| Entries |
| Document | Title | Date |
|---|
| 20080206060 | Forming firtree profiles - A firtree profile, for example on a component of a gas turbine engine, is formed in a two-stage process. In one stage, an intermediate profile is formed, for example by a mechanical machining operation such as grinding. Subsequently, in a second stage, loaded flanks | 08-28-2008 |
| 20080226457 | TURBOMACHINE ROTOR DISK - A turbomachine rotor disk ( | 09-18-2008 |
| 20080232969 | ROTARY ASSEMBLY FOR A TURBOMACHINE FAN - A rotary assembly for a turbomachine fan comprises: a disk rotatable about an axis; a plurality of blades fastened by their roots to said disk and extending radially outwards from said disk; and a plurality of inter-blade platforms, each extending between two adjacent blades and defining the inner profile for the flow section of the fluid passing through the fan. On their facing side faces, these adjacent blades present slides between which said platform can slide, these slides limiting outward radial movement of said platform. | 09-25-2008 |
| 20080260534 | BLADE/DISK DOVETAIL BACKCUT FOR BLADE/DISK STRESS REDUCTION (7FA+E, STAGE 1) - Blade load path on a gas turbine disk can be diverted to provide a significant disk fatigue life benefit. A plurality of gas turbine blades are attachable to a gas turbine disk, where each of the gas turbine blades includes a blade dovetail engageable in a correspondingly-shaped dovetail slot in the gas turbine disk. In order to reduce gas turbine disk stress, an optimal material removal area is defined according to blade and/or disk geometry to maximize a balance between stress reduction on the gas turbine disk, a useful life of the gas turbine blade, and maintaining or improving the aeromechanical behavior of the gas turbine blade. Removing material from the material removal area effects the maximized balance. | 10-23-2008 |
| 20080260535 | BLADE/DISK DOVETAIL BACKCUT FOR BLADE/DISK STRESS REDUCTION (6FA+E, STAGE2) - Blade load path on a gas turbine disk can be diverted to provide a significant disk fatigue life benefit. A plurality of gas turbine blades are attachable to a gas turbine disk, where each of the gas turbine blades includes a blade dovetail engageable in a correspondingly-shaped dovetail slot in the gas turbine disk. In order to reduce gas turbine disk stress, an optimal material removal area is defined according to blade and/or disk geometry to maximize a balance between stress reduction on the gas turbine disk, a useful life of the gas turbine blade, and maintaining or improving the aeromechanical behavior of the gas turbine blade. Removing material from the material removal area effects the maximized balance. | 10-23-2008 |
| 20080273981 | Windmill - A windmill, characterized by connecting blade root parts to a hub in the radial direction of a windmill shaft by an undercut, fitting structure which is suitable particularly for a small-sized windmill having FRP blades. By this structure, the blades can be connected to the hub at the blade root parts without basically requiring a bolt fastening structure, a reduction in the weight of the blades can be achieved, and the strength, rigidity and installation accuracy of connection parts between the blades and the hub can be satisfactorily maintained. | 11-06-2008 |
| 20080298972 | ROTOR DISK FOR TURBOMACHINE FAN - A rotor disk ( | 12-04-2008 |
| 20090004017 | SPACER INTERPOSED BETWEEN A BLADE ROOT AND THE BOTTOM OF A SLOT IN THE DISK IN WHICH THE BLADE IS MOUNTED - Wedging blades attached to the disk of a rotor having slots. According to the invention, each wedging spacer is made of an elastically deformable material and at least one longitudinal segment of the spacer presents a transverse profile of arcuate shape to define two lateral contact zones. | 01-01-2009 |
| 20090004018 | DEVICE FOR AXIALLY RETAINING BLADES MOUNTED ON A TURBOMACHINE ROTOR DISK - The invention relates to a device for axially retaining blades mounted on a turbomachine rotor disk, the device comprising a rotor disk having a plurality of slots and a flange extending radially outwards, cooperating with a bearing face of the disk to define a groove that is open radially outwards. The device also comprises a plurality of blades, each having a root mounted in a slot of the disk, each blade root having a respective radial bearing face that corresponds to the bearing face of the disk and that has at least one nib extending radially inwards thereover to define a notch that is open radially inwards, and a retaining ring that is mounted against the bearing faces of the disk and of the blade roots, said retaining ring being housed in the groove of the disk, being held outwardly in the notches of the blade roots, and being constituted by a plurality of angular segments placed end to end. | 01-01-2009 |
| 20090016890 | TURBOMACHINE ROTOR ASSEMBLY - A turbomachine rotor assembly comprising: a rotor disk ( | 01-15-2009 |
| 20090022591 | STEAM TURBINE AND ROTATING BLADE - A blade mountable to a disc comprises a blade platform and a blade root extending from the blade platform. The blade root comprises first, second, and third hooks and first, second and third necks. Each hook comprises a contact surface and a non-contact surface, and an angle between each contact surface and each non-contact surface is optimized to reduce local and average stresses. | 01-22-2009 |
| 20090060745 | SHIM FOR A TURBOMACHINE BLADE | 03-05-2009 |
| 20090068017 | WIND TURBINE BLADE - Apparatus and methods related to wind turbine blades and manufacturing of the blades. | 03-12-2009 |
| 20090081046 | SHIM FOR A TURBOMACHINE BLADE - Shim for a turbomachine blade, for covering the root of said blade, the shim comprising: two branches for covering the bearing surfaces of the blade root; a base interconnecting these branches; and at least one holder element located at one end of the shim and suitable for coming into contact with the blade root to retain the shim relative to the blade root, the shim further comprising, at its other end, at least one foolproofing element projecting from the base in the opposite direction to the branches. A turbomachine rotor assembly including such a shim. | 03-26-2009 |
| 20090087316 | ROTOR BLADE, METHOD FOR PRODUCING A ROTOR BLADE, AND COMPRESSOR WITH A ROTOR BLADE - A rotor blade for fastening on the rotor of a turbomachine, especially of a compressor of a gas turbine, has a blade airfoil and a blade root ( | 04-02-2009 |
| 20090092496 | AXIAL FLOW HYDRAULIC TURBINE WITH BLADE MOUNTING - A hydraulic turbine has a runner blade fixedly mounted to a runner hub. The runner blade has a mounting flange having a generally rectangular shape held in contact with a complementary generally rectangular shaped outside surface portion of the runner hub. The complementary rectangular shapes increases surface contact area between the blade mounting flange and the hub over that of circular shaped flanges and thereby reduces the stress levels between the blade flange and the hub. Further, the surface contact area between the blade mounting flange and the blade root is increased to thereby reduce the stress level in the blade root fillets. | 04-09-2009 |
| 20090104038 | Airfoil Family for a Blade of a Wind Turbine - A wind turbine rotor blade comprising a series of profiles is presented, which series of profiles comprises a number of profiles describing the outline of the blade transversally of its longitudinal axis, wherein some of the profiles of the series of profiles comprise approximately the same profile rear edge which describes at least a portion of the rear edge of the blade. The rear edge of the blade is configured in one piece and/or of a flexible material. Moreover a method of designing a series of profiles for a wind turbine rotor blade is presented. | 04-23-2009 |
| 20090123288 | METAL IMPELLER BLADE MANUFACTURED BY MOLDING AND METHOD OF MANUFACTURING THE IMPELLER BLADE - The present invention relates to an impeller blade for turbomachine formed by molding, comprising a blade, at one end of which is provided a heel formed of a single piece with the blade, to which it is joined at the level of a connection area, the heel comprising a platform on which is provided at least one sealing plate, a first bath being provided in the platform, characterized in that a second bath is provided in the first bath, at the level of the connection area between the blade and the heel. | 05-14-2009 |
| 20090129932 | DOVETAIL ATTACHMENT FOR USE WITH TURBINE ASSEMBLIES AND METHODS OF ASSEMBLING TURBINE ASSEMBLIES - A method of assembling a steam turbine including a rotor assembly is provided. The method includes providing at least one turbine bucket including a dovetail that includes a plurality of crush surfaces, a plurality of non-contact surfaces, and at least one neck defined between one of the crush surfaces and one of the non-contact surfaces. The method also includes providing a turbine wheel that includes at least one dovetail slot defined therein that is defined by a plurality of crush surfaces and a plurality of non-contact surfaces, and coupling the dovetail of the at least one turbine bucket within the turbine wheel slot such that a slant angle of the at least one neck facilitates a substantially uniform distribution of load between the dovetail and the at least one slot. | 05-21-2009 |
| 20090136349 | DEVICE FOR BLOCKING A RING FOR AXIALLY RETAINING A BLADE, ASSOCIATED ROTOR DISK AND RETAINING RING, AND ROTOR AND AIRCRAFT ENGINE COMPRISING THEM - A device for rotationally blocking a retaining ring on a rotor disk three successive blocking hooks of the disk ( | 05-28-2009 |
| 20090136350 | Damping and sealing system for turbine blades - With a gas-turbine engine, a sealing and damping element ( | 05-28-2009 |
| 20090136351 | Tail Rotor Hub - A tail rotor hub system and methods are disclosed. In one embodiment, the system includes a helicopter fuselage connected to a tail rotor assembly that holds tail blades. The assembly includes an elongated tail rotor housing and an elongated blade root fitting that rotates within the housing. A tension torsion strap is connected at one end to the housing and is connected at its other end to the blade root fitting to hold the blade root fitting in the housing when the housing rotates. Coupled between outside walls of the blade root fitting and inside walls of the housing are self lubricating bearings to enable the blade root fitting to rotate within the housing to change the pitch of the tail blades. | 05-28-2009 |
| 20090148297 | FAN-TURBINE ROTOR ASSEMBLY FOR A TIP TURBINE ENGINE - A fan-turbine rotor assembly ( | 06-11-2009 |
| 20090148298 | BLADE DISK SEAL - An apparatus and method are disclosed for reducing the operating stresses in a disk of a gas turbine engine while providing a seal plate to minimize leakage of a cooling fluid from the blades positioned in the disk. The seal plate is fastened to a tang of one or more of the blades. The seal plate configuration can be utilized with a newly manufactured disk and blades or with a modification to an existing disk and blades. The disk, blade, and seal plate configuration reduce operating stresses in the disk that are caused by mechanical loading on the disk by one or more rotating blades. | 06-11-2009 |
| 20090155081 | COMBINATION AXIAL-FLOW FAN - A high-performance low-noise combination axial-flow fan includes a fan hub that has a center connection portion for the connection of a fan motor shaft and a plurality of mounting grooves equiangularly spaced around the periphery, and fan blades each having a wedge block disposed at the inner end for insertion into one mounting groove to secure the respective fan blade to the fan hub so that the fan blades are radially fastened to the fan hub and no gap is seen between each two adjacent fan blades when viewed from the front side. | 06-18-2009 |
| 20090162205 | TURBINE COMPONENTS AND METHODS OF MANUFACTURING TURBINE COMPONENTS - Turbine components are provided. In an embodiment, by way of example, a hub and a ring are included. The hub comprises a first material. The ring is bonded to the hub. The ring comprises a plurality of arc segments forming a ring, each arc segment comprising a second material comprising a single crystal superalloy material having a predetermined primary orientation and a predetermined secondary orientation, each predetermined primary orientation of each arc segment being substantially equal, and each predetermined secondary orientation of each arc segment being substantially equal, each arc segment adjacent another arc segment, and the adjacent arc segments having a predetermined crystallographic mismatch therebetween. Methods of manufacturing are also provided. | 06-25-2009 |
| 20090208339 | BLADE ROOT STRESS RELIEF - In a gas turbine engine, a stress relief is formed along a blade root and disk slot junction. An exemplary relief is a chamfer along the pressure side of the blade root extending forward from the aft face of the root. | 08-20-2009 |
| 20090214350 | ROTOR OF A TURBOMACHINE AND METHOD FOR REPLACING ROTOR BLADES OF THE ROTOR - A rotor of a turbomachine is provided. The rotor includes at least first and second rotor portions and at least first and second blades. The first and second rotor portions are configured to rotate about an axis. The first and second rotor portions have first and second rim portions, respectively, which are spaced a predetermined distance apart from one another and have a perimetrical slot therebetween. The first and second rim portions have first and second dovetail slots, respectively, extending therethrough communicating with the perimetrical slot. The first and second blades have first and second dovetail portions, respectively. The first dovetail portion is disposed in one of the first and second dovetail slots, and the second dovetail portion is disposed in the other of the first and second dovetail slots. The perimetrical slot has a sufficient size to pass the first and second blades therethrough when the first and second blades are removed from the rotor. | 08-27-2009 |
| 20090214351 | METHOD OF GENERATING A CURVED BLADE RETENTION SLOT IN A TURBINE DISK - A method of forming a curved slot in a turbine disk includes the steps of forming a pre-slot in the turbine disk and finishing the pre-slot to form a slot that receives a portion of a turbine blade. The turbine disk including a first face, an opposing second face, and an outer perimeter surface extending between the first face and the opposing second face. The pre-slot includes a first curved wall and a second curved wall that each extend between the first face and the opposing second face. An intersection between the outer perimeter surface and each of the first curved wall and the second curved wall is defined by a curved line. | 08-27-2009 |
