| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 416193000 | Spaced inwardly of impeller periphery | 67 |
| 20080232968 | NON-AXISYMMETRIC END WALL CONTOURING FOR A TURBOMACHINE BLADE ROW - A turbomachine blade row is provided having a hub that includes a non-axisymmetric end wall modified by a transformation function. The blade row further includes a circumferential row of a plurality of airfoil members radially extending from the non-axisymmetric end wall of the hub and forming a plurality of sectoral passages there between. A radius of the non-axisymmetric end wall is determined by a transformation function including a plurality of geometric parameters defined by a user based on flow conditions. The plurality of geometric parameters provide for modification of the end wall in both an axial and a tangential direction to includes a plurality of concave profiled regions and convex profiled regions. | 09-25-2008 |
| 20100166558 | METHODS AND APPARATUS RELATING TO IMPROVED TURBINE BLADE PLATFORM CONTOURS - A flow directing assembly for use in a turbine engine comprising: a plurality of circumferentially spaced blades, each of the blades including a radial projecting airfoil with a concave pressure side and a convex suction side that extend from a platform; and a plurality of flow passages, each flow passage defined by the airfoils of neighboring blades and an inner wall formed by abutting platforms of neighboring blades, the inner wall forming the inner radial boundary of the flow passage; wherein the inner wall of one or more of the flow passages comprises means for reducing frictional losses between the flow through the turbine engine and the inner wall. The means for reducing frictional losses may comprise a non-axisymmetrical trough positioned between neighboring airfoils that is configured to reduce frictional losses. | 07-01-2010 |
| 20100290910 | ANNULUS FILLER - An annulus filler for mounting to a rotor disc of a gas turbine engine bridges the gap between adjacent disc blades. The annulus filler has a lid defining part of an airflow surface for air drawn through the engine; a separate support connectable to the lid and to the rotor disc with an engagement portion of the support extending radially past a substantially adjacent region of the lid; and a retainer configured to interconnect the lid and the support by engaging each engagement portion of the support and adjacent regions of the lid, the retainer defining another part of the airflow surface. The annulus filler can be configured to allow mounting to the rotor disc, where the support is connected to the rotor disc without the lid, and then the lid is mounted to the support such that each engagement portion remains visible from the lid's radially outermost side. | 11-18-2010 |
| 20110182737 | HEAT DISSIPATION FAN AND ROTOR THEREOF - A rotor includes a hub, rotary blades extending outwardly from the hub, and an annular wall surrounding the rotary blades. Each rotary blade includes a windward lateral surface and a leeward lateral surface at opposite sides thereof. The annular wall adjoins the outer ends of the rotary blades and is rotatable therewith. A perforation is defined in the annular wall between two neighboring rotary blades and adjacent to the leeward lateral surface of a leading rotary blade of the neighboring rotary blades. | 07-28-2011 |
| 20120014800 | FAN ASSEMBLY - A fan assembly according to an exemplary embodiment of the present invention includes: a hub; and a plurality of blades including a leading edge corresponding to a side hit by air and a trailing edge corresponding to an opposite side of the leading ledge, the plurality of blades configured to be extended radially from an outer peripheral surface of the hub, wherein each of the plurality of blades includes a first part extended radially from the outer peripheral surface of the hub, a bent part stepped on the end of the first part, and a second part further extended radially on the end of the bent part. | 01-19-2012 |
| 20120027598 | ROTOR COVER PLATE RETENTION METHOD - A mechanism for use in a gas turbine engine has a cover plate, a rotor disk, a first slot in the cover plate, a second slot in the rotor disk, a first finger in the cover plate extending through the second slot, and a second finger in the rotor disk extending through the first slot. The first finger and the second finger form a channel and a holder is disposed in the channel for locking the rotor disk and the cover plate together | 02-02-2012 |
| 20120121425 | ANNULAR TURBINE RING ROTOR - A fan-turbine rotor assembly includes one or more turbine ring rotors. Each turbine ring rotor is cast as a single integral annular ring. By forming the turbine as one or more rings, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine ring rotors to the diffuser ring includes axial installation and radial locking of each turbine ring rotor. | 05-17-2012 |
| 20130108448 | TURBINE BUCKET PLATFORM SHAPING FOR GAS TEMPERATURE CONTROL AND RELATED METHOD | 05-02-2013 |
| 20130170995 | AXIAL FLOW FAN BLADE STRUCTURE AND AXIAL FLOW FAN THEREOF - An axial flow fan blade structure and an axial flow fan thereof. The axial flow fan blade structure includes a fan impeller and an annular body. The fan impeller has a hub and multiple blades. Each blade has a first flow guide face and a second flow guide face opposite to the first flow guide face. The annular body is disposed on the blades. The annular body outward extends from the first and second flow guide faces and is annularly connected with the blades along the blades. The annular body not only is able to increase the strength of the blades of the axial flow fan, but also is able to reduce vibration and noise made by the axial flow fan. | 07-04-2013 |
| 20130189107 | Turbine Packing Deflector - A turbine includes a rotor being rotatable about an axis, a circumferential array of nozzles having circumferentially spaced airfoils and inner and outer bands disposed at opposite ends thereof, the inner band having a leading portion and a trailing portion, and an array of directors arranged on the inner band, the array of directors operative to direct a flow path of fluid, the flow path of fluid partially defined by the rotor and the inner band. | 07-25-2013 |
| 20140086751 | ANNULUS FILLER FOR AXIAL FLOW MACHINE - A fluid-washed assembly for an axial flow machine, such as a fan blade assembly for a gas turbine engine. The assembly has an array of members circumferentially spaced about the machine axis, each member extending from a radially inner end to a radially outer end with respect to the axis of rotation of the machine. Each member has opposing outer surfaces extending between a leading edge and a trailing edge thereof with respect to the direction of oncoming fluid flow in use. A plurality of annulus fillers are provided between each member, wherein each annulus filler is affixed against an outer surface of an associated member at a location between the inner and outer ends in a manner which supports the annulus filler in use. In preferred embodiments, the annulus fillers comprise a composite material which is bonded to the associated member using an adhesive. | 03-27-2014 |
| 20140154083 | FAN BLADE WITH FLEXIBLE AIRFOIL WING - A fan assembly is disclosed that includes one or more fan blades, each fan blade having a flexible airfoil wing. A curved, flexible wing is connected to a main spar element located between the upper and lower portions of the curved, flexible wing element. The curved, flexible wing forms the entire upper surface of the wing, the entire leading edge of the wing, and a portion of the lower surface of the wing. | 06-05-2014 |
| 20150050151 | ANNULUS FILLER - An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc, The annulus filler has an outer lid which defines an airflow surface for air being drawn through the engine, the lid having a leading edge and a trailing edge in an axial airflow direction. The annulus filler further has a support arrangement which is connectable to the rotor disc. The support arrangement includes a first engageable portion at the leading edge of the lid and a second engageable portion at the trailing edge of the lid. The engageable portions engage in use with respective adjacent parts of the gas turbine engine, and have respective galvanic corrosion barriers, which prevent or reduce galvanic corrosion between the material of the lid and the respective adjacent engine parts. | 02-19-2015 |
| 20150300194 | ANNULUS FILLER - An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc. The annulus filler is substantially entirely formed from a polymer matrix composite material. It has an outer lid which defines an airflow surface for air being drawn through the engine in an axial airflow direction, and a support structure which is connectable to the rotor disc to support the lid on the rotor disc. The support structure has two support walls extending from opposing lateral sides of the lid to an attachment strap for receiving a hook on the rotor disc, the attachment strap bridging the support walls. In use, under centrifugal loads, the opposing support walls resiliently deform to allow outward radial movement of the lid. Each support wall is thickened in a region neighbouring the attachment strap. | 10-22-2015 |
| 20160047261 | COMPOSITE FAN ANNULUS FILLER WITH NANO-COATING - According to the present disclosure, an fan annulus filler for use in a fan assembly of a gas turbine engine may include an annulus filler body formed of a polymer. The annulus filler body may include a surface coated with a nanocrystalline coating to form a flow surface. | 02-18-2016 |
