Having Mounting Or Supporting Structure Patents (Class 60/796)
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Publication number: 20150013344Abstract: The present disclosure relates generally to the field of tubes for carrying fluids. More specifically, the present disclosure relates to a tube having an oval shaped cross-section. In some embodiments, the tube with oval cross-section comprises a tube within a cavity in a gas turbine engine.Type: ApplicationFiled: July 3, 2014Publication date: January 15, 2015Inventors: Pawel Socha, Venu Ponnala, Usman Khan, Ryan Snyder
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Patent number: 8925332Abstract: A seal assembly for a turbojet nacelle includes a first end fastened to a first structure, and a second end contacting against a bearing zone of a second structure. The seal assembly further includes a plurality of adjacent blades arranged along the first end and extending longitudinally and perpendicularly thereto. In particular, a portion of the blades has an accordion-shaped structure.Type: GrantFiled: September 30, 2013Date of Patent: January 6, 2015Assignee: AircelleInventors: Stephane Beilliard, Alexandre Phi
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Patent number: 8925326Abstract: A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and an aerodynamic mounting assembly disposed in the air passage. The aerodynamic mounting assembly is configured to retain the combustion liner within the flow sleeve. The aerodynamic mounting assembly includes a flow sleeve mount coupled to the flow sleeve and a liner stop coupled to the combustion liner. The flow sleeve mount includes a first portion of an aerodynamic shape and the liner stop includes a second portion of the aerodynamic shape, which is configured to direct an airflow into a wake region downstream of the aerodynamic mounting assembly. The flow sleeve mount and the liner stop couple with one another to define the aerodynamic shape.Type: GrantFiled: May 24, 2011Date of Patent: January 6, 2015Assignee: General Electric CompanyInventors: David William Cihlar, Patrick Benedict Melton, Robert Joseph Rohrssen
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Publication number: 20150000305Abstract: A variable area fan nozzle comprising an array of rigid petals and a petal actuation system comprising left and right assemblies, each assembly comprising: a multiplicity of tracks attached to or integrally formed with respective petals; a curved pivoting ring segment; an actuator coupled to the ring segment; and a multiplicity of sets of cam followers spaced along the ring segment and aligned with respective tracks. Each ring segment is pivotable between first and second angular positions depending on how the state of the actuator changes. As one ring segment pivots in one direction, one set of cam followers exert inward forces on the tracks to deflect petals inward; as that ring segment pivots in the other direction, another set of cam followers exert outward forces on the tracks to deflect petals outward.Type: ApplicationFiled: June 27, 2013Publication date: January 1, 2015Applicant: The Boeing CompanyInventor: Christopher T. Jasklowski
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Publication number: 20150000306Abstract: A support, for example for a turboshaft engine, or for at least one bearing for a hot section of a turboshaft engine. The support includes at least a central hub incorporating an outer bearing seat for directly receiving the bearing, an annular casing segment around the central hub, and a plurality of radial arms connecting the central hub to the casing segment. The radial arms are inclined in an axial direction and in a tangential direction and are integrated as a single piece with the central hub and with the annular casing segment.Type: ApplicationFiled: January 11, 2013Publication date: January 1, 2015Applicant: TURBOMECAInventors: Jean-Francois Perronnet, Jean-Luc Breining, Manuel Silva
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Patent number: 8919136Abstract: An after-body assembly for an aeroengine, the assembly comprising an annular part (60) made of metallic material secured to the aeroengine and an after-body part (20) made of ceramic matrix composite material, the after-body part (20) being mounted on the annular part (60) by resiliently flexible fastener tabs (70) and having a first end (71) fastened to the annular part (60) and a second end (72) fastened to the upstream portion of the after-body part (20). Each fastener tab (70) includes an axial abutment element (720) that extends radially from the second end (72) of the tab and having at least a portion thereof facing the first end (71). The fastener tab (70) also includes a radial abutment element (721) at the second end (72) of the tab, the radial abutment element (721) at least partially overlying the first end (71).Type: GrantFiled: September 8, 2009Date of Patent: December 30, 2014Assignee: HeraklesInventor: Eric Conete