| 20090246030 | IMPELLER - To provide a can manufacturing pump impeller in which a stress of a base portion of a blade is prevented from increasing while improving the strength of a joint portion of a hub and a boss. In order to reinforce a joint portion of a hub and a boss, a plate is jointed to the inside of an impeller. In order not to overlap a base portion of a blade and the plate with each other on the hub, an opening portion is provided in the plate around the base portion of the blade on the hub. As a shape of the opening portion, a semicircular shape, a semielliptical shape, a rectangular shape, or a trapezoidal shape can be selected. Further, as a plate shape, a flat plate structure, a shell structure, or a curved structure can be selected. | 10-01-2009 |
| 20090257877 | ASYMMETRICAL ROTOR BLADE FIR-TREE ATTACHMENT - A rotor blade for a gas turbine engine includes an asymmetric attachment section received within a rotor disk rim with an asymmetric slot. | 10-15-2009 |
| 20090285690 | AXIAL BLADE SLOT PRESSURE FACE WITH UNDERCUT - A blade and disk assembly includes a blade body and a disk body having a slot to receive the blade body. The blade body has a blade bearing surface. The slot has a disk bearing surface that contacts the blade bearing surface at a bearing interface. The slot has an undercut surface that is spaced apart from the blade body. An angle between the disk bearing surface and a line tangent to the undercut surface is at least 70 degrees. | 11-19-2009 |
| 20090297351 | COMPRESSOR ROTOR BLADE UNDERCUT - A rotor blade for an axial compressor that may include an airfoil, which includes a leading edge, and a root, which includes a platform, the platform being the outer radial face of the root from which the airfoil extends, and a dovetail, the dovetail including a dovetail leading-face, which is the face of the dovetail that generally points up-stream once the rotor blade is installed in the axial compressor. The rotor blade may include an undercut groove that is formed on the dovetail leading-face that undercuts at least partially the intersection of the leading edge of the airfoil and the platform. | 12-03-2009 |
| 20090324413 | FAN BLADE - The present invention relates to a fan blade for axial fans with a blade body comprising an inner inlaid part and an outer blade shaped part partially enclosing said inner inlaid part. The outer blade is made of a material of lower rigidity than the inlaid part. The inlaid part is constructed as a substantially flat metal part adapted to the shape of the blade body and in the fan blade base region has an unencapsulated smooth fixing section. | 12-31-2009 |
| 20100008782 | Compliant Seal for Rotor Slot - A compliant seal assembly for sealing a gap between a dovetail tab of a bucket and a slot of a rotor. The compliant sealing assembly may include a sealing groove positioned about the slot and a compliant seal positioned about the sealing groove. The compliant seal is forced into the gap and about the dovetail tab when the bucket rotates. | 01-14-2010 |
| 20100034659 | FAN ROTOR BLADE SUPPORT STRUCTURE AND TURBOFAN ENGINE HAVING THE SAME - The fan rotor blade ( | 02-11-2010 |
| 20100040474 | FIXING DEVICE FOR ROTARY BLADE - A fixing device for fixing a rotary blade to a spindle in a bench circular saw, for example, has a structure in which it is difficult to achieve structural compactification in radial size. Therefore, there has been a problem of sacrificing an inclination angle and a cutting depth of the rotary blade. Provided is a fixing device free from such problems owing to employment of a structure which can be easily compactified in a radial direction. Cam portions are provided on respective surfaces opposite to each other of an intermediate flange and an outer flange so as to mesh with each other. The cam portions slide with each other with a rotational force imparted to the rotary blade so that the rotational force is converted into a displacement in a direction of an axis of the intermediate flange and is applied in a direction of clamping the rotary blade. | 02-18-2010 |
| 20100061859 | DOVETAIL FOR STEAM TURBINE ROTATING BLADE AND ROTOR WHEEL - A dovetail for a steam turbine rotating blade and rotor wheel is provided. The dovetail design comprises a rotating blade curved axial entry dovetail having a four hook profile and a rotor wheel dovetail slot sized to receive the blade dovetail. The blade dovetail and wheel dovetail slot each comprise a plurality of slanted crush surfaces, a plurality of non-contact surfaces, and a plurality of necks that each provide a transition between a slanted crush surface to a non-contact surface. Each neck comprises a slant angle defined by the transition of the slanted crush surface to the non-contact surface. The slant angle ranges from about 60 degrees to about 82 degrees. | 03-11-2010 |
| 20100068062 | Turbine bucket with dovetail seal and related method - A method of sealing gaps between a bucket dovetail and a rotor disk dovetail slot in which the bucket dovetail is adapted to be received, the method comprising applying a resin material to selected areas of the bucket dovetail; and inserting the bucket dovetail into the dovetail slot. | 03-18-2010 |
| 20100098547 | TURBINE BLADE INCLUDING MISTAKE PROOF FEATURE - A turbine blade includes a platform, an airfoil located on one side of the platform, and a base located on an opposite side of the platform. The base includes an attachment portion that is receivable in a blade retention slot of a turbine disk and a shelf located outside the turbine disk. The shelf includes a mistake proof feature that projects from an outer surface of the shelf. | 04-22-2010 |
| 20100111699 | SPACERS AND TURBINES - Spacers and turbines are provided. In an embodiment, and by way of example only, a spacer includes a strip, a first retention flange, and a second retention flange. The strip has a first edge, a second edge, and an impingement surface, and the impingement surface extends axially along the strip between the first edge and the second edge and is substantially flat. The first retention flange is recessed relative to the impingement surface and extends away from the first edge of the strip. The second retention flange is recessed relative to the impingement surface and extends away from the second edge of the strip | 05-06-2010 |
| 20100111700 | Turbine blade including a seal pocket - A turbine blade is disclosed. The turbine blade may have an airfoil extending from a first surface of a turbine platform. The turbine blade may further have a first side pocket of the turbine platform that is configured to substantially entirely house a first moveable seal between a forward wall of the first side pocket and an aft wall of the first side pocket. The first side pocket may have a convex surface, extending between the forward wall and the aft wall, and a concave surface. The turbine blade may also have a second side pocket of the turbine platform configured to receive a portion of a second moveable seal. | 05-06-2010 |
| 20100111701 | TURBINE ROTOR BLADE AND FIXATION STRUCTURE THEREOF - Disclosed is a turbine rotor blade that is highly manufacturable and capable of reducing the stress caused by centrifugal force. The turbine rotor blade includes: a vane portion having a blade leading edge which is positioned upstream in the distribution direction of working fluid, and a blade trailing edge which is positioned downstream of the blade leading edge; and a blade base portion which is extended unidirectionally on a base side of the vane portion and engaged with a blade groove formed in the outer circumference of a turbine rotor. The turbine rotor circumferential position of the end of the blade base portion on the side toward the blade leading edge is different from the turbine rotor circumferential position of the end of the blade base portion on the side toward the blade trailing edge. | 05-06-2010 |
| 20100129226 | AXIAL RETENTION OF A PLATFORM SEAL - A gas turbine engine component having an axial pin stop assembly that reduces stress around a seal pin damper slot between a platform and a buttress is disclosed. The seal pin damper slot is extended to the leading edge of the buttress and an axial pin stop seal extends into the pin damper slot to limit movement of the seal pin damper while relieving stress concentration at the interface between the buttress and platform. | 05-27-2010 |
| 20100135811 | ROOT SLEEVE FOR WIND TURBINE BLADE - A sleeve for a wind turbine blade includes an opening for receiving a root end of the wind turbine blade; and an inboard edge for substantially abutting a hub of a wind turbine. | 06-03-2010 |
| 20100150723 | Rotor for a Compressor - According to the present invention there is provided a rotor ( | 06-17-2010 |
| 20100150724 | PLATFORM SEAL IN A TURBOMACHINE ROTOR, METHOD FOR IMPROVING THE SEAL BETWEEN A PLATFORM AND A TURBOMACHINE BLADE - An elastomer material seal for an interleaved platform between two adjacent blades in a turbomachine rotor is disclosed. The seal is of elongate shape and includes transversely a contact part, an attachment part, and a flexible part between the attachment part and the contact part. The seal is noteworthy in that it further includes a local reinforcement of the flexible part, to avoid the tearing that would result from centrifugal forces on the seal. The local reinforcement of the flexible part includes at least one transverse rib on the flexible part. | 06-17-2010 |
| 20100150725 | WHEEL FORMED FROM A BLADED RING AND DISK - A wheel is constructed from a disk disposed for rotation about an axis and a ring with a plurality of blades being connectable to the disk. The wheel is operable for pumping, compressing, or expanding fluid in a turbomachine. The disk is configured to receive at least a portion of the ring within the disk and be coupled using a protrusion or protrusions. The protrusion can be configured to prevent relative movement between the disk and the ring. In some forms a bracket can be extended between the ring and disk to prevent relative movement. | 06-17-2010 |
| 20100166561 | TURBINE BLADE ROOT CONFIGURATIONS - A rotor blade for use in a turbine engine, the rotor blade comprising a root and, extending in a radial direction from the root, an airfoil, wherein the root includes at least one root aligned surface that is tilted. Tilted may comprises a non-radial orientation. The root aligned surfaces may comprise the surfaces along the root that are configured to align with and be relatively closely spaced from or in contact with the root aligned surfaces of the root of a neighboring rotor blade. The rotor blade may comprise at least two root aligned surfaces, one of which resides on a pressure side of the rotor blade and the other of which resides on a suction side of the rotor blade. All of the root aligned surfaces may be tilted. | 07-01-2010 |
| 20100166562 | TURBINE BLADE ROOT CONFIGURATIONS - A rotor blade for a turbine engine comprising a root and, extending in a radial direction from the root, an airfoil, wherein: the root comprises a shank and a dovetail; the shank extends from the dovetail and comprises a platform at an radial outward surface; the dovetail includes one or more tangs; the platform comprises an axially and circumferentially oriented surface that defines, at least in part, the inner most radial boundary of the flow path through the turbine; the dovetail is linear; and the platform is curved. | 07-01-2010 |
| 20100166563 | METHOD FOR IMPROVING THE SEALING ON ROTOR ARRANGEMENTS - A method is described for improving the sealing between rotor and a plurality of blades. The rotor has a plurality of generally axially extending profiled recesses into which a ring of blades, which have corresponding blade root profiles, are inserted in a form-fitting and/or frictionally locking manner into these recesses in a generally axial insertion direction. Between the recesses the rotor has tangential surface sections or circumferential surface sections which extend in the axial direction and circumferential direction and are generally indirectly covered by lower shrouds of circumferentially adjacently arranged blades in the radial direction. At least one of the tangential surface or circumferential surface sections is provided with a step in the radial direction, and a corresponding recess, which adjoins as flush as possible, is provided in the underside of the shroud of the blade which is arranged above it. Corresponding rotors or blades are also described. | 07-01-2010 |
| 20100189562 | COMPOSITE MATERIAL TURBOMACHINE BLADE WITH A REINFORCED ROOT - The invention relates to a turbomachine blade made of composite material including fiber reinforcement, the blade being obtained by three-dimensionally weaving yarns and densifying with a matrix. The blade comprises a single piece constituting both the airfoil and the root of the blade. The blade root has two substantially plane opposite side flanks that are formed in register with the pressure side and suction side surfaces respectively of the airfoil and it is clamped between two metal plates that are fastened against the side flanks of the root. | 07-29-2010 |
| 20100189563 | PROPELLER FOR VESSELS - The present invention refers to a fixed pitch type propeller for vessels, fitted with exchangeable blades and having a central core unit that can be coupled to the transmission receiving the movement from the corresponding engine, and a plurality of blades that surround it in an equiangular distribution and are affixed to the central core; said core ( | 07-29-2010 |
| 20100209253 | FAN BLADE ANTI-FRETTING INSERT - A fan blade anti-fretting insert is described whereby to reduce wear between the root portion of a fan blade and the root slot of the rotor fan hub of a turbo fan engine to which the fan blade are secured. The anti-fretting insert can be formed of a composite spring material having a memory and is dimensioned and shaped to be fitted between the fan blade platform and the outer surface portion of the rotor fan hub between adjacent fan blades, whereby to apply a pushing force against the platform and consequently to the fan blades secure thereto thereby applying a resulting pulling force on the root portion of the fan blades to prevent rocking of the root portion in their root slots formed in the rotor fan hub. | 08-19-2010 |
| 20100209254 | VANE FOR AIRCRAFT TURBINE ENGINE RECEIVER, PROVIDED WITH TWO HOLLOW CORES LODGED IN ONE ANOTHER - The invention relates to a vane ( | 08-19-2010 |
| 20100239424 | SPLIT DISK ASSEMBLY FOR A GAS TURBINE ENGINE - A split disk assembly for a gas turbine engine includes a forward disk section and an aft disk section, the aft disk section engageable with the forward disk section to retain a multitude of rotor blades therebetween. | 09-23-2010 |
| 20100247317 | TURBOMACHINE ROTOR ASSEMBLY AND METHOD - Disclosed is a rotor assembly for a turbomachine includes a disk having a first axial face and a second axial face. The disk includes at least one circumferential dovetail extending around an outer surface of the disk and a plurality of axial dovetails extending from the first axial face to the second axial face. Each blade of a plurality of blades is installed into an axial dovetail of the plurality of axial dovetails and each platform of a plurality of platforms is installed adjacent to a blade of the plurality of blades via the at least one circumferential dovetail. Further disclosed is a method of assembly of a rotor for a turbomachine. | 09-30-2010 |