| 20160130957 | TURBINE BLISK INCLUDING CERAMIC MATRIX COMPOSITE BLADES AND METHODS OF MANUFACTURE - In some embodiments, an apparatus includes a disk, a coupling member and a set of blades. The coupling member has a first surface and a second surface, and defines a set of openings between the first surface and the second surface. The first surface is configured to be coupled to the outer surface of the disk. A portion of each blade from the set of blades is disposed within an opening from the set of openings when the first surface of the coupling member is coupled to the outer surface of the disk such that the blade is coupled to the disk. | 05-12-2016 |
| 20160186592 | FLOWPATH BOUNDARY AND ROTOR ASSEMBLIES IN GAS TURBINES - A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a first axial section of an inner boundary of the flowpath; a second rotor wheel supporting a second rotor blade having a platform that defines a second axial section of the inner boundary of the flowpath; and an annulus filler that includes an outboard surface that defines at least part of a third axial section of the inner boundary of the flowpath occurring between the first axial section and the second axial section of the inner boundary of the flowpath. The first rotor wheel may include an axial connector for axially engaging a mating surface formed on a radially innermost face of the first rotor blade and a mating surface formed on a radially innermost face of the annulus filler. | 06-30-2016 |
| 20080286106 | TURBINE ROTOR BLADE ASSEMBLY AND METHOD OF FABRICATING THE SAME - A removable rotor blade platform includes a first platform leg, a second platform leg, and a platform portion coupled to the first and second platform legs. The first platform leg is configured to be retained by a first retainer coupled to a first rotor blade, and the second platform leg is configured to be retained by a second retainer coupled to a second adjacent rotor blade. A method of assembling a blade assembly that includes a removable platform, a rotor assembly including the removable platform, and a gas turbine engine assembly including the removable platform, are also described herein. | 11-20-2008 |
| 20090123286 | ASSEMBLY OF A FAN BLADE AND OF ITS DAMPER, FAN BLADE DAMPER AND METHOD FOR CALIBRATING THE DAMPER - The invention relates to a fan blade assembly of a turbojet with fan and a fan blade damper, the fan blade comprising a root and a platform, the fan blade damper being suitable for being attached in a housing formed in the lower face of the platform, said housing comprising an upstream side perpendicular to the root of the blade. The damper comprises a front edge of which a first portion is parallel to the upstream side of the housing and of which a second portion is inclined relative to said upstream side. The invention also relates to a fan blade damper and a method for calibrating said damper. | 05-14-2009 |
| 20090148295 | Gas Turbine Engine Systems Involving Rotor Bayonet Coverplates and Tools for Installing Such Coverplates - Gas turbine engine systems involving rotor bayonet coverplates and tools for installing such coverplates are provided. In this regard, a representative turbine assembly for a gas turbine engine includes: a turbine disk operative to mount a set of turbine blades; and a coverplate having an annular main body portion and a spaced annular arrangement of tabs extending radially inwardly from the main body portion with open-ended gaps being located between the tabs, the tabs being operative to secure an inner diameter of the coverplate to the turbine disk. | 06-11-2009 |
| 20100054942 | BLADE ASSEMBLY - Blade assemblies are provided in a number of forms. These blade assemblies may have blades secured to disks (blisk), rings (bling) and drums (blum). The blades and/or the rotor elements formed by these rings, drums or disks can fragment and it is necessary to contain such fragments within a casing. Impact energy has a significant effect upon the necessary thickness of the casing to ensure containment. By providing blades as well as rotor elements which incorporate discontinuities which provide flexing under impact, energy is absorbed prior to further fragmentation upon impact engagement with a casing surface; flexing is about the discontinuity. In such circumstances casings may be thinner and therefore significant weight savings achieved with regard to aircraft incorporating gas turbine engines having blade assemblies with discontinuities. | 03-04-2010 |
| 20100124502 | ROTOR BLADE ARRANGEMENT AND GAS TURBINE - A rotor blade arrangement ( | 05-20-2010 |
| 20100143140 | FLUID FLOW MACHINE WITH SIDEWALL BOUNDARY LAYER BARRIER - A fluid flow machine has a main flow path in which at least one row of blades ( | 06-10-2010 |
| 20100209251 | FAN BLADE PLATFORM - A fan blade platform assembly comprises a plate insert shaped and dimensioned to span a gap formed between the opposed facing platforms of adjacent fan blades of a turbo fan engine. The plate insert can be retained in engagement under arresting shoulders provided on the adjacent fan blades by a spring force exerted by a spring insert held captive and in contact between the plate insert and an outer surface of the fan hub. | 08-19-2010 |
| 20100221113 | INTERNALLY-DAMPED AIRFOIL AND METHOD THEREFOR - An airfoil component and method for producing the component. The component has root and airfoil portions, the latter having an airfoil tip and oppositely-disposed concave and convex surfaces that converge at leading and trailing edges of the airfoil portion. The airfoil portion has at least one stiffener between first and second walls thereof that define the concave and convex surfaces, respectively. The stiffener defines multiple internal cavities within the airfoil portion that extend in the span-wise direction of the airfoil portion. A polymeric material fills at least one of the internal cavities and is bonded to the airfoil portion only at an extremity of the internal cavity nearer the root portion, and not to the stiffener or to the first and second walls of the airfoil portion, to define an internal damping member that provides a vibratory damping effect to the airfoil portion. | 09-02-2010 |
| 20100221114 | Tornado Fan - A tornado fan for cooling a room may include a stand member to support the tornado fan, a motor member to connect to the stand member and to rotate a fan blade of the tornado fan, and a cage member to enclose the motor member and fan blade. The fan blade may be substantially planar and includes a semi circle cross-section, and the stand member may include a platform to connect to the motor member. The motor member may include a platform to connect to the platform of the stand member, and the cage member may include a platform to connect to the platform of the motor member and the platform of the stand member. The motor member may include a stopper platform to connect to the fan blade, and the motor member may include a traverse pin to cooperate with the stopper platform. | 09-02-2010 |
| 20100322772 | ANNULUS FILLER FOR A GAS TURBINE ENGINE - An annulus filler for mounting to a rotor disc of a gas turbine engine is provided to bridge the gap between adjacent blades. A first part is connectable to the rotor disc between adjacent blades. There is a separate second part that engages with the first part after connecting the rotor blades to the rotor disc. When installed, the filler is spaced from each blade by a respective clearance gap (G), and an operational configuration in which it contacts each of said blades. Engagement of the second part with the first part is effective to urge the first part from said installation configuration to said operational configuration and thus into blade contact. The first part may have a mounting region for connection to the rotor disc and allow, in said first step of said procedure, the mounting region to remain visible from a radially outer viewpoint. | 12-23-2010 |
| 20110110780 | ANNULUS FILLER FOR A GAS TURBINE ENGINE - An annulus filler is provided for mounting to a rotor disc of a gas turbine engine. The filler comprises a lid for bridging the gap between two adjacent blades attached to the rotor disc. The filler further comprises forward and rearward hook members projecting below the lid and configured to respectively engage with forward and rearward outwardly directed hooks provided on the rotor disc when the annulus filler is translated in a generally rearwards direction on mounting of the annulus filler to the rotor disc. The filler can further comprise a lip extending from the rear of the lid, the lip being configured to fit beneath a gas-washed element located rearwards of the annulus filler. One or more guide ramps then extend from the rear of the lip, the or each guide ramp being angled down relative to the lip to encourage the lip to slide beneath said fairing when the annulus filler is translated in the generally rearwards direction. Alternatively, or additionally, the forward hook member can have a stop surface which, on engaging the forward hook member to the forward outwardly directed hook, can abut a surface of the rotor disc to prevent or reduce rotation of the annulus filler about the forward hook member. The forward hook member then only engages with the forward outwardly directed hook when the rearward hook member also engages with the rearward outwardly directed hook. | 05-12-2011 |
| 20110217175 | TURBINE ROTOR BLADE - It is possible to easily and rapidly slot a blade root of a final (last) turbine rotor blade into a blade groove on a turbine disc even when the plan-view shape of a shroud of the turbine rotor blade is complex. A turbine rotor blade that is provided with a blade root that is slotted into a blade groove formed on a circumferential portion of the turbine disc to hold the whole blade, a blade portion that is exposed to high-temperature gas, a platform that supports this blade portion, a shank that connects the blade root and the platform, and a shroud that extends along the circumferential direction from the end of the blade portion has a cut-out portion cut out to a predetermined depth, either at the leading-edge or the trailing-edge of the blade root, along the lengthwise direction thereof from the end of the blade root to an intermediate part of the shank. | 09-08-2011 |