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Patent number: 8919133Abstract: A double-body gas turbine engine, including a low-pressure body LP and a high-pressure body HP, rotatably mounted about a single shaft in a stationary casing, the low-pressure body LP including a compressor and a turbine connected by a low-pressure shaft LP. The low-pressure shaft LP is supported by an upstream LP bearing, a first downstream LP bearing, and an additional downstream LP bearing by the stationary casing, the high-pressure body being supported by an upstream HP bearing and a downstream HP bearing which is an inter-shaft bearing including an inner track rigidly connected to the HP turbine rotor and an outer track rigidly connected to the LP shaft.Type: GrantFiled: April 15, 2010Date of Patent: December 30, 2014Assignee: SnecmaInventors: Jacques René Bart, Didler René André Escure, Ornella Gastineau
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Patent number: 8919134Abstract: An assembly for gas turbine engine includes a cross-over housing, an inter-shaft seal housing, and a linkage. The inter-shaft seal housing is disposed within the cross-over housing. The linkage is connected to the inter-shaft seal housing and extends through a slot in the cross-over housing. The linkage is removable from both the inner radial housing and the outer radial housing.Type: GrantFiled: January 26, 2011Date of Patent: December 30, 2014Assignee: United Technologies CorporationInventors: Neil L. Tatman, Christopher J. Larson
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Publication number: 20140373556Abstract: The present invention relates to a support structure (16) for a gas turbine engine (1). The support structure (16) has an axial extension in an axial direction (A) and a circumferential extension in a circumferential direction (C). Moreover, the support structure (16) comprises a plurality of tubular members (18, 20) of a first material type arranged in sequence in the circumferential direction (C). Each tubular member (18, 20) at least partially delimits a flow guiding passage extending at least partially in the axial direction (A). The support structure (16) comprises a leading portion (22) and a trailing portion (24) in the axial direction (A). Furthermore, the support structure (16) comprises a leading edge member (26) of a second material type, the leading edge member (26) being located at the leading portion (22). At least two of the tubular members (18, 20) are fixedly attached to a leading edge member (26).Type: ApplicationFiled: December 23, 2011Publication date: December 25, 2014Applicant: GKN AEROSPACE SWEDEN ABInventors: Egon Aronsson, Per Widstrom, Elinor Magnusson, Johan Thoreus, Christian Lundh
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Publication number: 20140373555Abstract: A gas turbine engine assembly is connected to a pylon for mounting the gas turbine engine to an aircraft. The assembly has a frame supporting at least one accessory independently of the gas turbine engine. Frame is attached to the pylon at forward and rearward engine mounting locations. The frame includes at least one hollow tube and at least one hollow tube is fluid tight. The one hollow tube is evacuated or contains pressurised fluid and a pressure sensor is provided to detect a change in pressure in the at least one hollow tube to determine if there is a leak in the at least one hollow tube and hence if the frame is damaged. This ensures that the frame may be repaired or replaced before there is a loss of operation of one or more of the accessories which may result in a failure of the gas turbine engine.Type: ApplicationFiled: June 10, 2014Publication date: December 25, 2014Inventors: Jürgen BEIER, Gideon Daniel VENTER
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Patent number: 8915090Abstract: A gas turbine engine includes first and second stages having a rotational axis. A circumferential array of airfoils is arranged axially between the first stage and the second stage. At least one of the airfoils have a curvature provided equidistantly between pressure and suction sides. The airfoils extend from a leading edge to a trailing edge at a midspan plane along the airfoil. An angle is defined between first and second lines respectively tangent to the intersection of the midspan plane and the curvature at airfoil leading and trailing edges. The angle is equal to or greater than about 10°.Type: GrantFiled: March 21, 2014Date of Patent: December 23, 2014Assignee: United Technologies CorporationInventors: Thomas J. Praisner, Shankar S. Magge, Matthew B. Estes