| 20100290913 | REINFORCED COMPOSITE FAN BLADE - A fan blade for a turbine engine includes an exterior surface defining an airfoil that is provided by leading and trailing edges, opposing generally chord-wise surfaces interconnecting the leading and trailing edges, and a tip. The airfoil extends from a root. A fan rotor includes a slot that receives the root. A spar is constructed from a first material and includes opposing sides. The spar provides at least a portion of the exterior surface. A sheath is constructed from a second material different than the first material. The sheath is arranged on both of the opposing sides to provide at least a portion of the exterior surface at the opposing surfaces. | 11-18-2010 |
| 20100296937 | BALANCED ROTOR FOR A TURBINE ENGINE - A balanced rotor of a turbine engine, having a rotor disc with a circumferential slot and a row of rotor blades mounted in the slot and a balance weight having a land which extends beneath the root of a blade and having a mass-adjustment protrusion extending from the land in a radial direction relative to the axis of the rotor component and which lies wholly between the blade root and an adjacent blade root. | 11-25-2010 |
| 20100329872 | METHOD AND APPARATUS FOR ASSEMBLING ROTATING MACHINES - A method for assembling a rotating machine includes providing a rotating element. The method also includes forming a first dovetail slot having a first axial length within a portion of a rotating element. The first dovetail slot is substantially parallel to an axial centerline of the rotating element. The method further includes forming a second dovetail slot having a second axial length within a portion of the rotating element. The second dovetail slot is substantially parallel to the axial centerline of the rotating element. At least a portion of the second dovetail slot is radially outboard of at least a portion of the first dovetail slot. The first axial length is greater than the second axial length. The method also includes enclosing at least a portion of the rotating element within at least a portion of a casing. | 12-30-2010 |
| 20110008172 | PROCESS AND APPARATUS FOR PROVIDING FIRTREE SLOTS - A process for forming a firtree slot in a disc of a bladed rotor assembly for a gas turbine engine may include making a first pass with a machining quill to form a rough profile of the firtree slot, making a second pass with an inclined machining quill having the shape of one of the finished side wall profile of the firtree slot and avoiding engagement with the other side, and making a third pass with an inclined second quill having the shape of the other of the finished side wall profile of the firtree slot and avoiding engagement with the other side, in order to provide a firtree slot for receiving and fixing the root of a blade. | 01-13-2011 |
| 20110027091 | Axial-flow compressor, more particularly one for an aircraft gas-turbine engine - On an axial-flow compressor, more particularly one for an aircraft gas-turbine engine, including at least one rotor disposed in a casing and having compressor blades extending from a rotor hub as well as one stator, a slot-type recess ( | 02-03-2011 |
| 20110033302 | FAN BLADE DOVETAIL WITH COMPLIANT LAYER - A fan blade includes an airfoil and a dovetail at a radially inner end of the airfoil. The dovetail extends between first and second axial ends, and has outer circumferential faces. The dovetail is formed of relatively rigid composite material. Compliant material is placed on each outer circumferential face of the dovetail. The compliant material is less rigid than the composite material for forming the dovetail. In a second embodiment, the compliant layer may be positioned within the disk slots in a disk, such that the compliant layer will come in contact with circumferentially outer faces of the dovetail. | 02-10-2011 |
| 20110052398 | FAN ASSEMBLY - A fan assembly is disclosed herein. The fan assembly includes a fan operable to rotate about an axis. The fan includes a hub and a plurality of blades extending radially from the hub relative to the axis. The fan also includes a reinforcing member positioned adjacent to the fan along the axis. The reinforcing member contacts a predetermined subset of less than all of the plurality of blades. | 03-03-2011 |
| 20110070089 | GUIDE VANE FOR A GAS TURBINE - A stator blade for a gas turbine includes a blade airfoil extending in a longitudinal direction of the blade and is delimited by leading and trailing edges. The stator blade includes a shroud, whose inner side is exposed to hot gas which flows through the gas turbine. A hook-like fastening element for fastening the stator blade on a casing of the gas turbine projects outwards in the region of the trailing edge. The fastening element has a locating slot above the trailing edge for fixing a heat shield, which is connected to the shroud in the flow direction of the hot gas. A cavity is provided on the shroud between the locating slot for the heat shield and the trailing edge of the blade airfoil for reducing the thermal and mechanical stresses in the region of transition between the trailing edge and shroud, thereby extending the service life of the stator blade. | 03-24-2011 |
| 20110103960 | APPARATUS AND METHOD FOR REDUCING WEAR IN DISK LUGS - A disk includes a disk lug and a wear element. The disk lug includes an outer surface, an inner surface radially inward of the outer surface, and a plurality of lateral surfaces between the outer surface and the inner surface, wherein the outer surface is wider than the inner surface. The wear element is disposed on at least one of the plurality of lateral surfaces, and the wear element creates a raised surface on at least one of the plurality of lateral surfaces. A method for installing a wear element to a disk lug includes machining a slot into the disk lug and inserting the wear element at least partially into the slot so that the wear element creates a raised surface on the disk lug. | 05-05-2011 |
| 20110110783 | Trunnion hole repair utilizing interference fit inserts - A vane shroud for a gas turbine engine has a cylindrical shaped body and a hole arranged at a circumference of the body. The hole is for receiving a trunnion from a variable vane. A counterbore is arranged concentrically around the hole on a radially inward facing surface of the body, and receives a trunnion hub from the variable vane. A shrink-fit insert is seated into the counterbore such that the trunnion hub is provided with a contact surface, and the shrink-fit insert is secured to the shroud through an interference fit. | 05-12-2011 |
| 20110110784 | TURBINE BLADE AND ROTOR - Embodiments of the invention relate generally to turbine blades and rotors and, more particularly, to turbine blades having, among other features, complimentarily shaped integral covers and bases capable of increasing stiffness and damping characteristics while decreasing vibratory stress. In one embodiment, the invention provides a turbine blade comprising: an elongate vane having a twisted configuration about a longitudinal axis thereof, the elongate vane having a leading face and a trailing face; a base at a proximal end of the elongate vane, the base having: a substantially planar member substantially normal to the longitudinal axis of the elongate vane; and a dovetail member on a surface of the planar member opposite the elongate vane; and a cover member at a distal end of the elongate vane, the cover member having a leading face and a trailing face. | 05-12-2011 |
| 20110110785 | ROTOR FOR AN AXIAL-THROUGHFLOW TURBOMACHINE AND MOVING BLADE FOR SUCH A ROTOR - A rotor is provided for an axial-throughflow turbo machine, which carries a plurality of moving blades which are each pushed with a blade root into a rotor groove extending about the axis and are held. The blade root includes a hammer root with a hammerhead and is supported on radial stop faces of the rotor groove which lie further outward in the radial direction, against centrifugal forces acting on the moving blades, and are supported on axial stop faces lying further inward in the radial direction, against axial forces which act on the moving blade. The rotor groove has at its bottom, to reduce thermal stresses, an axially and radially widened bottom region with a continuously curved cross-sectional contour. In such a rotor, an advantageous adaptation of the blading is achieved by the blade root of the moving blades being adapted to the widened bottom region in the radial direction. | 05-12-2011 |
| 20110110786 | Rotor Blade and Flow Engine Comprising a Rotor Blade - A rotor blade for a flow machine, in particular a steam turbine, includes an insertion root with a first finger and two second fingers which are arranged on either side of the first finger in axial direction. The first finger and the second fingers have a shoulder in axial direction on axial sides facing one another such that the fingers have a radially outer first portion and a radially inner second portion whose axial extension is shorter than that of the outer, first portion. In relation to a total axial width between axial sides of the two second fingers which face away from one another, the radial height of the first, radially outer portion is in the range of 0.39 to 0.45, particularly 0.40 to 0.44, and the radial height of the second, radially inner portion is between 0.40 and 0.46, particularly between 0.41 and 0.45. | 05-12-2011 |
| 20110150657 | TURBOMACHINE FAN ROTOR - A turbomachine fan rotor including a disk carrying blades with roots that are engaged in axial grooves of the disk, a spacer being interposed between the bottom of each groove and the corresponding blade root, the spacer including at its upstream end a nib for retaining the blade root, the nib including a downstream abutment face against which the upstream end of the blade root bears in event of a violent force being applied thereto, the abutment face being oblique relative to the axis of rotation of the rotor. | 06-23-2011 |
| 20110158814 | TURBINE ENGINE ROTOR BLADES AND ROTOR WHEELS - A rotor wheel and a rotor blade for use in a turbine engine, the rotor wheel and the rotor blade being configured to comprise a connection formed between a root of the rotor blade and an outer radial portion of the rotor wheel that secures the rotor blade to the rotor wheel during operation of the turbine engine; wherein the connection comprises two or more tangential dovetails. | 06-30-2011 |
| 20110217176 | METHOD FOR CONNECTING AT LEAST ONE TURBINE BLADE TO A TURBINE DISK OR A TURBINE RING - The invention relates to a method for connecting at least one turbine blade ( | 09-08-2011 |
| 20110223027 | COMPOSITE FAN BLADE DOVETAIL ROOT - A composite fan blade having an airfoil with a leading edge and a trailing edge and a dovetail root includes a first pressure face and second pressure face, a lower horizontal face connecting the pressure faces at the bottom of the dovetail and a first and a second dovetail runout fillet connecting the pressure faces to the airfoil. The pressure faces are each angled outward at about 65 degrees to about 75 degrees from horizontal. | 09-15-2011 |
| 20110293429 | BLADE FIXING DESIGN FOR PROTECTING AGAINST LOW SPEED ROTATION INDUCED WEAR - The blade dovetails and associated dovetail slots of a gas turbine engine rotor assembly are shaped so that during windmilling the high stress regions of the blade dovetails are shielded from rubbing against the disk and vice versa. Bumper surfaces are provided in low stress regions of the dovetail assembly such that the windmilling contact points between the blade dovetails and the disk are in non-critical areas of the dovetail assembly. | 12-01-2011 |
| 20110293430 | TURBINE BLADE WALKING PREVENTION - A turbine assembly has a casing, a turbine ring and a blade. The blade has a root portion having an axially extending first shape, an airfoil attaching to the root portion and having a trailing edge and a radially outward tip. The tip has a first portion disposed in parallel to the axis of rotation for minimizing escape of air between the tip and the casing and a second portion extending aft from the first portion at an inward angle. The ring has a cut-out having a second shape mating with the first shape. | 12-01-2011 |
| 20110293431 | COMPONENT HAVING VARYING STRUCTURES AND METHOD FOR PRODUCTION - Single-crystalline or stem-shaped turbine blades are difficult to produce. A turbine blade is provided which has varying structures for different areas of the turbine blade, wherein the airfoil region always includes a stem-shaped or single crystalline structure and the other regions may deviate therefrom. A method for producing the turbine blade is also provided. | 12-01-2011 |
| 20110311365 | FAN BLADE AND ATTACHING MEANS THEREFOR - In order to disclose attaching means ( | 12-22-2011 |
| 20110318186 | Root-End of a Wind Turbine Blade - The root-end of a blade of a wind turbine contains at least two segments. The segments contain a connection mechanism for their connection to build up the root-end. The segments contain a first segment section, which is prepared for a connection with fiber reinforced components of the blade. The segments contain a second segment section, which is prepared for a connection with a hub of a wind turbine or which is prepared for a connection with pitch-components of a wind turbine. | 12-29-2011 |
| 20120014802 | DOVETAIL CONNECTION FOR TURBINE ROTATING BLADE AND ROTOR WHEEL - Swivel dovetail connections, such as a tangential entry, straight axial entry or curved axial entry dovetails, for connecting a blade and a rotor wheel in a turbomachine are disclosed. A modified shape of dovetail contact surfaces creates a swivel dovetail connection between blades and rotor wheels, and allows limited motion of blades relative to wheels, while still maintaining the structural connection between blades and wheels. The swivel dovetail connection is achieved by providing concave or convex dovetail contact surfaces between a rotor wheel and a blade such that the contact surfaces lie along a common substantially toroidal arc, an axially extending, substantially cylindrical arc, or a substantially frusto-conical arc. | 01-19-2012 |
| 20120020796 | RETAINING RING - A retaining ring presenting, on its periphery, a plurality of radial bores, each of the bores being able to receive a blade root. The retaining ring also includes at least one first radial opening traversed by a compression tube and at least one second radial opening, the at least first radial opening and the at least second radial opening being separated from each other by at least one of the bores of the plurality of radial bores. The ventilation device finds a particularly interesting application in the field of turbine engines including a pusher open rotor. | 01-26-2012 |