| 20110223025 | GAS TURBINE ENGINE ROTOR SECTIONS HELD TOGETHER BY TIE SHAFT, AND WITH BLADE RIM UNDERCUT - An integrally bladed rotor is utilized in at least a stage of one of a compressor and turbine section. Airfoils extend radially outwardly from a platform, and there is an undercut inward from the platform at a downstream edge of the airfoil. | 09-15-2011 |
| 20110243742 | STATOR STAGE FOR TURBOMACHINE COMPRESSOR - A turbomachine stator stage comprising two coaxial shrouds, respectively an inner shroud and an outer shroud with substantially radial vanes extending therebetween, the radially outer ends of the vanes being welded to the outer shroud and the radially inner ends of the vanes passing through orifices in an outer ring of the inner shroud, the inner ends being held by elastomer spacers in an annular cavity formed between the outer ring and an inner ring that is fastened to the outer ring. | 10-06-2011 |
| 20120045337 | TURBINE BUCKET ASSEMBLY AND METHODS FOR ASSEMBLING SAME - A method for assembling a rotor assembly for use with a turbine engine. The method includes providing at least two rotor blades that each include a shank extending between a dovetail and a platform. The shank includes at least one cover plate that extends inwardly from the platform towards the dovetail. An airfoil extends outwardly from the platform. A first rotor blade is coupled to a rotor disk. A second rotor blade is coupled to the rotor disk, such that a cavity is defined between the first and second rotor blades, and such that a seal path is defined between a first rotor blade cover plate and a second rotor blade cover plate. | 02-23-2012 |
| 20120087795 | ROTOR FOR TURBOMACHINERY - A rotor includes a disc, on which are fixed vanes, and platforms between these vanes. The rotor is particularly remarkable in that the platforms are fixed securely and tightly to the disc. To this end, the disc includes between two successive vanes an upstream stop projecting axially from the upstream surface, and each platform includes: a plate, a retaining groove extending axially and in which the upstream stop of the disc is engaged, an axial stop bearing axially against the upstream surface of the disc. | 04-12-2012 |
| 20120263596 | ANNULUS FILLER SYSTEM - An annulus filler system bridges the gap between two adjacent blades attached to a rim of the rotor disc of a gas turbine engine. The system includes an annulus filler having a lid which extends between the adjacent blades and defines an airflow surface for air being drawn through the engine. The filler also has a support body extending beneath the lid and terminating in an elongate foot which, in use, extends along a groove provided in the rim of the disc. The groove has a neck which prevents withdrawal of the foot through the neck in a radially outward direction of the disc. The system further includes a sleeve which, after installation of the filler, is slidably locatable into a gap between the foot and sides of the groove. | 10-18-2012 |
| 20130004315 | MATEFACE GAP CONFIGURATION FOR GAS TURBINE ENGINE - In a gas turbine engine, adjoining pairs of airfoil structures include airfoils mounted to respective platforms. The platforms have side edges defining matefaces that form a mateface gap extending from an upstream edge of the platforms to a downstream edge of the platforms. A flow field of working gas adjacent to endwalls of the platform comprises streamlines extending generally transverse to the axial direction from a first airfoil toward an adjacent second airfoil. To achieve improved aerodynamic performance, the mateface gap has portions oriented transverse to the streamlines and oriented aligned with the streamlines. A step in elevation of the side edges at the transverse portion can include injected cooling flow in a direction that enhances attachment of the flow at a downstream side. | 01-03-2013 |
| 20130017091 | RADIAL TURBINE BACKFACE CURVATURE STRESS REDUCTIONAANM Duong; Loc QuangAACI San DiegoAAST CAAACO USAAGP Duong; Loc Quang San Diego CA USAANM Hu; XiaolanAACI San DiegoAAST CAAACO USAAGP Hu; Xiaolan San Diego CA USAANM Yang; GaoAACI San DiegoAAST CAAACO USAAGP Yang; Gao San Diego CA USAANM Jones; Anthony C.AACI San DiegoAAST CAAACO USAAGP Jones; Anthony C. San Diego CA US - A turbine wheel is disposed about an axis and has a back having a separator disposed thereon, an inner undercut disposed between the separator and the axis, and an outer undercut disposed between the separator and an outer periphery of the back face. The inner undercut is defined by a first radius blending toward the axis and into a first flat section, and further defined by a second radius blending into the first flat section and into the separator. | 01-17-2013 |
| 20130064667 | TURBINE BLADE AND NON-INTEGRAL PLATFORM WITH PIN ATTACHMENT - Platforms ( | 03-14-2013 |
| 20130224027 | SCALLOPED SURFACE TURBINE STAGE WITH PURGE TROUGH - A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a scalloped flow surface including a purge trough commencing tangentially in a blend area of the platform. The purge trough extending axially toward the suction side of the airfoil, aft of the leading edge, to channel a purge flow. | 08-29-2013 |
| 20140003949 | INTERBLADE PLATFORM FOR A FAN, ROTOR OF A FAN AND ASSOCIATED MANUFACTURING METHOD | 01-02-2014 |
| 20140056711 | AIRCRAFT ENGINE ANNULAR SHROUD COMPRISING AN OPENING FOR THE INSERTION OF BLADES - An aircraft engine annular shroud includes, on its internal surface, a peripheral annular groove able to accept a plurality of blade roots; an insertion opening for inserting the blade roots into the annular groove; and a closure device for closing off the insertion opening. | 02-27-2014 |
| 20140079552 | Attaching The Blades To The Drum Of An Axial Turbocompressor - The invention relates to the design of rotor blades of an axial turbomachine compressor, especially the method of attaching the blades to the rotor. The blades comprise an aerofoil portion and a platform for attaching them to the rotor. The platform comprises, along the main axis of the blade, a first layer forming a surface bounding the fluid stream and skirting the aerodynamic surfaces and a second layer, underneath the first layer with respect to the aerodynamic surfaces, designed to be able to mate with the inner face of a wall of the rotor around an aperture in the rotor for the purpose of attaching it. | 03-20-2014 |
| 20140161616 | MULTI-PIECE BLADE FOR GAS TURBINE ENGINE - A blade assembly for a gas turbine engine includes a rim seal including leading and trailing edge seal portions joined to one another by an axial portion. The leading and trailing edge seal portions and the axial portion together provide a notch. A blade has a root received in the notch. A rotating stage of a gas turbine engine includes a rotor including a slot. A rim seal includes leading and trailing edge seal portions adjoined to one another by an axial portion and providing a notch. A blade has a root received in the notch. A method of assembling a rotor stage includes inserting a root of a blade into a notch of a rim seal, and sliding the rim seal and blade into a rotor slot. | 06-12-2014 |
| 20140169973 | Ni-Based Heat Resistant Alloy, Gas Turbine Component and Gas Turbine - A Ni-based heat resistant alloy has a composition of, by mass percent, carbon: 0.001 to 0.1%, chromium: 16 to 22%, aluminum: 0.5 to 1.5%, molybdenum: 0.1 to 2.0%, tungsten: 0.1 to 6.0%, niobium: 3.5 to 5.5%, titanium: 0.8 to 3.0%, iron: 16 to 20%, and the balance being nickel and inevitable impurities. A parameter Ps indicating a segregation tendency is in a range of Ps≧−3.5. The parameter Ps is represented by Formula (1). | 06-19-2014 |
| 20140193265 | ROTOR DISK INCLUDING A PLURALITY OF HOOKS - A rotor disk comprises a plurality of circumferentially distributed hooks, the set of hooks defining an annular groove adapted to cooperate with at least two flange sectors. At least one of the hooks comprises a second element through which a recess is formed which opens up at each of the transverse flanks of the second element and at the internal peripheral surface of the second element. | 07-10-2014 |
| 20140212292 | Airfoil Member and Composite Platform Having Contoured Endwall - An airfoil member and platform assembly for a gas turbine engine is provided. The platform to which the airfoil member is anchored is made of a composite material and includes an endwall defining a contoured region for improved aerodynamics. The contoured region influences the flow of gases through the flow passages between the airfoil members, thereby reducing endwall losses due to horseshoe vortexing. The composite material may be woven ceramic matrix composite fibers infiltrated with a ceramic matrix material or woven organic matrix composite fibers infiltrated with an organic matrix material. | 07-31-2014 |
| 20140212293 | AIRCRAFT ROTOR BLADE AND RELATIVE FORMING METHOD - An aircraft rotor blade having a root portion having a through seat and designed for connection to the rotor; and a main portion extending from the root portion. The blade is produced by polymerizing an assembly having a main structure of composite material, and a composite material covering defining the outer surface of the blade. At the root portion, the main structure has a contoured block; and a lamina member extending about at least part of the block, and having a first part adhering to a first peripheral portion of the block, and a second part spaced apart from and facing a second peripheral portion of the block to form the seat; the lamina member having a pre-preg of continuous unidirectional fibres. | 07-31-2014 |
