable for being included in airplane turbojets. According to the invention, the stage comprises a disk ( | 01-08-2015 |
20150023796 | EXPANDING LOCK PIN FOR TURBINE SIDE ENTRY BLADE - An expanding lock pin for side entry turbine blades for turbines, including steam turbines compensates for worn or oversize mating pin grooves formed in rotor steeples and blade roots. The expanding pin expands circumferentially to fill the oversize mating groove. In one embodiment of the expanding lock pin a tapered plug mates with a mating tapered aperture formed in the pin. As the plug is driven into the pin its circumference increases. The expanding lock pin eliminates the need to re-machine worn or oversize pin grooves or machine new grooves. | 01-22-2015 |
20150030456 | IMPELLER FOR A ROTOR OF A TURBOMACHINE, AND ROTOR AND TURBOMACHINE HAVING AN IMPELLER OF SAID TYPE - An impeller for a rotor of a turbomachine includes: a wheel disc mounted on the rotor, the wheel disc having plural grooves arranged along a circumference of the wheel disc and extending in the thickness direction of the wheel disc. A toothed profile is formed on two sides of each groove. A plurality of impeller blades each have one root with two sides on each of which one toothed profile is formed. Each blade is inserted into a groove so as to form a blade-groove combination with the toothed profiles of the root and of the groove in engagement. Each combination having a fixing device that fixes the blade in the groove in the thickness direction and in the radial direction of the wheel disc. Each fixing device has a recess movably received in the groove base. | 01-29-2015 |
20150037162 | MECHANICAL JOINING USING ADDITIVE MANUFACTURING PROCESS - A method of manufacturing an assembly ( | 02-05-2015 |
20150044054 | COMPOSITE RETENTION FEATURE - A retention feature for use in a gas turbine engine is disclosed herein. The retention feature includes a ceramic post, an insert, and a braze layer coupling the insert to the ceramic post. The ceramic post includes a body adapted to be coupled to a turbine engine component and a head coupled to the body. The insert is arranged in a space formed in the head and the braze layer extends from the ceramic post to the insert to bond the insert to the ceramic post. | 02-12-2015 |
20150071785 | TURBINE BLADE AND NON-INTEGRAL PLATFORM WITH PIN ATTACHMENT - Platforms ( | 03-12-2015 |
20150078907 | TURBOMACHINE INCLUDING A NON-DESTRUCTIVE FASTENER ELEMENT FOR JOINING COMPONENTS - A turbomachine includes a first component including a first surface and a second surface spaced from the first surface by a gap. One of the first and second surfaces includes a non-destructive fastener element receiving opening and a wire retention feature. A second component extends into the gap between the first and second surfaces. A non-destructive fastener element is detachably mounted to the first component. The non-destructive fastener element includes a post member and a wire member operatively connected to the post member. The post member extends into the non-destructive fastener element receiving opening preventing removal of the second component and the wire member engages with the wire retention feature to secure the non-destructive fastener element to the first component. | 03-19-2015 |
20150086374 | PROPELLER ASSEMBLY AND PROPELLER BLADE RETENTION ASSEMBLY - A propeller assembly having a hub having at least one receiver opening, a receiver located within the receiver opening and having a first collar defining a blade opening, a blade having a second collar and a protrusion with the second collar abutting the first collar and the protrusion received within the blade opening, and a first retainer, and a second retainer. | 03-26-2015 |
20150086375 | CEILING FAN - A ceiling fan includes blade ( | 03-26-2015 |
20150093248 | RETAINER PLATE - A retainer plate is provided for retaining a dovetail root of a fan blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a fan disc. In use, the plate locates in a cavity formed at an end of the slot such that a first side of the plate is arranged for contact with an axial end face of the dovetail root and an opposite second side of the plate is arranged for contact with an abutment surface of the cavity to limit axial movement of the root along the slot. The retainer plate is a unitary component and has a layered structure including a first layer at the first side of the plate, a second layer at the second side of the plate, and an intermediate layer between the first and the second layers. | 04-02-2015 |