| 20120027604 | COMPOSITE VANE MOUNTING - A vane includes a composite airfoil having chordwise spaced apart forward and aft dovetail feet at or near leading and trailing edges of the airfoil. Each foot includes a shank connecting a dovetail root to an airfoil base and each root is slidably received in a dovetail slot in an inner vane mount. The dovetail slot has a triangular slot cross section and a flat slot bottom and flat slot pressure and suction side crush faces corresponding to pressure and suction sides of the airfoil. The dovetail root having a triangular root cross section and a flat root bottom and flat dovetail root pressure and suction side crush faces. A biasing means urges the root bottom of the dovetail roots away from the slot bottom and presses and preloads the dovetail root pressure and suction side crush faces against the slot pressure and suction side slot crush faces. | 02-02-2012 |
| 20120034086 | SWING AXIAL ENTRY DOVETAIL FOR STEAM TURBINE BUCKETS - An arrangement and a method for mounting articulated turbine buckets in axial entry slots of rotor wheels. A curvature on a vertical plane may be incorporated on a swing axial-entry male dovetail projection of the bucket root and the associated swing axial-entry female dovetail slot of the rotor wheel. The curvature facilitates loading of buckets otherwise precluded by interferences, such as interlocking tip shrouds on adjacent buckets. Such loading may be provided by locating the shroud tip shroud in proximity to an adjacent tip shroud and pivoting the root end of the swing axial-entry bucket around the location of the tip shroud such that the arc formed by the bucket allows the curvature of the swing axial-entry male dovetail projection to swing into the swing axial-entry female dovetail slot of the rotor wheel. | 02-09-2012 |
| 20120034087 | Axial Turbomachine Rotor Having a Sealing Plate - An axial turbomachine rotor is provided. The turbomachine includes a rotor body designed in a rotation symmetrical manner around the rotor axis, a rotor blade ring including rotor blades that are each fixed to the rotor body by the blade foot thereof and a sealing disc designed in a rotation symmetrical manner around the rotor axis that is arranged having the outer edge thereof radially inside, neighboring an axially extending protrusion of the blade foot, so that a hollow space is formed between the blade foot and the sealing disc, wherein a groove exists on the outer edge leading radially to the outside, wherein a sealing ring is mounted that may slide radially to the outside in the groove during operation of the rotor by centrifugal force until the sealing ring radially contacts the inside of the protrusion and thus seals the hollow space on the blade foot. | 02-09-2012 |
| 20120039718 | CASTING APPARATUS FOR PRODUCING A TURBINE ROTOR BLADE OF A GAS TURBINE AND TURBINE ROTOR BLADE - A casting apparatus for producing a turbine rotor blade of a gas turbine, and to a turbine rotor blade produced therewith is provided. The casting apparatus includes a hollow ceramic shell mold, of which the pouring gate and cores arranged therein are oriented with respect to each other such that a hot casting material flowing into a cavity of the ceramic shell mold does not come in direct contact with the cores. Thus, so-called hot spots on cores are avoided, which until now have had negative effects on the solidification of the casting material. Especially in the region of the blade root of the turbine rotor blade to be produced improved solidification of the casting material may thus be obtained, reducing any disturbance in the structure of the solidified casting material. | 02-16-2012 |
| 20120076659 | ANTI FRET LINER ASSEMBLY - An anti-fret assembly for a turbine engine, the assembly comprising an elongate liner having first and second walls connected by a base to provide a generally U-shaped channel, the liner having an outer surface adapted to lie against a first component and an inner surface adapted to lie against a second component, at least the first wall being provided with a notch for receipt of an anti-translation pin, the assembly further comprising an anti-translation pin. | 03-29-2012 |
| 20120082551 | GAS TURBINE BLADE AND METHOD OF PROTECTING SAME - An airfoil blade of a gas turbine engine includes a root configured for mating attachment with a cooperating rotor hub and an airfoil extending away from the root. The root is composed of a first metal and has a nanocrystalline metal coating, composed of a second metal, over at least a portion thereof. A method of protecting such a blade by applying a nanocrystalline metal coating to a portion of the blade root is also disclosed. | 04-05-2012 |
| 20120093654 | Rotor blade for an axial flow turbomachine and mounting for such a rotor blade - A rotor blade for an axial flow turbomachine, preferably a turbine, and to a mounting for such a rotor blade is provided. In the rotor blade, the two opposing lateral walls of the blade base are continuously curved along their extension between platform and bottom side of the blade base in order to reduce the mechanical load in the blade base and that of the walls supporting the blade base of a rotor. | 04-19-2012 |
| 20120099999 | SWING AXIAL-ENTRY FOR CLOSURE BUCKET USED FOR TANGENTIAL ROW IN STEAM TURBINE - An arrangement and a method for mounting articulated turbine buckets in axial entry slots of rotor wheels. A curvature on a vertical plane may be incorporated on an axial male dovetail projection of the bucket root and the associated axial female dovetail slot of the rotor wheel. The curvature facilitates loading of buckets otherwise precluded by interferences, such as interlocking tip shrouds on adjacent buckets. Such loading may be provided by locating the shroud tip shroud in proximity to an adjacent tip shroud and pivoting the root end of the bucket around the location of the tip shroud such that the arc formed by the bucket allows the curvature of the axial male dovetail projection to swing into the axial female dovetail slot of the rotor wheel. | 04-26-2012 |
| 20120134834 | ASYMMETRICAL ROTOR BLADE SLOT ATTACHMENT - A gas turbine engine includes a disk having an annular hub circumscribed about a centerline with an annular web extending radially outward from the hub to an annular rim. A multiple of slots extend generally axially through the rim and at least one of the multiple of slots having an asymmetric slot root for lower stress and higher service life. | 05-31-2012 |
| 20120156045 | METHODS, SYSTEMS AND APPARATUS RELATING TO ROOT AND PLATFORM CONFIGURATIONS FOR TURBINE ROTOR BLADES - A rotor blade assembly for a turbine engine, the rotor blade assembly including: a turbine blade that includes a shank situated between attachment means and an airfoil, the shank having a forward portion and an aft portion; and a platform comprising a platform pressure side and a platform suction side, each of which comprising non-integral components to the other and the turbine blade. The platform may comprise an interface between the platform pressure side and the platform suction side. And, the platform may be configured such that the interface aligns with at least one of the forward portion and the aft portion of the shank. | 06-21-2012 |
| 20120171039 | TURBINE AIRFOIL COMPONENT ASSEMBLY FOR USE IN A GAS TURBINE ENGINE AND METHODS FOR FABRICATING SAME - A turbine airfoil component assembly for use with a turbine engine including a attachment assembly having an inner surface defining a cavity. The attachment assembly includes a metal alloy substrate. An airfoil assembly is at least partially positioned within the attachment assembly and extends outwardly from the attachment assembly. The airfoil assembly includes a ceramic matrix composite (CMC) substrate. A reaction barrier coating is disposed over at least a portion of the airfoil assembly. The reaction barrier coating is positioned between the attachment assembly and the airfoil assembly. | 07-05-2012 |
| 20120183405 | TURBINE BLADE WITH LATERALLY BIASED AIRFOIL AND PLATFORM CENTERS OF MASS - A turbine blade airfoil ( | 07-19-2012 |
| 20120183406 | TURBINE ROTOR - Providing a turbine rotor in which the rotational inertia of the turbine rotor can be reduced without changing the geometry of the blade part, whereas the turbine rotor is provided with the rear side surface so that the stress concentration appearing at the root part regarding the hub part on the rear surface side is constrained in order that the strength and the durability of the turbine rotor can be enhanced. A turbine rotor that comprises a hub part | 07-19-2012 |
| 20120189452 | Impeller Attachment Method - A pump is provided having an impeller in combination with a power transmission shaft. The impeller has a tapered bore with impeller threads. The power transmission shaft has a shaft end with tapered threads configured to couple directly to the impeller threads of the tapered bore of the impeller, to transmit torque directly through the tapered threads, and to provide self axial or radial alignment even if the coupling of the tapered threads and the impeller threads of the tapered bore start out of alignment. The tapered thread configuration substantially reduces investment in lifting equipment and time by maintenance personnel because it eliminates the need for maintenance personnel to precisely align the impeller threads and the tapered threads before attaching or removing the impeller and the tapered threads release much more quickly from the impeller than a standard thread configuration, reducing the number of turns the power transmission shaft must be rotated by hand to free it from the impeller. | 07-26-2012 |
| 20120224971 | TURBINE BLADE FASTENING FOR A TURBO ENGINE - A turbine blade fastening is provided. The turbine blade fastening include a blade root implemented in a fir tree design, which includes anchoring teeth implemented toward the blade casting tip such that the height of the anchoring teeth is reduced toward the blade casting tip. The anchoring teeth are designed for fitting into corresponding recesses in a rotor. | 09-06-2012 |
| 20120230829 | TURBINE OR COMPRESSOR BLADE - A blade for a turbine or a compressor, at least partially made of fiber-reinforced plastic, in particular carbon fiber reinforced plastic, being particularly durable under operating conditions is provided. The blade includes a blade body and a blade root. The blade body is substantially made of a folded fabric web made of fiber reinforced plastic, wherein a retaining loop is formed in the area of the fold, and wherein a blade surface is formed in the area of the fold, and wherein a blade surface is formed from the overlapping web ends. The blade root includes a longitudinal beam and at least two holders for anchoring the blade in a corresponding groove of a rotor, the holders being preferably each fixedly connected to the beam at both ends. The blade body is suspended on the beam by means of the retaining loop. | 09-13-2012 |
| 20120237349 | Methods and Apparatus to Repair a Rotor Disk for a Gas Turbine - Embodiments of the invention can provide methods and apparatus to repair a rotor disk for a gas turbine. In one embodiment, a method to repair a rotor disk for a gas turbine is provided, wherein the rotor disk can include a base and at least one dovetail slot between a pair of dovetail walls. The method can include identifying one or more cracks on the base of the rotor disk, and removing one or more cracks by providing one or more fillets on the base of the rotor disk. Further, the method can include providing one or more conic cuts on the base of the rotor disk between the pair of dovetail walls of at least one dovetail slot. | 09-20-2012 |
| 20120244002 | TURBINE BUCKET ASSEMBLY AND METHODS FOR ASSEMBLING SAME - A turbine bucket for use with a turbine engine. The turbine bucket includes a shank and a platform bordered by a forward edge and an aft edge that are coupled together by a pair of side edges, the forward edge upstream from the aft edge. The platform includes at least one interlock seal extending outward from at least one of the side edges and a mating groove defined in at least one of the side edges, the groove sized to receive the at least one interlock seal extending from an adjacent turbine bucket. | 09-27-2012 |
| 20120244003 | ROTOR HAVING AN ANNULUS FILLER - An annulus filler for installation between blades, such as fan blades, of the rotor of a gas turbine engine includes a channel which accommodates a post defined between blade slots of the disc. A chocking surface of the annulus filler contacts regions of a contact surface of the post to chock the head of the post within the channel. The annulus filler is thus supported along the axial length of the post, enabling it to withstand circumferential forces generated on rotation of the disc. | 09-27-2012 |
| 20120251327 | PROCESS OF PREPARING A TURBINE ROTOR WHEEL, A REPAIR TOOL FOR A TURBINE ROTOR WHEEL, AND A TURBINE ROTOR WHEEL - A process of preparing a turbine rotor wheel, a repair tool for machining a turbine rotor wheel, and a turbine rotor wheel are disclosed. The process includes providing the turbine rotor wheel, the turbine rotor wheel having a dovetail slot, a cooling slot, and a dovetail acute corner formed by the dovetail slot and the cooling slot and removing a stress region from the dovetail acute corner. The repair tool permits removal of strained material while also reducing the operating stress of the feature. The turbine rotor wheel includes a machined portion resulting in lower stress for the turbine rotor wheel. | 10-04-2012 |
| 20120251328 | METHOD AND SYSTEM FOR SEALING A DOVETAIL - A method and system for sealing a gap between a bucket dovetail and a rotor is provided. The dovetail seal includes a first end portion extending from a first extent of the first end portion a predetermined distance along a length of the dovetail seal, a second end portion extending from a first extent of the second end portion a predetermined distance along a length of the dovetail seal towards the first end portion, and a body extending between the first and second end portions. The body includes a U-shaped bend complementary to a sealing groove in a dovetail of a turbine blade. The first end portion includes a converging flared cross-section from the first extent of the first end portion toward the second end portion and the second end portion includes a converging flared cross-section from the first extent of the second end portion toward the first end portion. | 10-04-2012 |
| 20120282104 | TURBINE ENGINE FAN DISK - The invention relates to a turbine engine fan disk comprising a cylindrical rim including in its outer periphery substantially axial slots for mounting blade roots and opening out to a radially upstream face of the rim. A shroud extends from the rim and connects with a rotary drive shaft. A cylindrical lip extends upstream from the upstream face of the rim. The inside surface of the disk having a cylindrical portion extended upstream by a portion of greater diameter that forms a setback that is axially offset upstream relative to the upstream radial face of the rim. | 11-08-2012 |
| 20120294721 | TURBINE ENGINE FAN - A turbine engine air blower including a rotor disk that includes, on an outer periphery thereof, longitudinal ribs, each including a radial lug for attaching the disk onto a downstream compressor rotor. The flanks of the lugs form abutments for holding vanes that are mounted onto the disk. A mechanism protecting flanks of the lugs is circumferentially inserted between the lugs and the vanes. | 11-22-2012 |