| 20140271205 | TURBINE BLADE PIN SEAL - A gas turbine engine turbine disk assembly includes a turbine disk, turbine blades, and pin seals. Each turbine blade includes a platform with a pressure side seal slot extending into a pressure side of the platform and a suction side seal slot extending into a suction side of the platform. The pressure side seal slot and the suction side seal slot are each angled between three and ten degrees in the radial direction relative to the axis of the turbine disk. The pin seal includes a cylindrical shape and is located within a seal slot formed from the pressure side seal slot and the suction side seal slot of adjacent turbine blades. | 09-18-2014 |
| 20140271206 | TURBINE BLADE WITH A PIN SEAL SLOT - A gas turbine engine turbine disk assembly includes a turbine disk, turbine blades, and pin seals. Each turbine blade includes a platform with a pressure side seal slot extending into a pressure side of the platform and a suction side seal slot extending into a suction side of the platform. The pressure side seal slot and the suction side seal slot are each angled between three and ten degrees in the radial direction relative to the axis of the turbine disk. The pin seal includes a cylindrical shape and is located within a seal slot formed from the pressure side seal slot and the suction side seal slot of adjacent turbine blades. | 09-18-2014 |
| 20140271207 | FAN BLADE - A rotor blade assembly for a gas turbine engine includes two aerofoil members joined together at their roots by a blade assembly attachment web. The rotor blade assembly is made from a composite material, for example an organic fibre composite material. The blade assembly attachment web is used to attach a plurality of rotor blade assemblies to the rest of the gas turbine engine in order to form a rotor stage. The rotor stage may, for example, be the fan stage of a turbofan gas turbine engine. | 09-18-2014 |
| 20140286777 | BLANK CASTING FOR PRODUCING A TURBINE ENGINE ROTOR BLADE AND PROCESS FOR MANUFACTURING THE ROTOR BLADE FROM THIS BLANK - The invention relates to a blank casting for producing a turbine engine rotor blade, with a vane connected by a platform ( | 09-25-2014 |
| 20140294587 | TURBINE ENGINE BLADE - The invention relates to a turbine engine blade ( | 10-02-2014 |
| 20140301850 | Turbomachine Blade Assembly - Embodiments of the present disclosure include a system comprising a turbomachine blade assembly having a blade portion, a shank portion, and a mounting portion, wherein the blade portion, the shank portion, and the mounting portion comprise a first plurality of plies extending from a tip of the airfoil to a base of the dovetail. | 10-09-2014 |
| 20140308133 | ROTOR WHEEL FOR A TURBINE ENGINE - A rotor wheel for a turbine engine, such as an airplane turboprop or turbojet, the rotor wheel including a rotor disk including teeth at its outer periphery defining slots for axially mounting and radially retaining blade roots. An annular lip includes an annular rim extending axially downstream from and radially towards an inside of a radial retaining mechanism formed to project axially from an upstream face of the disk, and a sealing mechanism is arranged radially inside the annular lip and upstream ends of platforms of the blades. | 10-16-2014 |
| 20140356172 | TURBINE WHEEL IN A TURBINE ENGINE - The invention relates to a turbine wheel ( | 12-04-2014 |
| 20140356173 | TURBINE ENGINE WHEEL, IN PARTICULAR FOR A LOW PRESSURE TURBINE - The invention relates to a turbine engine wheel ( | 12-04-2014 |
| 20140363299 | COMPOSITE MATERIAL REINFORCING PART OF PI-SHAPED SECTION, IN PARTICULAR A PLATFORM FOR A TURBINE ENGINE FAN, AND ITS METHOD OF FABRICATION - A reinforcing part of π-shaped section made out of composite material, and a method of making the part, the method including: making a first set of layers of interlinked yarns by three-dimensional weaving to form a first fiber blank portion to form a base preform; making a second set of layers of interlinked yarns by three-dimensional weaving to form a second fiber blank portion to form a stiffener preform, yarns of the second set being interlinked with yarns of the first set by weaving over a central interlinked strip that flares towards side edges of the first fiber blank portion in a zone corresponding to the step of the base; shaping the two fiber blank portions to obtain a single-piece fiber preform having a portion forming a base preform and a portion forming a stiffener preform; and depositing a resin in the fiber preform to form a matrix. | 12-11-2014 |
| 20150023793 | TURBOMACHINE ROTOR BLADE - A turbomachine rotor blade presenting an outer part ( | 01-22-2015 |
| 20150050150 | ANNULUS FILLER - An annulus filler, mounted to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc, is disclosed. The annulus filler, formed from a polymer matrix composite material, includes an outer lid, defining an airflow surface for air drawn through the engine in an axial airflow direction, and a support structure, connectable to the rotor disc, to support the rear of the lid on the rotor disc. The support structure has two support walls extending from opposing lateral sides of the lid to an attachment strap for receiving a hook on the rotor disc, the attachment strap bridging the support walls. Under centrifugal loads, the opposing support walls resiliently deform. Each support wall has a concave rear edge. Each rear edge has a first curved section, a second curved section and a substantially straight section therebetween. | 02-19-2015 |
| 20150071783 | TURBINE BLADE - A turbine blade is provided having a blade and a modular platform which follow one another along a longitudinal axis of the turbine blade. In order to provide a modular turbine blade that has an especially plain and simple design and that ensures an especially reliable, long-lasting, durable connection of the individual components among each other, the blade has an extension and the platform has an outer platform part and an at least two-part inner platform part which is radial in relation to the longitudinal axis and which lie laterally against the extension of the blade, and the outer platform part is designed as an endless platform frame that surrounds the outer edge of the inner platform part. | 03-12-2015 |
| 20150118055 | GAS TURBINE ENGINE ROTOR ASSEMBLY AND METHOD OF ASSEMBLING THE SAME - A rotor assembly includes a rotor disc including a plurality of circumferentially-spaced diskposts and a plurality of dovetail slots. Each dovetail slot is defined between a pair of circumferentially-adjacent diskposts. A plurality of rotor blades are coupled to the rotor disc. Each rotor blade includes a dovetail portion that is configured to slidably engage a respective dovetail slot. A plurality of platform sections are coupled to the rotor disc such that each platform section is adjacent a respective rotor blade. Each platform section includes a diskpost slot that is configured to receive one of the plurality of diskposts such that each dovetail slot receives a respective dovetail portion and at least a portion of at least one of the platform sections adjacent the rotor blade. | 04-30-2015 |
| 20150125305 | LOW PROFILE FAN PLATFORM ATTACHMENT - A platform for a fan of a gas turbine engine includes a body portion, a forward flange at a front of the body portion that includes an engagement feature that interacts with a forward flange of a lug of a hub of a fan of a gas turbine engine, and a pin integral with a rear portion of the body portion. The pin is receivable in an aperture in a rear flange of the lug. | 05-07-2015 |
| 20150139808 | Rotor of a turbomachine - A rotor of a turbomachine. The rotor includes at least one blade ( | 05-21-2015 |
| 20150308279 | ROTATING ASSEMBLY FOR A TURBOMACHINE - A rotating assembly for a turbomachine, including a disc having an external periphery with alternating recesses and teeth, blades extending radially from the disc and the feet of which are axially engaged and radially retained in the recesses of the disc, platforms extending on the circumference from the blades and being arranged end to end on the circumference, with respect to each other, axial sealing device upstream and/or downstream of an annular zone extending radially from the platforms up to the disc. The sealing device radially includes an internal annular portion and an external annular portion structurally distinct from each other, and the external annular portion of which is elastically constrained radially inwards by the internal annular portion. | 10-29-2015 |
| 20160069196 | REPAIRED OR REMANUFACTURED BLADE PLATFORM FOR A GAS TURBINE ENGINE - A article of manufacture, the article having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1, and wherein X and Y are distances in inches which, when connected, define profile sections at each distance Z in inches to form a portion of a rotor blade. | 03-10-2016 |
| 20160153303 | SNAP IN PLATFORM DAMPER AND SEAL ASSEMBLY FOR A GAS TURBINE ENGINE | 06-02-2016 |
| 20160186572 | TURBINE BLADE PLATFORM UNDERCUT WITH DECREASING RADII CURVE - A turbine blade has an undercut beneath its platform proximate a trailing edge region. The undercut incorporates a curved portion to reduce to reduce undesirable stress concentration. The undercut shape includes a curved portion of decreasing radius with increasing distance from the underside of the platform. | 06-30-2016 |
| 20160252102 | ROTARY ASSEMBLY FOR AN AVIATION TURBINE ENGINE, THE ASSEMBLY COMPRISING A SEPARATE FAN BLADE PLATFORM MOUNTED ON A FAN DISK | 09-01-2016 |