20150104320 | TURBINE WITH BUCKET FIXING MEANS - There is provided a turbine including a rotor wheel including a plurality of dovetail grooves and at least one insertion groove, the dovetail grooves and the insertion groove arranged in a circumferential direction of the rotor wheel; a plurality of first buckets, each of the first buckets including a vane, a platform provided at a first end portion of the vane, and a dovetail provided at the platform and having a shape corresponding to a corresponding dovetail groove; at least one second bucket including a vane, a platform provided at a first end portion of the vane, and at least one protrusion portion provided at the platform and configured to be inserted into a corresponding insertion groove of the insertion groove; and a fixing member configured to be inserted through the protrusion portion and the rotor wheel and configured to restrict radial movement of the second bucket. | 04-16-2015 |
20150110634 | RETAINER PLATE - A retainer plate is provided for retaining a dovetail root of a fan blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a fan disc. In use, the plate locates in a cavity formed at an end of the slot such that a first side of the plate is arranged for contact with an axial end face of the dovetail root and an opposite second side of the plate is arranged for contact with an abutment surface of the cavity to limit axial movement of the root along the slot. The retainer plate is formed from fibre-reinforced composite material, at least a portion of the composite material being reinforced by 3D-woven fibre tows. | 04-23-2015 |
20150118056 | ROTOR TURNING SYSTEM AND METHOD - A rotor turning system includes a fixture plate configured for attachment to a gearbox, a locking mechanism configured for attachment to the fixture plate, and a reaction fixture configured for attachment to the locking mechanism. The rotor turning system is configured to permit rotation of the rotor only when rotational torque is applied to the locking mechanism, and this rotation is in only one rotational direction. | 04-30-2015 |
20150361813 | ROTOR ASSEMBLY FOR GAS TURBINE - The present invention relates to a rotor assembly for a rotary machine such as a gas turbine. The present solution provides a sealing wire located inside a groove engraved in the rotor body. The sealing wire is responsive to radial centrifugal forces acting during normal operation of the machine, and moves radially in the groove until a sealing configuration is achieved such to prevent damaging hot leakage towards machine components. | 12-17-2015 |
20150369057 | DAMPER MASS DISTRIBUTION TO PREVENT DAMPER ROTATION - A damper seal for a gas turbine engine rotor assembly has an axially elongated body with a leading edge, a trailing edge, a pressure side, and a suction side. The elongated body includes a first enlarged portion formed on the pressure side at the leading edge and a second enlarged portion formed on the suction side adjacent the trailing edge. | 12-24-2015 |
20150369063 | BLADE WHEEL AND METHOD FOR PRODUCING A BLADE THEREFOR - A turbine blade wheel includes a wheel disk with a disk element ( | 12-24-2015 |
20160040542 | COVER PLATE FOR A ROTOR ASSEMBLY OF A GAS TURBINE ENGINE - A cover plate according to an exemplary aspect of the present disclosure includes, among other things, a body, a first tab near a bore of the body, and a second tab circumferentially spaced from the first tab. A slot is defined between the first tab and the second tab, the first tab, the second tab and the slot extending at an angle relative to a slot axis that extends through the bore. In another embodiment, the cover plate includes a bumper that limits deflection of the body. | 02-11-2016 |
20160090854 | BLADED ROTOR ARRANGEMENT - A bladed rotor arrangement comprising a rotor, a plurality of rotor blades, at least one seal plate and a plurality of lock plates. Each rotor blade locates in a corresponding axially extending slot in the rotor. A plurality of lock plates are arranged at a first axial end of the rotor, the radially outer ends of the lock plates engage grooves on the platforms of the rotor blades, and the radially inner ends of the lock plates engage a circumferentially extending groove. The seal plate is arranged at the first axial end of the rotor, the radially inner ends of the lock plates engage the circumferentially extending groove defined by the seal plate. The seal plate has at least one projection extending axially from the seal plate and arranged to locate in a slot in a first axial end of the root of a rotor blade. | 03-31-2016 |