| 20120308391 | LAYOUT OF A BLISK - A layout of a blisk includes two inserts housed between the bulb of the blade and the wall of a groove in a disk to compensate for variations in inclination between the overhanging faces of the groove and the upper faces of the bulb at their central part. This construction makes it possible to select blades for which upper faces of the bulb are slightly inclined relative to the radial direction, which facilitates their construction from a composite material. | 12-06-2012 |
| 20130004319 | ROTOR ASSEMBLY AND REVERSIBLE TURBINE BLADE RETAINER THEREFOR - A blade retainer for a gas turbine engine includes a plate-like member with an arcuate outer face, an opposed inner face, and two spaced-apart end faces. The member has an outer portion disposed adjacent the outer face, and an inner portion disposed adjacent the inner face, and a wedge-shaped recess with a concave radiused valley is formed in the inner portion adjacent each end face. The retainer is left-right symmetrical. | 01-03-2013 |
| 20130028742 | SYSTEM AND METHOD FOR EFFICIENT WIND POWER GENERATION - A system and method for efficient wind power generation is provided. The system includes a shaft that rotates around a vertical axis, a plurality of blades, and a plurality of arms that couple the blades to the shaft. The blades are configured to have a rounded, symmetrical design which minimizes the effects of lift. The blades are also configured to include a notched portion for capturing wind and using it to propel the blades. The blades may also be configured to include winglets, which reduce vortex shedding, drag, and noise, and could also reduce friction on the bearings caused by gravity. | 01-31-2013 |
| 20130034445 | TURBINE BUCKET HAVING AXIALLY EXTENDING GROOVE - A turbine bucket and corresponding turbines are disclosed herein. In one aspect, the turbine bucket includes: a blade member; and a base member affixed to the blade member, the base member configured to attach to a turbine rotor radially inward of the blade member, wherein the base member includes a first semi-elliptical extension spanning substantially an axial length of the base member and extending at least partially perpendicularly in relation to a primary axis of the turbine bucket. | 02-07-2013 |
| 20130064668 | TURBINE ROTOR BLADE ASSEMBLY AND METHOD OF ASSEMBLING SAME - A rotor blade assembly for a rotor of a gas turbine engine having an axis of rotation includes a shank portion formed from a ceramic matrix composite (CMC) material. The rotor blade assembly also includes a platform portion formed from a substantially similar CMC material as that of the shank portion. The platform portion is coupled to the shank portion. The platform portion and the shank portion cooperate to at least partially define two opposing side portions of the rotor blade assembly. The opposing side portions are angularly separated with respect to the axis of rotation. The rotor blade assembly further includes a damper retention apparatus. The damper retention apparatus is coupled to the shank portion. The damper retention apparatus includes at least one angled bracket apparatus extending toward a circumferentially adjacent rotor blade assembly. | 03-14-2013 |
| 20130064669 | BLADE AND METHOD FOR MANUFACTURING BLADE - A method of manufacturing a rotor blade is provided. The method includes forming a preform from a plurality of composite plies, the preform including an airfoil portion and a dovetail portion, removing a cutout portion from the dovetail portion of the preform to define a cutout in the preform, wherein the removing the cutout portion facilitates reducing residual stresses in the preform, and inserting an insert into the cutout formed by the removal of the cutout portion. | 03-14-2013 |
| 20130064670 | TURBINE BLADE - An airfoil profile is formed such that a passage width ratio, represented in a dimensionless manner, of an inter-blade passage width of vane root cross-section to an outlet throat width substantially monotonously decreases from a blade inlet toward a blade outlet. The blade has a blade airfoil profile shape in an envelope within a range of ±2.0 mm in a direction normal to any surface location of an airfoil profile portion. The airfoil profile portion has a reference airfoil contour represented in Cartesian coordinates, wherein Z is a distance representing a sectional height from a root of the airfoil profile portion. The contours represented by X and Y at each section Z are joined smoothly with one another in a blade height direction to form a complete shape of the airfoil profile portion. | 03-14-2013 |
| 20130078103 | HOLLOW FAN BLADE RIB GEOMETRY - A fan blade has a main body extending between a leading edge and a trailing edge. Channels are formed into the main body from at least one open side. A plurality of ribs extend across the main body intermediate the channels. The fan blade has a dovetail and an airfoil extending radially outwardly from the dovetail. The ribs have a thickness defined as measured generally from the leading edge toward the trailing edge. A thickness of at least one of the ribs is generally thicker adjacent radially inner ends and becomes thinner moving in a radially outward direction. | 03-28-2013 |
| 20130078104 | FAN BLADE HAVING INTERNAL RIB BREAK-EDGE - A fan blade has a main body extending between a leading edge and a trailing edge. Channels are formed into the main body from at least one open side. A plurality of ribs extend across the main body intermediate the channels. The fan blade has a dovetail, and an airfoil extends radially outwardly from the dovetail. The ribs having a thickness defined as measured from said leading edge toward said trailing edge. The ribs have break-edges at ends of the thickness that extend away from an outer face of the rib. | 03-28-2013 |
| 20130084188 | Blade - Disclosed herein is a blade that avoids fretting damage, while reducing stress occurring at the neck portion as caused by the stress relief groove. The blade disposed on an outer periphery of a rotor is provided. The blade includes: a blade portion; a dovetail portion for holding the blade on the rotor; a platform portion that connects the dovetail portion and the blade portion; and a stress relief groove that connects a side surface of the platform portion and a blade load bearing surface of the dovetail portion, wherein the dovetail portion has a width that increases toward a bottom side thereof within a range from a connection point between the side surface of the platform portion and the stress relief groove to a connection point between the dovetail portion and the stress relief groove. | 04-04-2013 |
| 20130094968 | ADAPTOR ASSEMBLY FOR COUPLING TURBINE BLADES TO ROTOR DISKS - An adaptor assembly for coupling a blade root of a turbine blade to a root slot of a rotor disk is described. The adaptor assembly includes a turbine blade having a blade root and an adaptor body having an adaptor root. The adaptor body defines a slot having an open end configured to receive the blade root of the turbine blade such that the adaptor root of the adaptor body and the blade root of the turbine blade are adjacent to one another when the blade root of the turbine blade is positioned within the slot. Both the adaptor root of the adaptor body and the blade root of the turbine blade are configured to be received within the root slot of the rotor disk. | 04-18-2013 |
| 20130094969 | SYSTEM FOR SEALING A SHAFT - An embodiment of the present invention takes the form of a seal that may substantially reduce cross-shank leakage between components mounted on a shaft. Embodiments of the seal may be connected to a wide variety of rotatable components including, but not limited to, compressor blades, turbine buckets, or the like. | 04-18-2013 |
| 20130101421 | WEAR-RESISTANT PART FOR THE SUPPORT OF A BLADE OF A TURBOJET FAN - An aircraft turbojet fan including multiple fan blades including a support that includes a rear portion including a first surface located on an intrados side and a second surface located on an extrados side. A fan disk includes, between recesses, attaching flanges radially protruding towards the outside such that the first surface and the second surface are located respectively opposite two attaching flanges. The fan further includes a wear-resistant part installed on the blade to form a protective shell on each of the first and second surfaces of the support, preventing contact between each surface and the attaching flange located opposite it. | 04-25-2013 |
| 20130101422 | FASTENING ASSEMBLY FOR BLADES OF TURBOMACHINES HAVING AXIAL FLOW AND METHOD FOR PRODUCING SUCH AN ASSEMBLY - A fastening assembly for blades of turbomachines through which axial flow can take place, preferably compressors, includes a blade carrier having a lateral face, in which retaining groves are distributed along the circumference, with blades being inserted in the grooves, wherein a resilient tensioning element is provided between each groove base and the underside of the respective blade foot, the underside being located opposite of the groove base. The tensioning element is supported on the respective underside and on the respective groove base in a pretensioning manner, wherein a channel is provided both in the groove base and in the underside, with the tensioning element resting in the channels. | 04-25-2013 |
| 20130108449 | SYSTEM FOR COUPLING A SEGMENT TO A ROTOR OF A TURBOMACHINE | 05-02-2013 |
| 20130149158 | ROTOR WITH RELIEF FEATURES AND ONE-SIDED LOAD SLOTS - An exemplary turbomachine rotor assembly includes a pair of spaced rails that extend around a cylindrical surface to define a rotor hub. The rails define a space for receiving blades. Load slots are formed in one of the rails. A relief feature is formed in an opposite surface of an opposing rail. The load slots and relief feature utilized to move at least one of the blades into the space. | 06-13-2013 |
| 20130156587 | RETROFITTING METHODS AND DEVICES FOR LARGE STEAM TURBINES - A method of replacing rotating metal blades of a steam turbine inserted into a rotor having one or more existing grooves for inserting root sections of the metal blades is described, the method including the steps of providing replacement blades having radially inwards directed root sections of fiber-reinforced composite material, changing the shape of the one or more grooves in the rotor to form a cavity for the insertion of the root sections of fiber-reinforced composite material and inserting the replacement blades into the rotor. | 06-20-2013 |
| 20130164138 | TURBINE ROTOR INSERT AND RELATED METHOD OF INSTALLATION - Systems, methods and devices adapted to ease installation of turbine bucket assemblies about a rotor and to reduce related stress concentrations in the rotor are disclosed. In one embodiment, an insert includes: a base portion adapted to complement an entry slot in a rotor of a turbine; and a neck portion extending radially outboard from the base portion, the neck portion adapted to complement a post of the rotor to form a substantially continuous dovetail about the rotor. | 06-27-2013 |
| 20130170996 | ROTOR BLADE MOUNTING - A wheel dovetail groove with a wheel hook retains blade hooks of mounted blades. Opposed arcuate cut-outs in upper recessed areas of the groove may form an assembly gate. Blade hooks may be inserted into the groove in a first orientation, rotated to a second orientation at the assembly gate, and slid into a predetermined position. Blades may be secured with shims between adjacent bucket dovetails. Blade tip cover blocks may be included to form a cover. All blades may be substantially identical and not need special mounting arrangements at the assembly gate. | 07-04-2013 |
| 20130183156 | ROTOR WHEEL FOR A TURBOMACHINE - A rotor wheel for a turbomachine includes a rotor wheel body having a first face and an opposing second face joined by an outer diameter surface having a centerline. A blade receiving slot is formed in the outer diameter surface and extends about the rotor wheel body. A blade loading slot is formed in the outer diameter surface. The blade loading slot is connected with and axially off-set from the blade receiving slot. | 07-18-2013 |
| 20130183157 | METHOD OF SURFACE TREATMENT FOR DOVETAIL IN GAS TURBINE ENGINE FAN BLADE - A method of surface treating a dovetail in a blade includes the steps of providing a burnishing operation along circumferential sides of the dovetail. Next, shot peening is provided at axial ends of the dovetail. A fan blade made by the method is also claimed. | 07-18-2013 |
| 20130183158 | Anti-Ovalization Tool for Introduction Into a Wind Turbine Blade Root and Method of Reducing Ovalization of a Wind Turbine Blade Root - Anti-ovalization tool for introduction into a wind turbine blade root comprising two or more rigid bodies connected to one another along their side edges with distances in between them and together forming a substantially cylindrical body, wherein the distances between the rigid bodies are adjustable. The invention is further related to the method of reducing ovalization of a wind turbine blade root and to the use of a tool comprising two or more rigid bodies as an anti-ovalization tool. | 07-18-2013 |
| 20130189109 | THIN AIRFOIL CEILING FAN BLADE - A fan blade comprising a root end, a blade region, and a transition region. Wherein each of the root end and blade region comprise a unique profile, and wherein the transition region comprises a profile which transitions the root end profile to the blade region profile. The root end profile comprises a substantially convex top surface, a substantially concave domed sector, and reliefs to allow for the root end to be coupled with a similarly shaped fan hub extrusion. The blade region profile comprises a substantially convex top surface and bottom surface which terminate at a leading edge and trailing edge. The blade region slopes upward along a length of the blade region and terminates at a curved tip. | 07-25-2013 |
| 20130189110 | TURBINE ARRANGEMENT AND GAS TURBINE ENGINE - A turbine arrangement includes first and second platforms forming a section of a main fluid path, aerofoils, and an impingement plate. Each aerofoil extends from the first to the second platform. The second platform has a surface opposite to the main fluid path with recesses surrounded by a raised edge, which provides support for the mountable impingement plate. The edge is formed as a first closed loop surrounding a first recess and further surrounding a first aperture of a first aerofoil and as a second closed loop surrounding a second recess and further surrounding a second aperture of a second aerofoil. A portion of the edge defines a continuous barrier between the first recess and the second recess for blocking cooling fluid. The barrier forms a mating surface for a central area of the impingement plate. | 07-25-2013 |