| 416193000 | Root platforms | 50 |
| 20080232968 | NON-AXISYMMETRIC END WALL CONTOURING FOR A TURBOMACHINE BLADE ROW - A turbomachine blade row is provided having a hub that includes a non-axisymmetric end wall modified by a transformation function. The blade row further includes a circumferential row of a plurality of airfoil members radially extending from the non-axisymmetric end wall of the hub and forming a plurality of sectoral passages there between. A radius of the non-axisymmetric end wall is determined by a transformation function including a plurality of geometric parameters defined by a user based on flow conditions. The plurality of geometric parameters provide for modification of the end wall in both an axial and a tangential direction to includes a plurality of concave profiled regions and convex profiled regions. | 09-25-2008 |
| 20100166558 | METHODS AND APPARATUS RELATING TO IMPROVED TURBINE BLADE PLATFORM CONTOURS - A flow directing assembly for use in a turbine engine comprising: a plurality of circumferentially spaced blades, each of the blades including a radial projecting airfoil with a concave pressure side and a convex suction side that extend from a platform; and a plurality of flow passages, each flow passage defined by the airfoils of neighboring blades and an inner wall formed by abutting platforms of neighboring blades, the inner wall forming the inner radial boundary of the flow passage; wherein the inner wall of one or more of the flow passages comprises means for reducing frictional losses between the flow through the turbine engine and the inner wall. The means for reducing frictional losses may comprise a non-axisymmetrical trough positioned between neighboring airfoils that is configured to reduce frictional losses. | 07-01-2010 |
| 20100290910 | ANNULUS FILLER - An annulus filler for mounting to a rotor disc of a gas turbine engine bridges the gap between adjacent disc blades. The annulus filler has a lid defining part of an airflow surface for air drawn through the engine; a separate support connectable to the lid and to the rotor disc with an engagement portion of the support extending radially past a substantially adjacent region of the lid; and a retainer configured to interconnect the lid and the support by engaging each engagement portion of the support and adjacent regions of the lid, the retainer defining another part of the airflow surface. The annulus filler can be configured to allow mounting to the rotor disc, where the support is connected to the rotor disc without the lid, and then the lid is mounted to the support such that each engagement portion remains visible from the lid's radially outermost side. | 11-18-2010 |
| 20110182737 | HEAT DISSIPATION FAN AND ROTOR THEREOF - A rotor includes a hub, rotary blades extending outwardly from the hub, and an annular wall surrounding the rotary blades. Each rotary blade includes a windward lateral surface and a leeward lateral surface at opposite sides thereof. The annular wall adjoins the outer ends of the rotary blades and is rotatable therewith. A perforation is defined in the annular wall between two neighboring rotary blades and adjacent to the leeward lateral surface of a leading rotary blade of the neighboring rotary blades. | 07-28-2011 |
| 20120014800 | FAN ASSEMBLY - A fan assembly according to an exemplary embodiment of the present invention includes: a hub; and a plurality of blades including a leading edge corresponding to a side hit by air and a trailing edge corresponding to an opposite side of the leading ledge, the plurality of blades configured to be extended radially from an outer peripheral surface of the hub, wherein each of the plurality of blades includes a first part extended radially from the outer peripheral surface of the hub, a bent part stepped on the end of the first part, and a second part further extended radially on the end of the bent part. | 01-19-2012 |
| 20120027598 | ROTOR COVER PLATE RETENTION METHOD - A mechanism for use in a gas turbine engine has a cover plate, a rotor disk, a first slot in the cover plate, a second slot in the rotor disk, a first finger in the cover plate extending through the second slot, and a second finger in the rotor disk extending through the first slot. The first finger and the second finger form a channel and a holder is disposed in the channel for locking the rotor disk and the cover plate together | 02-02-2012 |
| 20120121425 | ANNULAR TURBINE RING ROTOR - A fan-turbine rotor assembly includes one or more turbine ring rotors. Each turbine ring rotor is cast as a single integral annular ring. By forming the turbine as one or more rings, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine ring rotors to the diffuser ring includes axial installation and radial locking of each turbine ring rotor. | 05-17-2012 |
| 20130108448 | TURBINE BUCKET PLATFORM SHAPING FOR GAS TEMPERATURE CONTROL AND RELATED METHOD | 05-02-2013 |
| 20130170995 | AXIAL FLOW FAN BLADE STRUCTURE AND AXIAL FLOW FAN THEREOF - An axial flow fan blade structure and an axial flow fan thereof. The axial flow fan blade structure includes a fan impeller and an annular body. The fan impeller has a hub and multiple blades. Each blade has a first flow guide face and a second flow guide face opposite to the first flow guide face. The annular body is disposed on the blades. The annular body outward extends from the first and second flow guide faces and is annularly connected with the blades along the blades. The annular body not only is able to increase the strength of the blades of the axial flow fan, but also is able to reduce vibration and noise made by the axial flow fan. | 07-04-2013 |
| 20130189107 | Turbine Packing Deflector - A turbine includes a rotor being rotatable about an axis, a circumferential array of nozzles having circumferentially spaced airfoils and inner and outer bands disposed at opposite ends thereof, the inner band having a leading portion and a trailing portion, and an array of directors arranged on the inner band, the array of directors operative to direct a flow path of fluid, the flow path of fluid partially defined by the rotor and the inner band. | 07-25-2013 |
| 20140086751 | ANNULUS FILLER FOR AXIAL FLOW MACHINE - A fluid-washed assembly for an axial flow machine, such as a fan blade assembly for a gas turbine engine. The assembly has an array of members circumferentially spaced about the machine axis, each member extending from a radially inner end to a radially outer end with respect to the axis of rotation of the machine. Each member has opposing outer surfaces extending between a leading edge and a trailing edge thereof with respect to the direction of oncoming fluid flow in use. A plurality of annulus fillers are provided between each member, wherein each annulus filler is affixed against an outer surface of an associated member at a location between the inner and outer ends in a manner which supports the annulus filler in use. In preferred embodiments, the annulus fillers comprise a composite material which is bonded to the associated member using an adhesive. | 03-27-2014 |
| 20140154083 | FAN BLADE WITH FLEXIBLE AIRFOIL WING - A fan assembly is disclosed that includes one or more fan blades, each fan blade having a flexible airfoil wing. A curved, flexible wing is connected to a main spar element located between the upper and lower portions of the curved, flexible wing element. The curved, flexible wing forms the entire upper surface of the wing, the entire leading edge of the wing, and a portion of the lower surface of the wing. | 06-05-2014 |
| 20150050151 | ANNULUS FILLER - An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc, The annulus filler has an outer lid which defines an airflow surface for air being drawn through the engine, the lid having a leading edge and a trailing edge in an axial airflow direction. The annulus filler further has a support arrangement which is connectable to the rotor disc. The support arrangement includes a first engageable portion at the leading edge of the lid and a second engageable portion at the trailing edge of the lid. The engageable portions engage in use with respective adjacent parts of the gas turbine engine, and have respective galvanic corrosion barriers, which prevent or reduce galvanic corrosion between the material of the lid and the respective adjacent engine parts. | 02-19-2015 |
| 20150300194 | ANNULUS FILLER - An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc. The annulus filler is substantially entirely formed from a polymer matrix composite material. It has an outer lid which defines an airflow surface for air being drawn through the engine in an axial airflow direction, and a support structure which is connectable to the rotor disc to support the lid on the rotor disc. The support structure has two support walls extending from opposing lateral sides of the lid to an attachment strap for receiving a hook on the rotor disc, the attachment strap bridging the support walls. In use, under centrifugal loads, the opposing support walls resiliently deform to allow outward radial movement of the lid. Each support wall is thickened in a region neighbouring the attachment strap. | 10-22-2015 |
| 20160047261 | COMPOSITE FAN ANNULUS FILLER WITH NANO-COATING - According to the present disclosure, an fan annulus filler for use in a fan assembly of a gas turbine engine may include an annulus filler body formed of a polymer. The annulus filler body may include a surface coated with a nanocrystalline coating to form a flow surface. | 02-18-2016 |