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Publication number: 20140366555Abstract: A gas turbine engine assembly is connected to a pylon for mounting the gas turbine engine to an aircraft. The assembly has a frame supporting at least one accessory independently of the gas turbine engine. The frame is attached to the pylon at forward and rearward engine mounting locations. The frame comprises at least one hollow tube and at least one duct is arranged to supply coolant into the at least one hollow tube and the at least one hollow tube is arranged to supply coolant to the at least one accessory.Type: ApplicationFiled: May 22, 2014Publication date: December 18, 2014Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KGInventor: Jürgen BEIER
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Patent number: 8899051Abstract: The disclosure is directed to a unique apparatus having a gas turbine engine flange assembly. Also disclosed is a unique system having a gas turbine engine flange assembly in which a fluid flow circuit is provided. Also disclosed are apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engine flange assemblies, in which a fluid flow circuit extends between flanges or from a cavity within a turbine engine case to an interior portion of a flange assembly.Type: GrantFiled: December 24, 2011Date of Patent: December 2, 2014Assignee: Rolls-Royce CorporationInventors: Edward Claude Rice, Naveen Rau, Robert C Koth
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Patent number: 8899010Abstract: A pulse detonation combustor including a plurality of nozzles engaged with one another via mating surfaces to support a gas discharge annulus in a circumferential direction. The pulse detonation combustor also including multiple pulse detonation tubes extending for the nozzles and a plurality of thermal expansion control joints coupled to the plurality of pulse detonation tubes. Each of the plurality of thermal expansion control joints is configured to facilitate independent thermal growth of each of the plurality of pulse detonation tubes. The thermal expansion control joints may be configured as a bellows expansion joint or a sliding expansion joint.Type: GrantFiled: November 17, 2010Date of Patent: December 2, 2014Assignee: General Electric CompanyInventors: Ross Hartley Kenyon, Adam Rasheed, Paul Whitson Dom, Jr., Mark Joseph Pombles
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Publication number: 20140341722Abstract: A device for axially arresting a sealing ring made of an abradable material in contact with a periphery of an aircraft turbomachine module rotor, the device having a first reference central axis, and including: a support including a support opening defining a circular track centered on a second axis at a distance from the axis; and an axial stop part including an extraction passage centered on a third axis at a distance from the axis, and defining a complementary circular track around its periphery, cooperating with the track to allow the part to rotate about the axis, between an axial stop position for the sealing ring, and a position to extract the ring through the extraction passage.Type: ApplicationFiled: December 4, 2012Publication date: November 20, 2014Applicant: SNECMAInventors: Olivier Belmonte, Sebastien Jean Laurent Prestel
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Patent number: 8887511Abstract: The present invention relates to a nacelle (1) for a jet engine (4) comprising a forward air inlet section (5), a mid-section (6) intended to surround a jet engine fan, and an aft section (9), at least one portion forming the aft section being connected to the mid-section via an at least partially peripheral radial knife-edge (31) capable of engaging by complementarity of shape with a corresponding groove (32) belonging to a portion (6a) of the mid-section, characterized in that the knife-edge comprises at least one reinforcing segment (35, 36) situated in a region for accommodating high loads, said reinforcing segment being made from a material which is stronger than the remainder of the knife-edge and tailored to the loads which are to be borne by said segment in this region.Type: GrantFiled: May 19, 2008Date of Patent: November 18, 2014Assignee: AircelleInventors: Etienne Germain, Jean-Yves Elegoët, Patrice Dhainault
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Publication number: 20140325993Abstract: An electrical harness assembly is provided that comprises a flexible printed circuit electrically connected to one end of an electrical connector. The other end of the electrical connector is presented for connection to another electrical component. Electrical tracks or conductors in the flexible printed circuit terminate in receiving holes. The electrical connector comprises terminals, each of which has a first end that is received in one of the receiving holes to form a connection formation, and a second end which is present for connection to the other electrical device. The connection formation is encapsulated so as to be sealed, thereby providing a reliable and robust connection between the connector and the flexible printed circuit.Type: ApplicationFiled: April 24, 2014Publication date: November 6, 2014Inventors: Paul BROUGHTON, Jonathan WILSON