| 20130224029 | BALANCING OF ROTORS - A balanced rotor comprising a circumferential slot and a plurality of aerofoils each secured in the slot by a respective root, the root having a root block having circumferentially facing flanks and a seal wing extending circumferentially from one of the flanks, characterised in that the seal wing has a notch engaging a balance weight positioned between adjacent roots. | 08-29-2013 |
| 20130259694 | Method for Manufacturing Multi-Finger Pinned Root for Turbine Blade Attached to Turbine Rotor and Turbine Blade - In manufacturing a multi-finger pinned root pin-coupling a turbine blade made of a high-strength material and a rotor disc, a reamer used to ream a pin insertion hole formed through a turbine blade attachment base is removed from the pin insertion hole while being rotated so as to cause a scratch formed by a chip on the inner surface of the pin insertion hole to be inclined with respect to the axial direction of the pin insertion hole. This brings the direction of the scratch on the inner surface of the pin insertion hole and the direction of tensile stress generated on the inner surface of the pin insertion hole adequately close to be parallel to each other. As a result, the fatigue strength reduction caused by the scratch can be inhibited. | 10-03-2013 |
| 20130266448 | AERODYNAMIC ELEMENT FOR AN AIRCRAFT NACELLE - An aerodynamic element for an aircraft nacelle is provided that includes a fixed shroud and an intake lip axially movable relative to the shroud. The aerodynamic element is flexible and has a substantially cylindrical general shape and defines an upstream portion attached to the inner wall of the intake lip of the nacelle, and a downstream portion bearing radially against an inner face of the shroud. The downstream portion of the element includes a ring shaped bead protruding towards an outside of the aerodynamic element and an end blade which, at rest, is tilted towards the outside of the aerodynamic element in a direction of its free end. | 10-10-2013 |
| 20130272885 | Turbomachine Blade Mounting System - Embodiments of the present disclosure include a system having a turbine blade segment having a blade and a mounting segment coupled to the blade, wherein the mounting segment has a multi-piece assembly configured to mount in a radial direction into a slot of a turbomachine rotor. | 10-17-2013 |
| 20130287578 | BLADE DOVETAIL BOTTOM - A blade has an airfoil extending radially outwardly of a dovetail. The dovetail has edges that will be at circumferential sides of the blade when the blade is mounted within a rotor. A bottom surface of the dovetail will be radially inward when the rotor blade is mounted in a rotor, and is formed such that a circumferentially central portion of the bottom surface is radially thicker than are circumferential edges. A fan and a gas turbine engine are also described. | 10-31-2013 |
| 20130302170 | ROTOR DISK AND ROTOR ASSEMBLY - The disclosure generally relates to rotor disks and rotor assemblies having a composite lubricated sheet adhered thereon and having improved tribological properties at high temperatures. | 11-14-2013 |
| 20130323064 | AIRFOIL AND DISK INTERFACE SYSTEM FOR GAS TURBINE ENGINES - A gas turbine engine system includes a disk and an airfoil. The disk includes a first rail, a second rail, a retention slot located between the first and second rails, and a ridge extending radially outward from the second rail. The airfoil is engaged with the retention slot, and includes a platform with an upstream angled portion, a downstream angled portion, and a notch defined in the platform. The ridge of the disk extends at least partially into the notch of the platform. | 12-05-2013 |
| 20130323065 | FAN ROTOR BLADE AND FAN - A fan rotor blade has a rotor blade leading edge. On a hub side of the rotor blade leading edge, a vertical hub section is formed. From a top end of the vertical hub section to a mid-span side of the rotor blade leading edge, a backward tilt mid-span section is formed. From a top end of the backward tilt mid-span section to a tip end of the rotor blade leading edge, a forward tilt tip section is formed. From a hub end of the rotor blade leading edge to a base end of the vertical hub section, a backward tilt hub section is formed. The backward tilt hub section is backwardly tilted so that a top end thereof is positioned behind a base end thereof. | 12-05-2013 |
| 20130330196 | FAN BLADE PLATFORM - A fan assembly includes a first fan blade with a rib extending therealong and a first fairing platform mounted on and supported from the first fan blade. The first fairing platform has a flange with a groove that mates with the rib. | 12-12-2013 |
| 20130330197 | BLADE FOR A WIND TURBINE - A blade for a wind turbine comprising a blade root portion is described. The blade root portion defines an mounting surface for coupling to a hub or extender of the wind turbine and comprises a plurality of first holes provided with an insert, the blade root portion further comprises a mounting flange arranged in the periphery of the mounting surface and provided with second holes, wherein the inserts comprise a first end embedded in the blade root portion and a second end opposite to said first end, the second end protruding beyond the mounting surface of the blade root portion, and wherein the second ends are fitted in the second holes of the mounting flange and the mounting flange is attached to the blade by means of the inserts. Furthermore, a wind turbine rotor comprising such a blade is described. Methods of manufacturing half a wind turbine blade and a whole wind turbine blade are also described. | 12-12-2013 |
| 20130343895 | SYSTEM HAVING BLADE SEGMENT WITH CURVED MOUNTING GEOMETRY - Embodiments of the present disclosure include a system having a blade segment having a blade and a mounting segment coupled to the blade. Additionally, the mounting segment includes a first contact face and a second contact face, wherein the first and second contact face are concave with respect to a longitudinal axis of the blade segment. To reduce stresses within the mounting segment, the mounting segment further includes a lower face coupling the first contact face and the second contact face, wherein the lower face is convex across the longitudinal axis of the blade segment. | 12-26-2013 |
| 20140030098 | ARTICLE OF MANUFACTURE - An article of manufacture has a first component configured for use with a turbomachine. The first component is configured for attachment to a second component, and reduces the possibility of attachment with an undesired third component by modification of a. characteristic of the first component. This modification is matched by a complementary characteristic of the second component. The first component has a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table selected from the group consisting of TABLES 1-11. Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying by a number. X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height. The airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape. | 01-30-2014 |
| 20140030099 | PUMP IMPELLER - An impeller, which is rotatable about an axis, includes an inlet shroud and a backing plate. An inlet orifice is defined by the inlet shroud, and a plurality of outlet orifices are radially outward of the inlet orifice. A plurality of vanes are disposed between the inlet shroud and the backing plate. The vanes are formed integrally as one-piece with the inlet shroud. | 01-30-2014 |
| 20140030100 | AXIAL RETENTION OF A PLATFORM SEAL - A gas turbine engine component has an axial seal pin assembly for sealing between adjacent platform regions where the seal pin assembly design provides a seal pin damper slot extending to a forward axial stop in a forward buttress region. The forward axial stop includes a relief slot to interrupt the loadpath from the airfoil into the blade neck and attachment regions to reduce the stress concentrations in these regions. | 01-30-2014 |
| 20140044549 | DUCTILE COMPENSATION LAYER FOR BRITTLE COMPONENTS - Disclosed is a blade element of a turbomachine, in particular of a gas turbine, which comprises a fastening element ( | 02-13-2014 |
| 20140056712 | TURBINE BUCKET INCLUDING AN INTEGRAL ROTATION CONTROLLING FEATURE - A turbine bucket including an integral rotation controlling feature is disclosed. In one embodiment, a turbine bucket includes: a blade section having an inner radial end and an outer radial end; an integral cover section connected to the outer radial end of the blade section; and a base section for engaging a rotor body, the base section connected to the inner radial end, wherein the base section includes: a central body; a set of tangs extending axially from the central body; a set of flanges radially inboard of the set of tangs and extending axially from the central body; and an integral rotation controlling feature extending from the central body, wherein the rotation controlling feature engages a radial opening in the rotor body. The integral rotation controlling feature is sized to limit rotation of the base section, when the turbine bucket is engaged with a rotor body. | 02-27-2014 |
| 20140056713 | TURBINE ENGINE ROTOR ASSEMBLY - A turbine engine rotor assembly includes a turbine engine rotor disk that extends axially along a centerline between a first disk end and a second disk end, and radially to an outer disk surface. The rotor disk includes one or more blade retention slots arranged circumferentially around the centerline. A first of the blade retention slots extends axially into the rotor disk from a disk end surface at the first disk end to a slot end surface, and radially into the rotor disk from the outer disk surface to a slot base surface. | 02-27-2014 |
| 20140056714 | TURBOMACHINE ROTOR HAVING DOVETAIL SLOT AND METHOD OF MACHINING - Various embodiments include a rotor having a dovetail slot with a bulbous fillet region, and in some cases, recessed inclined bearing surfaces. Various embodiments include methods of forming such a slot in a turbomachine rotor. | 02-27-2014 |
| 20140064976 | ROTOR KEYHOLE FILLET FOR A GAS TURBINE ENGINE - A rotor for a gas turbine engine includes an annular structure having a blade slot. A hub engagement feature is provided on the annular structure. The hub engagement feature includes first and second surfaces transverse to one another and joined by a fillet that is recessed with respect to the first and second surfaces. A method of manufacturing a rotor includes the steps of machining an annular hub engagement feature into a rotor. The hub engagement feature includes first and second surfaces transverse to one another and is joined by a fillet that is recessed with respect to the first and second surfaces. The method includes the step of peening the fillet, and grinding the first and second surfaces. | 03-06-2014 |
| 20140072436 | TURBINE AIRFOIL PLATFORM RAIL WITH GUSSET - A blade for a gas turbine engine includes a shank interconnecting a root and a platform, and an airfoil extending radially from the shank. The shank includes a pocket with the platform overhanging the pocket. A rail extends axially along a lateral edge of the platform and extends radially inward from the platform in a direction opposite the airfoil. A gusset extends from an underside of the platform facing the pocket and in a circumferential direction between the rail and the shank. | 03-13-2014 |
| 20140112794 | BLADE ATTACHMENT ASSEMBLY - An assembly and method for affixing a turbomachine rotor blade to a rotor wheel are disclosed. In an embodiment, an adaptor member is provided disposed between the blade and the rotor wheel, the adaptor member including an adaptor attachment slot that is complementary to the blade attachment member, and an adaptor attachment member that is complementary to the rotor wheel attachment slot. A coverplate is provided, having a coverplate attachment member that is complementary to the rotor wheel attachment slot, and a hook for engaging the adaptor member. When assembled, the coverplate member matingly engages with the adaptor member, and retains the blade in the adaptor member, and the assembly in the rotor wheel. | 04-24-2014 |
| 20140119927 | REDUNDANT AIRFOIL ATTACHMENT - An airfoil attachment according to one example of this disclosure includes an airfoil and a disk supporting the airfoil. Further, there are primary contact surfaces and secondary contact surfaces between the airfoil and the disk. The secondary contact surfaces are not engaged during a normal operating condition. | 05-01-2014 |
| 20140119928 | Turbomachine Blade Reinforcement - Embodiments of the present disclosure include a system having a turbomachine blade segment including a blade and a mounting segment coupled to the blade, wherein the mounting segment has a plurality of reinforcement pins laterally extending at least partially through a neck of the mounting segment. | 05-01-2014 |
| 20140127025 | WIND TURBINE ROTOR BLADE AND METHOD FOR INSTALLING A WIND TURBINE ROTOR BLADE - There is provided a wind power installation rotor blade having a rotor blade root, a rotor blade tip, a rotor blade leading edge, a rotor blade trailing edge, a pressure side and a suction side. The rotor blade further has a rotor blade outer casing with at least one opening in the pressure and/or suction side for receiving handling means for fitting or removing the rotor blade. The rotor blade also has at least one fixing unit for fixing the handling means which are introduced through the at least one opening. The fixing unit is arranged in the interior of the rotor blade outer casing between the pressure side and the suction side. | 05-08-2014 |
| 20140133990 | Hub Piloting Diameter With Relief Cuts - A hub for mounting propeller blades has a plurality of mount locations for receiving propeller blades at a radially outer location. The hub has a piloting diameter centered on a center axis. The hub has a plurality of openings to receive a drive member for transmitting rotation/torque from an adapter. There are reliefs cut into the piloting diameter at locations circumferentially aligned with the openings. | 05-15-2014 |
| 20140140852 | BLADE ROOT, CORRESPONDING BLADE, ROTOR DISC, AND TURBOMACHINE ASSEMBLY - A blade root including of a plurality of lobes and fillets and flanks in between is provided. A shoulder is provided between the flanks and the fillets to increase the distance to a corresponding lobe of a corresponding rotor disc into which a blade with such a blade root is inserted. A rotor blade having such a blade root is also provided. Furthermore this feature may alternatively or additionally also be applied to a rotor disc slot of a rotor disc, such that a flank of the rotor disc slot merges into a fillet of the rotor disc slot via a soft shoulder to increase the distance to a corresponding lobe of a blade root. A shoulder could also be applied to both the blade root and the corresponding slot of the rotor disc. | 05-22-2014 |