| 20160130957 | TURBINE BLISK INCLUDING CERAMIC MATRIX COMPOSITE BLADES AND METHODS OF MANUFACTURE - In some embodiments, an apparatus includes a disk, a coupling member and a set of blades. The coupling member has a first surface and a second surface, and defines a set of openings between the first surface and the second surface. The first surface is configured to be coupled to the outer surface of the disk. A portion of each blade from the set of blades is disposed within an opening from the set of openings when the first surface of the coupling member is coupled to the outer surface of the disk such that the blade is coupled to the disk. | 05-12-2016 |
| 20160186592 | FLOWPATH BOUNDARY AND ROTOR ASSEMBLIES IN GAS TURBINES - A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a first axial section of an inner boundary of the flowpath; a second rotor wheel supporting a second rotor blade having a platform that defines a second axial section of the inner boundary of the flowpath; and an annulus filler that includes an outboard surface that defines at least part of a third axial section of the inner boundary of the flowpath occurring between the first axial section and the second axial section of the inner boundary of the flowpath. The first rotor wheel may include an axial connector for axially engaging a mating surface formed on a radially innermost face of the first rotor blade and a mating surface formed on a radially innermost face of the annulus filler. | 06-30-2016 |
| 20080286106 | TURBINE ROTOR BLADE ASSEMBLY AND METHOD OF FABRICATING THE SAME - A removable rotor blade platform includes a first platform leg, a second platform leg, and a platform portion coupled to the first and second platform legs. The first platform leg is configured to be retained by a first retainer coupled to a first rotor blade, and the second platform leg is configured to be retained by a second retainer coupled to a second adjacent rotor blade. A method of assembling a blade assembly that includes a removable platform, a rotor assembly including the removable platform, and a gas turbine engine assembly including the removable platform, are also described herein. | 11-20-2008 |
| 20090123286 | ASSEMBLY OF A FAN BLADE AND OF ITS DAMPER, FAN BLADE DAMPER AND METHOD FOR CALIBRATING THE DAMPER - The invention relates to a fan blade assembly of a turbojet with fan and a fan blade damper, the fan blade comprising a root and a platform, the fan blade damper being suitable for being attached in a housing formed in the lower face of the platform, said housing comprising an upstream side perpendicular to the root of the blade. The damper comprises a front edge of which a first portion is parallel to the upstream side of the housing and of which a second portion is inclined relative to said upstream side. The invention also relates to a fan blade damper and a method for calibrating said damper. | 05-14-2009 |
| 20090148295 | Gas Turbine Engine Systems Involving Rotor Bayonet Coverplates and Tools for Installing Such Coverplates - Gas turbine engine systems involving rotor bayonet coverplates and tools for installing such coverplates are provided. In this regard, a representative turbine assembly for a gas turbine engine includes: a turbine disk operative to mount a set of turbine blades; and a coverplate having an annular main body portion and a spaced annular arrangement of tabs extending radially inwardly from the main body portion with open-ended gaps being located between the tabs, the tabs being operative to secure an inner diameter of the coverplate to the turbine disk. | 06-11-2009 |
| 20100054942 | BLADE ASSEMBLY - Blade assemblies are provided in a number of forms. These blade assemblies may have blades secured to disks (blisk), rings (bling) and drums (blum). The blades and/or the rotor elements formed by these rings, drums or disks can fragment and it is necessary to contain such fragments within a casing. Impact energy has a significant effect upon the necessary thickness of the casing to ensure containment. By providing blades as well as rotor elements which incorporate discontinuities which provide flexing under impact, energy is absorbed prior to further fragmentation upon impact engagement with a casing surface; flexing is about the discontinuity. In such circumstances casings may be thinner and therefore significant weight savings achieved with regard to aircraft incorporating gas turbine engines having blade assemblies with discontinuities. | 03-04-2010 |
| 20100124502 | ROTOR BLADE ARRANGEMENT AND GAS TURBINE - A rotor blade arrangement ( | 05-20-2010 |
| 20100143140 | FLUID FLOW MACHINE WITH SIDEWALL BOUNDARY LAYER BARRIER - A fluid flow machine has a main flow path in which at least one row of blades ( | 06-10-2010 |
| 20100209251 | FAN BLADE PLATFORM - A fan blade platform assembly comprises a plate insert shaped and dimensioned to span a gap formed between the opposed facing platforms of adjacent fan blades of a turbo fan engine. The plate insert can be retained in engagement under arresting shoulders provided on the adjacent fan blades by a spring force exerted by a spring insert held captive and in contact between the plate insert and an outer surface of the fan hub. | 08-19-2010 |
| 20100221113 | INTERNALLY-DAMPED AIRFOIL AND METHOD THEREFOR - An airfoil component and method for producing the component. The component has root and airfoil portions, the latter having an airfoil tip and oppositely-disposed concave and convex surfaces that converge at leading and trailing edges of the airfoil portion. The airfoil portion has at least one stiffener between first and second walls thereof that define the concave and convex surfaces, respectively. The stiffener defines multiple internal cavities within the airfoil portion that extend in the span-wise direction of the airfoil portion. A polymeric material fills at least one of the internal cavities and is bonded to the airfoil portion only at an extremity of the internal cavity nearer the root portion, and not to the stiffener or to the first and second walls of the airfoil portion, to define an internal damping member that provides a vibratory damping effect to the airfoil portion. | 09-02-2010 |
| 20100221114 | Tornado Fan - A tornado fan for cooling a room may include a stand member to support the tornado fan, a motor member to connect to the stand member and to rotate a fan blade of the tornado fan, and a cage member to enclose the motor member and fan blade. The fan blade may be substantially planar and includes a semi circle cross-section, and the stand member may include a platform to connect to the motor member. The motor member may include a platform to connect to the platform of the stand member, and the cage member may include a platform to connect to the platform of the motor member and the platform of the stand member. The motor member may include a stopper platform to connect to the fan blade, and the motor member may include a traverse pin to cooperate with the stopper platform. | 09-02-2010 |
| 20100322772 | ANNULUS FILLER FOR A GAS TURBINE ENGINE - An annulus filler for mounting to a rotor disc of a gas turbine engine is provided to bridge the gap between adjacent blades. A first part is connectable to the rotor disc between adjacent blades. There is a separate second part that engages with the first part after connecting the rotor blades to the rotor disc. When installed, the filler is spaced from each blade by a respective clearance gap (G), and an operational configuration in which it contacts each of said blades. Engagement of the second part with the first part is effective to urge the first part from said installation configuration to said operational configuration and thus into blade contact. The first part may have a mounting region for connection to the rotor disc and allow, in said first step of said procedure, the mounting region to remain visible from a radially outer viewpoint. | 12-23-2010 |
| 20110110780 | ANNULUS FILLER FOR A GAS TURBINE ENGINE - An annulus filler is provided for mounting to a rotor disc of a gas turbine engine. The filler comprises a lid for bridging the gap between two adjacent blades attached to the rotor disc. The filler further comprises forward and rearward hook members projecting below the lid and configured to respectively engage with forward and rearward outwardly directed hooks provided on the rotor disc when the annulus filler is translated in a generally rearwards direction on mounting of the annulus filler to the rotor disc. The filler can further comprise a lip extending from the rear of the lid, the lip being configured to fit beneath a gas-washed element located rearwards of the annulus filler. One or more guide ramps then extend from the rear of the lip, the or each guide ramp being angled down relative to the lip to encourage the lip to slide beneath said fairing when the annulus filler is translated in the generally rearwards direction. Alternatively, or additionally, the forward hook member can have a stop surface which, on engaging the forward hook member to the forward outwardly directed hook, can abut a surface of the rotor disc to prevent or reduce rotation of the annulus filler about the forward hook member. The forward hook member then only engages with the forward outwardly directed hook when the rearward hook member also engages with the rearward outwardly directed hook. | 05-12-2011 |
| 20110217175 | TURBINE ROTOR BLADE - It is possible to easily and rapidly slot a blade root of a final (last) turbine rotor blade into a blade groove on a turbine disc even when the plan-view shape of a shroud of the turbine rotor blade is complex. A turbine rotor blade that is provided with a blade root that is slotted into a blade groove formed on a circumferential portion of the turbine disc to hold the whole blade, a blade portion that is exposed to high-temperature gas, a platform that supports this blade portion, a shank that connects the blade root and the platform, and a shroud that extends along the circumferential direction from the end of the blade portion has a cut-out portion cut out to a predetermined depth, either at the leading-edge or the trailing-edge of the blade root, along the lengthwise direction thereof from the end of the blade root to an intermediate part of the shank. | 09-08-2011 |