20160097287 | FAN - Fan for gas turbine engine includes hub and annular array of fan blades mounted to hub and extending radially outwardly from hub, each fan blade includes blade root. The hub includes plurality of hub grooves having shape complimentary to shape of blade root and each hub groove receives and radially retains one blade root. A slot is provided on the suction side and on the pressure side of each blade root. Plurality of keys is provided, each key engages with slots in one blade root and with corresponding hub groove so as to axially retain fan blade. The key includes two arms and joining member, two arms are received in slots provided on blade root and joining member extends between the arms. Interface is defined between key arms and slots in blade root, and greater or equal percentage of interface is curved than is planar. | 04-07-2016 |
20160097289 | SLIDER - A slider for chocking a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc. The slider, in use, is slidingly inserted in an axially-extending cavity formed in the base of the root and in the disc at the base of the slot to urge the blade radially outwardly and thereby mate flanks of the root to flanks of the slot. The slider is arc-shaped and the cavity is correspondingly arc-shaped. The normal to the plane of the arc of the arc-shaped cavity is substantially perpendicular to the engine axis such that, when inserted in the cavity, the slider also retains the root axially in the slot. | 04-07-2016 |
20160138406 | COMPOSITE COMPONENTS FOR GAS TURBINE ENGINES - A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed as a composite structure including a number of plies of ceramic-containing material. The blades each include a root to fit within dovetail slots of the rotor disk to couple the blades to the rotor disk. | 05-19-2016 |
20160177748 | TURBINE WHEEL WITH COMPOSITE BLADED RING | 06-23-2016 |
20160177750 | ARRANGEMENT OF A ROTOR AND AT LEAST A BLADE | 06-23-2016 |
20160186573 | Radial Lock for Fan Blade Sheath - A turbojet fan blade adapted for securement to an engine rotor includes a titanium sheath that extends continuously over its leading edge from blade tip to blade root. The sheath provides impact protection over the leading edge of the blade, and also incorporates enhanced radial securement of the sheath to the rotor. As such, a radial lock system for the sheath is disclosed that includes a fully integrated sheath portion that extends completely over the frontal face of a fan blade dovetail, providing a radial lock of the sheath to the rotor in the event of failure of any adhesive used to attach the sheath to the leading edge. Because the sheath extends continuously from blade tip to the blade root, lightning strike protection is enhanced by avoidance of any discontinuities otherwise associated with related art sheaths that typically extend over only a flow path portion of the leading edge. | 06-30-2016 |
20160201483 | TURBINE WHEEL WITH CLAMPED BLADE ATTACHMENT | 07-14-2016 |
20160201484 | TURBINE WHEEL WITH CLAMPED BLADE ATTACHMENT | 07-14-2016 |
20160252103 | FAN ROTOR WITH INTEGRATED PLATFORM ATTACHMENT | 09-01-2016 |
20180023394 | ROTOR WITH A LOCKING PLATE FOR SECURING AN ANTIROTATION LOCK AGAINST UNSCREWING | 01-25-2018 |
20180023401 | WHEEL DISK ASSEMBLY HAVING SIMPLIFIED SEALING-PLATE MOUNTING | 01-25-2018 |
20120087797 | ROTOR BLADE WITH CONTROL TUBE - A system comprising a rotor blade ( | 04-12-2012 |
20120134835 | CONNECTION MEANS - A connection means ( | 05-31-2012 |
20130164139 | FAN WITH REPLACABLE VANES - A fan includes a frame, a rotor rotatably mounted in the frame, and a vane. The rotor includes a slot defined in the circumference of the rotor. The slot extends through an end surface of the rotor. The vane forms an installing portion to be inserted into the slot through the end surface. A first base and a second base are formed on the end surface at opposite sides of the slot. A blocking member is pivotably mounted to the first base with a first end, and is detachably engaged with the second base with a second end, to fix the installing portion in the slot. | 06-27-2013 |
20190145424 | FAN WITH ENGAGEMENT STRUCTURE | 05-16-2019 |