| 20140169975 | ROTOR BLADE ROOT SPACER WITH A FRACTURE FEATURE - A rotor assembly is provided that includes a rotor disk, a rotor blade and a root spacer. The rotor disk includes a slot. The rotor blade includes a blade root that is arranged within the slot. The root spacer is arranged within the slot between the rotor disk and the blade root. The root spacer includes a base segment, a side segment and a fracture feature. The base segment radially engages the rotor disk. The side segment is radially separated from the rotor disk by a gap. The fracture feature may radially fracture the root spacer at an intersection between the base segment and the side segment. | 06-19-2014 |
| 20140169976 | ROTOR BLADE ROOT SPACER FOR ARRANGING BETWEEN A ROTOR DISK AND A ROOT OF A ROTOR BLADE - A rotor assembly is provided that includes a rotor blade, a root spacer, and a rotor disk with a slot. The rotor blade includes a blade root arranged within the slot. The blade root includes a root base segment and a pair of root side segments. The root base segment is laterally separated from the rotor disk by the root side segments. The root spacer is arranged within the slot, and includes a side surface that extends radially between an inner surface and an outer surface. The side surface is approximately laterally aligned with an intersection between the root base segment and a first of the root side segments. The outer surface engages the root base segment. | 06-19-2014 |
| 20140186187 | NON-INTEGRAL FAN BLADE PLATFORM - Described are a gas turbine engine fan blade platform, related rotor assembly and gas turbine engine, as well as a method of assembling the same. The platform has a forward portion proximal to an axis of rotation, an aft portion, and a transition portion between the forward and aft portions. The forward portion has a forward interface surface facing axially forward, the aft portion has an aft interface surface facing radially outward, and the transition portion has at least one mounting feature. For the method of assembly, an aft support is installed on a fan disk and booster spool assembly. A plurality of fan blades are installed into a fan disk, followed by installing a fan platform between adjacent blades and securing the mounting features to the disk, thereby filling the annulus of the fan disk. Finally, a forward support is installed on the fan disk. | 07-03-2014 |
| 20140199172 | TURBOMACHINE AND METHOD OF HANDLING TURBOMACHINE COMPONENTS - A turbomachine is provided and includes a blade wheel having an outer radial portion defining first and second nested pockets, a blade having a root section, which is receivable in the first pocket and thereby securable in the first pocket in circumferential and radial dimensions and an insert, which is receivable in the second pocket and configured to secure the root section in an axial dimension with positive retention. | 07-17-2014 |
| 20140212295 | SPINNER ASSEMBLY WITH REMOVABLE FAN BLADE LEADING EDGE FAIRINGS - A gas turbine engine spinner assembly including a spinner defining at least in part an aerodynamically smooth surface, a shell defining at least in part the aerodynamically smooth surface, and circumferentially spaced apart removable aerodynamic fairings located around the shell. Fairing shanks disposed in circumferentially spaced apart axially extending slots in the shell may be attached to the aerodynamic fairings. The fairings may shield radially extending portions of the fan blades including portions of blade shanks or portions of transition regions of the blade shanks. The fairing shanks may be disposed between and monolithically formed with the fairings and fairing roots attached to the fairing shanks. The fairings may be made of an injectable thermoplastic and the shell made of metal. The fairing shanks may be setback from fairing forward tips and the fairing shanks may be setback from root forward tips of the fairing roots. | 07-31-2014 |
| 20140219805 | LOW RADIUS RATIO FAN FOR A GAS TURBINE ENGINE - A fan blade for a gas turbine engine includes: a straight axial dovetail, an airfoil, and a transition section disposed between the dovetail and the airfoil, the fan blade having opposed pressure and suction sides, and further including at least one shoulder protruding from a nominal surface of a selected one of the pressure and suction sides, wherein the at least one shoulder includes a boss defining a side face, and an upper section extending radially outward from the boss and tapering inward to join a nominal surface of the selected side. | 08-07-2014 |
| 20140219806 | ROTOR BLADE SUPPORT STRUCTURE - The purpose of the invention is to provide a rotor blade support structure, wherein the concentration of stress near the rotor blade groove in which the rotor blade is embedded is limited even as increase in production cost is limited. A rotor blade support structure, in which rotor blades ( | 08-07-2014 |
| 20140241891 | TURBOMACHINE BLADE AND RELATIVE PRODUCTION METHOD - A turbomachine blade having a metal coupling root, and a metal airfoil-shaped oblong member cantilevered from the coupling root; the airfoil-shaped oblong member being divided into: a lower connecting fin cantilevered from and formed in one piece with the coupling root; an upper connecting fin cantilevered from a coupling head towards the coupling root and formed in one piece with the coupling head; and a main plate-like body which is shaped and positioned between the two connecting fins to form an extension of the fins, and is butt-welded to the same connecting fins to form one piece with the fins. | 08-28-2014 |
| 20140241892 | TURBOMACHINE BLADE AND RELATIVE PRODUCTION METHOD - A turbomachine blade of the type having a metal lower coupling root, a metal upper coupling head, and a metal airfoil-shaped oblong member designed to connect the coupling root rigidly to the coupling head; the airfoil-shaped oblong member having a substantially airfoil-shaped main plate-like element connected to the coupling root and to the coupling head, and which is divided into: a lower connecting fin cantilevered from and formed in one piece with the coupling root; an upper connecting fin cantilevered from and formed in one piece with the coupling head; and a center plate-like body, which is located between the lower and upper connecting fins, is shaped/designed to form an extension of the lower and upper connecting fins, and is butt-welded to, to form one piece with, the lower and upper connecting fins. | 08-28-2014 |
| 20140286781 | INTEGRAL FAN BLADE WEAR PAD AND PLATFORM SEAL - A fan section for a gas turbine engine includes a fan hub having a slot. A platform is supported by the fan hub. A fan blade has a root that is received in the slot. A wear pad is provided between the fan hub and the root and includes a flap integral with the wear pad to provide a seal relative to the platform. A fan blade for a gas turbine engine includes an airfoil extending from a root. A wear pad is secured to the root and has a free end providing a flap canted toward the root. | 09-25-2014 |
| 20140308134 | TURBOMACHINE VANE COOPERATING WITH A VANE RETENTION DISK - A turbomachine vane for cooperating with a vane retention disk including a plurality of peripheral teeth, the vane including a shank including a neck and a bulb for cooperating with a socket of the disk so as to radially hold the shank in the socket, the socket being a space bounded by two successive teeth of the disk, a pole on top of the neck, including two side walls facing the active surface side of the vane and two side walls facing the passive surface side of the vane, each wall having a rib at a lower end of the pole, the rib extending in the direction of the side wall facing the wall and providing a function of holding the vane when the vane is retained in the disk. | 10-16-2014 |
| 20140356176 | ROTOR BLADE ASSEMBLY HAVING A STIFFENING ROOT INSERT - A rotor blade assembly for a wind turbine having a rigid root insert is disclosed. The rotor blade assembly includes a blade root section having an end face with a substantially annular cross-section defined by an outer sidewall surface and an inner sidewall surface. The end face is configured to attach the rotor blade assembly to a hub. The rotor blade assembly includes a radial bore hole provided a predetermined span-wise distance from the end face and extending between the sidewall surfaces and a longitudinal bore hole provided between the sidewall surfaces and extending from the end face to the radial bore hole. The rigid root insert is disposed within the longitudinal bore hole and extends from the end face to the radial bore hole. As such, the rigid root insert is configured to increase the stiffness of the blade root section when the rotor blade assembly is attached to the hub with bolts that extend into and through the radial bore hole and the longitudinal bore hole. | 12-04-2014 |
| 20150017004 | MOUNTING IN HUB FOR BLADES OF A HYDRO TURBINE - A hydro turbine assembly includes a hub configured to rotate about a center axis and configured to be mounted in a water passage. The hub includes an upstream end, a downstream end and an outer surface between the upstream and downstream ends. The hub includes at least three mounting recesses arranged in the outer surface wherein each mounting recess includes a first hub mounting surface and a second hub mounting surface, and the second hub mounting surface is downstream and radially inward of the first hub mounting surface. The assembly includes at least three runner blades each including a base configured to seat in a respective one of the mounting recesses, wherein the base includes a first blade mounting surface arranged to abut the first hub mounting surface and a second blade mounting surface arranged to abut the second hub mounting surface. | 01-15-2015 |
| 20150064012 | BLADE OF A ROTARY FLOW MACHINE WITH A RADIAL STRIP SEAL - The invention refers to a blade of a rotary flow machine including an airfoil having a suction surface and a pressure surface joining each other along a trailing and a leading edge. A radially outward directed airfoil tip and a radially inward directed end joining an inner platform connect the airfoil to a shank at a radial end of the airfoil and providing, at least one shank pocket radially encircled by an axially extending portion of the platform. At least one radially extending rim extends from the trailing edge side of the shank and has an essentially radially orientated first slot for receiving a seal. A mount extends radially inwardly from said shank pocket. The first slot has a first aperture on a shank surface orientated in an axial direction. | 03-05-2015 |
| 20150078906 | FAST ASSEMBLING CEILING FAN BLADES - Fast assembling ceiling fan blades includes a motor housing having its outer circumferential side longitudinally provided with a plurality of gaps respectively secured therein with plural transverse engage blocks. A plurality of blades respectively have one side formed with a plurality of transverse guide grooves corresponding with the engage blocks of the gap, and each guide groove has its bottom extending upward to form an engage slot. Thus, one side of the blade, which corresponds to the engage blocks of the gap, can be pushed and fixed in the gap to have the engage blocks moved along the guide grooves and guided into the engage slots to enable the blade to be firmly engaged in the gap of the motor housing for quickly assembling the blades, simple, time-saving and convenient in assembly and disassembly of the ceiling fan blades. | 03-19-2015 |
| 20150098830 | ASSEMBLY FIXTURE FOR A STATOR VANE ASSEMBLY - A fixture for assembling a stator vane assembly for a gas turbine engine includes, an outer locating ring including a plurality of outer locating pins defining a position for each of a plurality of vanes relative to an outer fairing. An inner locating ring includes a plurality of inner locating rings defining a position of each of the plurality of vanes relative to an inner fairing. A clamp section includes a clamp portion and a clamp pin defining an angular orientation of each of the plurality of vanes relative to each of the inner and outer fairings. An inner locating section supports a plurality of radial locating pins defining a radial position of each of the plurality of vanes relative to the inner and outer fairings. | 04-09-2015 |
| 20150098831 | ROTOR BLADE ARRANGEMENT AND GAS TURBINE - A rotor blade arrangement ( | 04-09-2015 |
| 20150104319 | TURBINE WITH BUCKET FIXING MEANS - Provided is a turbine including a rotor wheel including a plurality of dovetail grooves and a insertion groove, the insertion groove including a first catching groove; a plurality of first buckets, each of the plurality of 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 the dovetail groove; a second bucket including a vane, a platform provided at a first end portion of the vane, and a protrusion portion and configured to be inserted into the insertion groove, the protrusion portion including a second catching groove; and a fixing member configured to be inserted into each of the first and second catching grooves, the fixing member configured to restrict radial movement of the second bucket. | 04-16-2015 |
| 20150292336 | Root Lightening Holes with Slot - An airfoil includes a dovetail root having a base. A grooved slot is disposed in the base and a plurality of root lightening cavities is disposed in the grooved slot. | 10-15-2015 |
| 20150300181 | AEROFOIL BLADE - A turbomachine aerofoil blade has an aerofoil body portion and a dovetail root fixing at the base of the aerofoil body portion which slides, in use, into a correspondingly shaped slot of a rotor of the turbomachine. The dovetail root fixing has a neck portion, and support flanks engage with matching angled surfaces of the slot under centrifugal loading of the aerofoil blade to support the aerofoil blade on the rotor. The neck portion is shaped such that a rotational adjustment of the aerofoil blade relative to its angular position when supported under centrifugal loading is needed to provide adequate clearance at the neck portion to allow the dovetail root fixing to slide into the slot. On centrifugal loading the engagement of the support flanks with the matching angled surfaces of the slot forces a reversal of the rotational adjustment and reduces the clearance at the neck portion. | 10-22-2015 |
| 20150308287 | RECESSABLE DAMPER FOR TURBINE - A turbine blade damping system for a turbine includes a turbine blade platform and a damper recessable within a pocket defined by the platform. An underside of the platform defines a beveled surface. An outer side of the damper defines a complementary beveled surface. When the turbine spools up, centrifugal force acting on the damper forces it in an outward direction from the pocket toward a mating surface of an adjacent turbine blade platform. | 10-29-2015 |
| 20150330233 | BLADE ANCHORED SECURELY IN RADIAL TRANSLATION, PROPELLER, TURBINE ENGINE AND AIRCRAFT - A blade includes an aerodynamic portion ( | 11-19-2015 |
| 20150361798 | FAN BLADE INCLUDING EXTERNAL CAVITIES - A blade of a gas turbine engine includes a blade portion. The blade portion includes a first portion located radially outwardly that is located in a flow path and a second portion located radially inwardly of the first portion that is not located in the flow path. A plurality of external cavities is in the second portion of the blade portion. | 12-17-2015 |