| 20110223025 | GAS TURBINE ENGINE ROTOR SECTIONS HELD TOGETHER BY TIE SHAFT, AND WITH BLADE RIM UNDERCUT - An integrally bladed rotor is utilized in at least a stage of one of a compressor and turbine section. Airfoils extend radially outwardly from a platform, and there is an undercut inward from the platform at a downstream edge of the airfoil. | 09-15-2011 |
| 20110243742 | STATOR STAGE FOR TURBOMACHINE COMPRESSOR - A turbomachine stator stage comprising two coaxial shrouds, respectively an inner shroud and an outer shroud with substantially radial vanes extending therebetween, the radially outer ends of the vanes being welded to the outer shroud and the radially inner ends of the vanes passing through orifices in an outer ring of the inner shroud, the inner ends being held by elastomer spacers in an annular cavity formed between the outer ring and an inner ring that is fastened to the outer ring. | 10-06-2011 |
| 20120045337 | TURBINE BUCKET ASSEMBLY AND METHODS FOR ASSEMBLING SAME - A method for assembling a rotor assembly for use with a turbine engine. The method includes providing at least two rotor blades that each include a shank extending between a dovetail and a platform. The shank includes at least one cover plate that extends inwardly from the platform towards the dovetail. An airfoil extends outwardly from the platform. A first rotor blade is coupled to a rotor disk. A second rotor blade is coupled to the rotor disk, such that a cavity is defined between the first and second rotor blades, and such that a seal path is defined between a first rotor blade cover plate and a second rotor blade cover plate. | 02-23-2012 |
| 20120087795 | ROTOR FOR TURBOMACHINERY - A rotor includes a disc, on which are fixed vanes, and platforms between these vanes. The rotor is particularly remarkable in that the platforms are fixed securely and tightly to the disc. To this end, the disc includes between two successive vanes an upstream stop projecting axially from the upstream surface, and each platform includes: a plate, a retaining groove extending axially and in which the upstream stop of the disc is engaged, an axial stop bearing axially against the upstream surface of the disc. | 04-12-2012 |
| 20120263596 | ANNULUS FILLER SYSTEM - An annulus filler system bridges the gap between two adjacent blades attached to a rim of the rotor disc of a gas turbine engine. The system includes an annulus filler having a lid which extends between the adjacent blades and defines an airflow surface for air being drawn through the engine. The filler also has a support body extending beneath the lid and terminating in an elongate foot which, in use, extends along a groove provided in the rim of the disc. The groove has a neck which prevents withdrawal of the foot through the neck in a radially outward direction of the disc. The system further includes a sleeve which, after installation of the filler, is slidably locatable into a gap between the foot and sides of the groove. | 10-18-2012 |
| 20130004315 | MATEFACE GAP CONFIGURATION FOR GAS TURBINE ENGINE - In a gas turbine engine, adjoining pairs of airfoil structures include airfoils mounted to respective platforms. The platforms have side edges defining matefaces that form a mateface gap extending from an upstream edge of the platforms to a downstream edge of the platforms. A flow field of working gas adjacent to endwalls of the platform comprises streamlines extending generally transverse to the axial direction from a first airfoil toward an adjacent second airfoil. To achieve improved aerodynamic performance, the mateface gap has portions oriented transverse to the streamlines and oriented aligned with the streamlines. A step in elevation of the side edges at the transverse portion can include injected cooling flow in a direction that enhances attachment of the flow at a downstream side. | 01-03-2013 |
| 20130017091 | RADIAL TURBINE BACKFACE CURVATURE STRESS REDUCTIONAANM Duong; Loc QuangAACI San DiegoAAST CAAACO USAAGP Duong; Loc Quang San Diego CA USAANM Hu; XiaolanAACI San DiegoAAST CAAACO USAAGP Hu; Xiaolan San Diego CA USAANM Yang; GaoAACI San DiegoAAST CAAACO USAAGP Yang; Gao San Diego CA USAANM Jones; Anthony C.AACI San DiegoAAST CAAACO USAAGP Jones; Anthony C. San Diego CA US - A turbine wheel is disposed about an axis and has a back having a separator disposed thereon, an inner undercut disposed between the separator and the axis, and an outer undercut disposed between the separator and an outer periphery of the back face. The inner undercut is defined by a first radius blending toward the axis and into a first flat section, and further defined by a second radius blending into the first flat section and into the separator. | 01-17-2013 |
| 20130064667 | TURBINE BLADE AND NON-INTEGRAL PLATFORM WITH PIN ATTACHMENT - Platforms ( | 03-14-2013 |
| 20130224027 | SCALLOPED SURFACE TURBINE STAGE WITH PURGE TROUGH - A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a scalloped flow surface including a purge trough commencing tangentially in a blend area of the platform. The purge trough extending axially toward the suction side of the airfoil, aft of the leading edge, to channel a purge flow. | 08-29-2013 |
| 20140003949 | INTERBLADE PLATFORM FOR A FAN, ROTOR OF A FAN AND ASSOCIATED MANUFACTURING METHOD | 01-02-2014 |
| 20140056711 | AIRCRAFT ENGINE ANNULAR SHROUD COMPRISING AN OPENING FOR THE INSERTION OF BLADES - An aircraft engine annular shroud includes, on its internal surface, a peripheral annular groove able to accept a plurality of blade roots; an insertion opening for inserting the blade roots into the annular groove; and a closure device for closing off the insertion opening. | 02-27-2014 |
| 20140079552 | Attaching The Blades To The Drum Of An Axial Turbocompressor - The invention relates to the design of rotor blades of an axial turbomachine compressor, especially the method of attaching the blades to the rotor. The blades comprise an aerofoil portion and a platform for attaching them to the rotor. The platform comprises, along the main axis of the blade, a first layer forming a surface bounding the fluid stream and skirting the aerodynamic surfaces and a second layer, underneath the first layer with respect to the aerodynamic surfaces, designed to be able to mate with the inner face of a wall of the rotor around an aperture in the rotor for the purpose of attaching it. | 03-20-2014 |
| 20140161616 | MULTI-PIECE BLADE FOR GAS TURBINE ENGINE - A blade assembly for a gas turbine engine includes a rim seal including leading and trailing edge seal portions joined to one another by an axial portion. The leading and trailing edge seal portions and the axial portion together provide a notch. A blade has a root received in the notch. A rotating stage of a gas turbine engine includes a rotor including a slot. A rim seal includes leading and trailing edge seal portions adjoined to one another by an axial portion and providing a notch. A blade has a root received in the notch. A method of assembling a rotor stage includes inserting a root of a blade into a notch of a rim seal, and sliding the rim seal and blade into a rotor slot. | 06-12-2014 |
| 20140169973 | Ni-Based Heat Resistant Alloy, Gas Turbine Component and Gas Turbine - A Ni-based heat resistant alloy has a composition of, by mass percent, carbon: 0.001 to 0.1%, chromium: 16 to 22%, aluminum: 0.5 to 1.5%, molybdenum: 0.1 to 2.0%, tungsten: 0.1 to 6.0%, niobium: 3.5 to 5.5%, titanium: 0.8 to 3.0%, iron: 16 to 20%, and the balance being nickel and inevitable impurities. A parameter Ps indicating a segregation tendency is in a range of Ps≧−3.5. The parameter Ps is represented by Formula (1). | 06-19-2014 |
| 20140193265 | ROTOR DISK INCLUDING A PLURALITY OF HOOKS - A rotor disk comprises a plurality of circumferentially distributed hooks, the set of hooks defining an annular groove adapted to cooperate with at least two flange sectors. At least one of the hooks comprises a second element through which a recess is formed which opens up at each of the transverse flanks of the second element and at the internal peripheral surface of the second element. | 07-10-2014 |
| 20140212292 | Airfoil Member and Composite Platform Having Contoured Endwall - An airfoil member and platform assembly for a gas turbine engine is provided. The platform to which the airfoil member is anchored is made of a composite material and includes an endwall defining a contoured region for improved aerodynamics. The contoured region influences the flow of gases through the flow passages between the airfoil members, thereby reducing endwall losses due to horseshoe vortexing. The composite material may be woven ceramic matrix composite fibers infiltrated with a ceramic matrix material or woven organic matrix composite fibers infiltrated with an organic matrix material. | 07-31-2014 |
| 20140212293 | AIRCRAFT ROTOR BLADE AND RELATIVE FORMING METHOD - An aircraft rotor blade having a root portion having a through seat and designed for connection to the rotor; and a main portion extending from the root portion. The blade is produced by polymerizing an assembly having a main structure of composite material, and a composite material covering defining the outer surface of the blade. At the root portion, the main structure has a contoured block; and a lamina member extending about at least part of the block, and having a first part adhering to a first peripheral portion of the block, and a second part spaced apart from and facing a second peripheral portion of the block to form the seat; the lamina member having a pre-preg of continuous unidirectional fibres. | 07-31-2014 |