| 20150361803 | TURBOMACHINE ROTOR BLADE, TURBOMACHINE ROTOR DISC, TURBOMACHINE ROTOR, AND GAS TURBINE ENGINE WITH DIFFERENT ROOT AND SLOT CONTACT FACE ANGLES - A turbomachine rotor blade has a firtree shaped root, to be secured in a rotor disc rotatable around a rotor axis. In a plane perpendicular to the rotor axis, the root has a first, second, and third root lobe with a first, second, and third root contact face. Each of the first, second, and third root contact face is angled relative to a radial root bottom axis with a first, second, and third root angle, respectively. The first root angle is smaller than the second and the second root angle is substantially equal to the third. A turbomachine rotor disc has a firtree shaped slot having a first, second, and third slot angle, the first slot angle being smaller than the second and the second slot angle being substantially equal to the third. A gas turbine engine has the turbomachine rotor herein. | 12-17-2015 |
| 20150361805 | ROTOR BLADE ROOT SPACER WITH GRIP ELEMENT - An assembly includes a rotor disk, a rotor blade and a root spacer. The rotor disk includes a slot that extends longitudinally into the rotor disk. The rotor blade includes a blade root arranged within the slot. The root spacer is arranged with the slot between the rotor disk and the blade root. The root spacer extends longitudinally to a spacer end, and includes a grip element and a plurality of notches. The grip element is arranged at the spacer end laterally between the notches. The grip element at least partially defines the notches. The notches extend radially and longitudinally into the root spacer. | 12-17-2015 |
| 20150369048 | TURBINE BLADE AND DAMPER RETENTION - A gas turbine engine rotor assembly has a plurality of blades spaced apart from each other for rotation about an axis. Each of the blades includes a platform having an inner surface and an outer surface. The inner surfaces of adjacent platforms define a pocket having a radially outer wall, a pressure side wall, and a suction side wall. The pocket includes a leading edge wall portion and a trailing edge wall portion, and a shelf extending in a tangential direction relative to the axis from the pressure side of the pocket. The shelf is spaced apart from the radially outer wall. | 12-24-2015 |
| 20150377027 | FAN DISC - A fan disc is provided for supporting fan blades of a gas turbine engine. The fan disc has a disc body having axially extending slots for receiving, in use, dovetail root fixings of a circumferential row of fan blades. The fan disc further has an annular drive arm which extends radially inwardly from a forward portion of the disc body to a connector for engaging, in use, with a corresponding connector portion of a drive shaft of the engine. The fan disc further has a hoop stiffening ring which is removably mounted to a rear portion of the disc body, the stiffening ring being axially spaced from the drive arm to increase the torsional stiffness of the fan disc. | 12-31-2015 |
| 20160003067 | Aluminum Fan Blades with Root Wear Mitigation - A fan blade assembly with wear mitigation characteristics is disclosed. In a titanium hub, dovetail shaped slots are used for accommodating dovetail shaped roots of fan blades. At least the inwardly facing walls of the dovetail shaped slots are coated with a dry film lubricant. The inwardly directed pressure faces of the dovetail shaped root of the fan blades are covered with polymeric wear mitigation pads. The combination of wear mitigation pads on the pressure faces of the root of the fan blade in combination with a dry film lubricant coating on the inwardly directed walls of the dovetail shaped slots in the hub provide excellent wear mitigation characteristics and prolong the life of the fan blades. | 01-07-2016 |
| 20160024946 | ROTOR BLADE DOVETAIL WITH ROUND BEARING SURFACES - A blade for use in a gas turbine engine, the blade having an airfoil portion and a dovetail root portion, wherein the dovetail root portion is dimensioned and configured to enable the blade to rotate within a shaped slot formed in a supporting hub of the engine about a center of rotation that extends parallel to a central axis of the hub in response to an impact force on the airfoil portion of the blade. | 01-28-2016 |
| 20160024947 | Blade Wear Pads and Manufacture Methods - A blade assembly comprises a blade ( | 01-28-2016 |
| 20160032751 | REVERSIBLE BLADE ROTOR SEAL - A rotatable sealing structure for a gas turbine engine includes a first blade and a second blade. A seal is arranged between the blades and has a body that is configured for operative association with the first and second blades in a first orientation and in a second orientation to seal a gap defined between the blades. | 02-04-2016 |
| 20160040541 | LIGHTWEIGHT BLADE FOR GAS TURBINE ENGINE - A blade for use in a gas turbine engine has an airfoil and a dovetail. The airfoil extends radially outwardly of the dovetail. An inner surface of the dovetail includes a slot extending along a length of the dovetail between a leading edge and a trailing edge. A rotor and a gas turbine engine are also disclose | 02-11-2016 |
| 20160061040 | COMPOSITE FAN SLIDER WITH NANO-COATING - A fan slider for use in a fan assembly to push a fan blade radially outward of a rotating axis of the gas turbine engine. The fan slider may include a fan slider body coated with a nanocrystalline metallic coating and a slider spring. | 03-03-2016 |
| 20160069203 | INTEGRALLY BLADED ROTOR - An integrally bladed rotor for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a radially inner hoop extending circumferentially about an axis, a plurality of circumferentially spaced, axially extending slots, separated by respective blade supports, and a seal system that includes seal fingers extending axially through the slots. | 03-10-2016 |
| 20160084086 | GAS TURBINE ENGINE - A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system comprises a fan case having an annular casing element for encircling an array of fan blades and a hook projecting in a generally radially inward direction from the annular casing element. An annular fan track liner is provided comprising a first fan track liner panel positioned circumferentially adjacent a second fan track liner panel. A coupling connects the first fan track liner panel to the second fan track liner panel and the first fan track liner panel and the second fan track liner panel each comprise a groove along an axial face thereof and a portion of the coupling is received in each of said grooves. | 03-24-2016 |
| 20160130956 | TURBOMACHINE ROTOR ASSEMBLY AND METHOD - A turbomachine assembly is shown, including a rotor and a ring of blades mounted on the rotor. Each blade includes an airfoil portion and a root portion inserted in a circumferential blade-retaining groove of the rotor. The blade-retaining groove includes an enlarged groove portion. The blades in the enlarged groove portion are rotatable around a respective, generally radial axis, to take a position of minimum tangential dimension. At least one removable insert is arranged along the enlarged groove portion, between the root portions of the blades located in the enlarged groove portion and a side wall of the blade-retaining groove, to force and lock the blades in a final assembled arrangement. | 05-12-2016 |
| 20160131144 | CENTRIFUGAL COMPRESSOR APPARATUS - A compressor has an axial portion and a centrifugal portion. A disk structure is provided to support the centrifugal portion and is connected to the centrifugal portion with a rabbet joint. | 05-12-2016 |
| 20160152319 | PROPELLER BLADE MOUNTING SYSTEM | 06-02-2016 |
| 20160160662 | TURBINE AIRFOIL ATTACHMENT WITH SERRATION PROFILE - An attachment root of an airfoil is provided. The attachment root may comprise a serration profile, a symmetry plane bisecting the serration profile, and a line perpendicular to the symmetry plane. A first lobe of the serration profile may have a first contact face angled 135 degrees from the line. A second lobe of the serration profile may have a second contact face angled 135 degrees from the line. A third lobe of the serration profile may have a third contact face angled 135 degrees from the line. | 06-09-2016 |
| 20160160663 | PLATFORM OF SMALL HUB-TIP RATIO - A platform for a bladed wheel having a small hub-tip ratio, suitable for being fabricated out of composite material from a three-dimensionally woven fiber preform, the platform including a bottom wall, a top wall defining an air flow passage, and two side walls extending transversely between the bottom wall and the top wall, wherein the side walls extend longitudinally beyond the upstream end of the bottom wall. The platform further includes a fastener tab that is folded from the upstream end of the bottom wall. | 06-09-2016 |
| 20160167767 | ROTOR HUB FOR ROTARY WING AIRCRAFT | 06-16-2016 |
| 20160169007 | APPARATUS HAVING ENGINEERED SURFACE FEATURE AND METHOD TO REDUCE WEAR AND FRICTION BETWEEN CMC-TO-METAL ATTACHMENT AND INTERFACE | 06-16-2016 |
| 20160169011 | TURBINE AIRFOIL ATTACHMENT WITH MULTI-RADIAL SERRATION PROFILE | 06-16-2016 |
| 20160177749 | BLADING MEMBER FOR A FLUID FLOW MACHINE | 06-23-2016 |
| 20160186581 | TURBINE WHEELS WITH PRELOADED BLADE ATTACHMENT - A wheel assembly for a gas turbine engine is disclosed. The wheel assembly includes a disk arranged for rotation about a central axis and formed to include a plurality of slots. The wheel assembly also includes a plurality of blades sized to be received in the plurality of slots so that the blades are coupled to the disk for common rotation about the central axis. The wheel assembly further includes a plurality of blade biasers positioned in the slots between the disk and the blades so that the blade biasers are engaged with the disk and the blades to preload the blades away from the central axis. | 06-30-2016 |
| 20160186582 | TURBOMACHINE ROTOR WITH OPTIMISED BEARING SURFACES - The invention relates to a turbomachine rotor including a disk and at least one blade wherein the root comprises a bulb accommodated into a groove associated with the disk, wherein the bulb includes a slot that opens up radially inwards at its lower face, and in that the rotor includes a retaining part extending partly into the groove projecting radially outwards from the bottom face of the groove, of which a radially outer end of the retaining part fits into the slot of the bulb and bears radially inwards on the inner wall of the slot of the bulb. | 06-30-2016 |
| 20160186583 | GAS TURBINE ENGINE CMC AIRFOIL ASSEMBLY - A gas turbine engine airfoil assembly includes an airfoil and an attachment structure respectively bonded to opposing sides of a platform. At least one of the airfoil, the platform and the attachment structure are constructed from a ceramic matrix composite. | 06-30-2016 |
| 20160251963 | ROTOR BLADE VIBRATION DAMPER | 09-01-2016 |
| 20160251972 | CERAMIC ATTACHMENT CONFIGURATION AND METHOD FOR MANUFACTURING SAME | 09-01-2016 |
| 20180023585 | IMPELLER ATTACHMENT METHOD | 01-25-2018 |
| 20090220344 | Propeller Blade Retention Device - A propeller blade retention system and method of manufacture are disclosed. Because of the design, a truly integral hub is able to house a set of variable pitch blades. Each hub socket establishes a substantially cylindrical interface with its respective blade, making the blade slidably receivable for installation. Each blade is allowed axial rotation, and held inside the socket by a set of angular contact bearings. A snap ring locks the blade against coming back out of the socket. An O-ring is provided in the interface to create a fluid seal. The hub alone accomplishes all of the required load-bearing and weather-seal functions. | 09-03-2009 |
| 20100104443 | PROPELLER BLADE RETENTION - A propeller blade assembly having mounting arrangements for composite aircraft propeller blades. | 04-29-2010 |
| 20120141281 | WIND TURBINE ROTOR BLADE ASSEMBLY WITH ROOT CURTAIN - A wind turbine rotor blade assembly includes a rotor blade having a pressure side, a suction side, a leading edge, and a trailing edge extending in a generally span-wise direction between a tip and a root. An edge extension is attached along either or both of the leading edge or trailing edge in a generally span-wise direction from adjacent the root towards the blade tip, with the edge extension having a contoured outer surface that defines a generally continuous aerodynamic surface. The edge extension has a terminal end that is spaced from root. A curtain is attached to the edge extension and extends in a span-wise direction from the terminal end t to the root. The curtain is formed from a pliant, flexible material that accommodates connection of the root to a rotor hub, as well as pitch movement of the rotor blade relative to the hub. | 06-07-2012 |
| 20130177428 | BLADE CONNECTION OF A ROTOR BLADE OF A WIND TURBINE - A fastening element ( | 07-11-2013 |
| 20140212294 | CEILINF FAN BLADE - A ceiling fan blade includes a lower blade and an upper blade combined together. The lower blade is provided with a recess and secured thereon with a plurality of engage fasteners, and the upper blade is formed with a recess and embedded therein with a plurality of engage posts respectively corresponding with the engage fasteners. The engage post is engaged with the engage fastener to form a one-way engagement for reinforcing combination of the upper blade with the lower blade. The ceiling fan blade of this invention can not only conform to environmental protection but also avoid being broken apart when used to insure safety in use. In addition, the ceiling fan blade of this invention is hollow in structure, able to lighten the blade, and no locking member is provided on the surface of the blade, able to keep beautiful external features of the ceiling fan. | 07-31-2014 |
| 20160017727 | FAN BLADE DOVETAIL AND SPACER - A blade according to an exemplary aspect of the present disclosure includes, among other things, a radially inner dovetail supporting a radially outer airfoil; and the dovetail having a radial thickness which is less in a circumferentially center portion of the dovetail than circumferentially opposing outer edges. | 01-21-2016 |
| 20160053771 | FAN AND MOULD FOR MAKING THE SAME - Embodiments of the application disclose a fan and a mould for making a fan blade structure for the fan. An embodiment of the fan comprises a fan blade structure and the fan blade structure comprises a mounting ring and a plurality of fan blades provided on the mounting ring, wherein mounting ring and the fan blades are integrally formed. The mould comprises a mounting ring and a plurality of fan blades provided on the mounting ring, the mould comprising a cavity having a ring-shaped channel configured for forming the mounting ring and a plurality of fan blade channels configured for forming the plurality of fan blades, in order to integrally form the fan blade structure. | 02-25-2016 |