| 20140271205 | TURBINE BLADE PIN SEAL - A gas turbine engine turbine disk assembly includes a turbine disk, turbine blades, and pin seals. Each turbine blade includes a platform with a pressure side seal slot extending into a pressure side of the platform and a suction side seal slot extending into a suction side of the platform. The pressure side seal slot and the suction side seal slot are each angled between three and ten degrees in the radial direction relative to the axis of the turbine disk. The pin seal includes a cylindrical shape and is located within a seal slot formed from the pressure side seal slot and the suction side seal slot of adjacent turbine blades. | 09-18-2014 |
| 20140271206 | TURBINE BLADE WITH A PIN SEAL SLOT - A gas turbine engine turbine disk assembly includes a turbine disk, turbine blades, and pin seals. Each turbine blade includes a platform with a pressure side seal slot extending into a pressure side of the platform and a suction side seal slot extending into a suction side of the platform. The pressure side seal slot and the suction side seal slot are each angled between three and ten degrees in the radial direction relative to the axis of the turbine disk. The pin seal includes a cylindrical shape and is located within a seal slot formed from the pressure side seal slot and the suction side seal slot of adjacent turbine blades. | 09-18-2014 |
| 20140271207 | FAN BLADE - A rotor blade assembly for a gas turbine engine includes two aerofoil members joined together at their roots by a blade assembly attachment web. The rotor blade assembly is made from a composite material, for example an organic fibre composite material. The blade assembly attachment web is used to attach a plurality of rotor blade assemblies to the rest of the gas turbine engine in order to form a rotor stage. The rotor stage may, for example, be the fan stage of a turbofan gas turbine engine. | 09-18-2014 |
| 20140286777 | BLANK CASTING FOR PRODUCING A TURBINE ENGINE ROTOR BLADE AND PROCESS FOR MANUFACTURING THE ROTOR BLADE FROM THIS BLANK - The invention relates to a blank casting for producing a turbine engine rotor blade, with a vane connected by a platform ( | 09-25-2014 |
| 20140294587 | TURBINE ENGINE BLADE - The invention relates to a turbine engine blade ( | 10-02-2014 |
| 20140301850 | Turbomachine Blade Assembly - Embodiments of the present disclosure include a system comprising a turbomachine blade assembly having a blade portion, a shank portion, and a mounting portion, wherein the blade portion, the shank portion, and the mounting portion comprise a first plurality of plies extending from a tip of the airfoil to a base of the dovetail. | 10-09-2014 |
| 20140308133 | ROTOR WHEEL FOR A TURBINE ENGINE - A rotor wheel for a turbine engine, such as an airplane turboprop or turbojet, the rotor wheel including a rotor disk including teeth at its outer periphery defining slots for axially mounting and radially retaining blade roots. An annular lip includes an annular rim extending axially downstream from and radially towards an inside of a radial retaining mechanism formed to project axially from an upstream face of the disk, and a sealing mechanism is arranged radially inside the annular lip and upstream ends of platforms of the blades. | 10-16-2014 |
| 20140356172 | TURBINE WHEEL IN A TURBINE ENGINE - The invention relates to a turbine wheel ( | 12-04-2014 |
| 20140356173 | TURBINE ENGINE WHEEL, IN PARTICULAR FOR A LOW PRESSURE TURBINE - The invention relates to a turbine engine wheel ( | 12-04-2014 |
| 20140363299 | COMPOSITE MATERIAL REINFORCING PART OF PI-SHAPED SECTION, IN PARTICULAR A PLATFORM FOR A TURBINE ENGINE FAN, AND ITS METHOD OF FABRICATION - A reinforcing part of π-shaped section made out of composite material, and a method of making the part, the method including: making a first set of layers of interlinked yarns by three-dimensional weaving to form a first fiber blank portion to form a base preform; making a second set of layers of interlinked yarns by three-dimensional weaving to form a second fiber blank portion to form a stiffener preform, yarns of the second set being interlinked with yarns of the first set by weaving over a central interlinked strip that flares towards side edges of the first fiber blank portion in a zone corresponding to the step of the base; shaping the two fiber blank portions to obtain a single-piece fiber preform having a portion forming a base preform and a portion forming a stiffener preform; and depositing a resin in the fiber preform to form a matrix. | 12-11-2014 |
| 20150023793 | TURBOMACHINE ROTOR BLADE - A turbomachine rotor blade presenting an outer part ( | 01-22-2015 |
| 20150050150 | ANNULUS FILLER - An annulus filler, mounted to a rotor disc of a gas turbine engine and bridging the gap between two adjacent blades attached to the rotor disc, is disclosed. The annulus filler, formed from a polymer matrix composite material, includes an outer lid, defining an airflow surface for air drawn through the engine in an axial airflow direction, and a support structure, connectable to the rotor disc, to support the rear of the lid on the rotor disc. The support structure has two support walls extending from opposing lateral sides of the lid to an attachment strap for receiving a hook on the rotor disc, the attachment strap bridging the support walls. Under centrifugal loads, the opposing support walls resiliently deform. Each support wall has a concave rear edge. Each rear edge has a first curved section, a second curved section and a substantially straight section therebetween. | 02-19-2015 |
| 20150071783 | TURBINE BLADE - A turbine blade is provided having a blade and a modular platform which follow one another along a longitudinal axis of the turbine blade. In order to provide a modular turbine blade that has an especially plain and simple design and that ensures an especially reliable, long-lasting, durable connection of the individual components among each other, the blade has an extension and the platform has an outer platform part and an at least two-part inner platform part which is radial in relation to the longitudinal axis and which lie laterally against the extension of the blade, and the outer platform part is designed as an endless platform frame that surrounds the outer edge of the inner platform part. | 03-12-2015 |
| 20150118055 | GAS TURBINE ENGINE ROTOR ASSEMBLY AND METHOD OF ASSEMBLING THE SAME - A rotor assembly includes a rotor disc including a plurality of circumferentially-spaced diskposts and a plurality of dovetail slots. Each dovetail slot is defined between a pair of circumferentially-adjacent diskposts. A plurality of rotor blades are coupled to the rotor disc. Each rotor blade includes a dovetail portion that is configured to slidably engage a respective dovetail slot. A plurality of platform sections are coupled to the rotor disc such that each platform section is adjacent a respective rotor blade. Each platform section includes a diskpost slot that is configured to receive one of the plurality of diskposts such that each dovetail slot receives a respective dovetail portion and at least a portion of at least one of the platform sections adjacent the rotor blade. | 04-30-2015 |
| 20150125305 | LOW PROFILE FAN PLATFORM ATTACHMENT - A platform for a fan of a gas turbine engine includes a body portion, a forward flange at a front of the body portion that includes an engagement feature that interacts with a forward flange of a lug of a hub of a fan of a gas turbine engine, and a pin integral with a rear portion of the body portion. The pin is receivable in an aperture in a rear flange of the lug. | 05-07-2015 |
| 20150139808 | Rotor of a turbomachine - A rotor of a turbomachine. The rotor includes at least one blade ( | 05-21-2015 |
| 20150308279 | ROTATING ASSEMBLY FOR A TURBOMACHINE - A rotating assembly for a turbomachine, including a disc having an external periphery with alternating recesses and teeth, blades extending radially from the disc and the feet of which are axially engaged and radially retained in the recesses of the disc, platforms extending on the circumference from the blades and being arranged end to end on the circumference, with respect to each other, axial sealing device upstream and/or downstream of an annular zone extending radially from the platforms up to the disc. The sealing device radially includes an internal annular portion and an external annular portion structurally distinct from each other, and the external annular portion of which is elastically constrained radially inwards by the internal annular portion. | 10-29-2015 |
| 20160069196 | REPAIRED OR REMANUFACTURED BLADE PLATFORM FOR A GAS TURBINE ENGINE - A article of manufacture, the article having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1, and wherein X and Y are distances in inches which, when connected, define profile sections at each distance Z in inches to form a portion of a rotor blade. | 03-10-2016 |
| 20160153303 | SNAP IN PLATFORM DAMPER AND SEAL ASSEMBLY FOR A GAS TURBINE ENGINE | 06-02-2016 |
| 20160186572 | TURBINE BLADE PLATFORM UNDERCUT WITH DECREASING RADII CURVE - A turbine blade has an undercut beneath its platform proximate a trailing edge region. The undercut incorporates a curved portion to reduce to reduce undesirable stress concentration. The undercut shape includes a curved portion of decreasing radius with increasing distance from the underside of the platform. | 06-30-2016 |
| 20160252102 | ROTARY ASSEMBLY FOR AN AVIATION TURBINE ENGINE, THE ASSEMBLY COMPRISING A SEPARATE FAN BLADE PLATFORM MOUNTED ON A FAN DISK | 09-01-2016 |