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Publication number: 20140325992Abstract: An electrical unit comprises an electrical connector having a set of elongate electrical terminals which are each a one-piece component. The terminals extend into the unit such that first ends of the terminals are connected to multiple electrical conductors within the unit and second ends of the terminals project from a surface of the unit. A collar is formed at the surface of the unit to at least partially encircle the projecting second ends. This arrangement allows the unit to be electrically connected at the electrical connector by press fitting to a terminating region of a flexible electrical harness, the collar defining a recess in which the terminating region is located.Type: ApplicationFiled: April 9, 2014Publication date: November 6, 2014Applicant: ROLLS-ROYCE PLCInventor: Philip SUMMERFIELD
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Patent number: 8876042Abstract: An assembly includes a unitary nacelle structure and an integrated fan housing for a gas turbine engine assembly. The unitary nacelle structure includes an inlet region and a fan cowl region, and is configured to at least partially circumscribe the integrated fan housing. The integrated fan housing comprises an integral composite structure and includes a fan case sized and configured for encircling a fan blade assembly of an associated gas turbine engine, a fan hub, and a plurality of fan outlet guide vanes. The unitary nacelle structure cooperates with the integrated fan housing to transfer static and dynamic loads directly to a support structure, rather than through the engine core, to minimize backbone bending.Type: GrantFiled: June 30, 2010Date of Patent: November 4, 2014Assignee: General Electric CompanyInventors: Donald George LaChapelle, Christopher Charles Glynn, Donald Lee Gardner, Stephen Craig Mitchell, Mullahalli Venkataramaniah Srinivas, Edward Atwood Rainous, David Lance Pennekamp
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Patent number: 8875486Abstract: A guide system for translating components of an aircraft engine nacelle includes a track assembly and a slider assembly. The track assembly includes a track guide member and a track liner engaged therewith. The track guide member includes a track channel configured to receive the track liner. The track liner defines an interior surface and includes a projection portion projecting inwardly of the track channel to define a convex surface. The slider assembly translatably engages the track assembly and includes a slider member having a head portion configured to be received within the track channel. The head portion defines a concave surface substantially corresponding to the convex surface of the track liner and is configured to mate therewith. The slider member further includes an extension portion extending from the head portion and outwardly of the track assembly.Type: GrantFiled: May 17, 2010Date of Patent: November 4, 2014Assignee: Rohr, Inc.Inventor: Stephen Michael Roberts
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Patent number: 8875520Abstract: A gas turbine engine adapter is provided. In one form the adapter is segmented and may be attached to a gas turbine engine support ring. The adapter can provide a channel that may receive part of a gas turbine engine component such as, but not limited to, a plug nozzle. The adapter can include a load bearing support to counteract axial forces experienced by the plug nozzle during operation of the gas turbine engine. A compressible seal can be provided between the plug nozzle and the adapter. A leaf seal can also be provided to seal between segments of the adapter. The plug nozzle can be discouraged from rotating relative to the adapter.Type: GrantFiled: December 9, 2009Date of Patent: November 4, 2014Assignee: Rolls-Royce North American Technologies, Inc.Inventors: Gregory W. P. Zeaton, David L. Sutterfield, Sean F. Sullivan
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Patent number: 8876448Abstract: A shipping fixture for a turbine lower casing includes a frame having a substantially rectangular shape including a pair of elongated, laterally-spaced side beams and a pair of transverse end beams. A first lateral support structure extends between the side beams at a first location corresponding to a first vertically-oriented joint between the turbine compressor casing section and the turbine combustor casing section; and a second lateral support structure includes support blocks mounted on the side beams at a second location corresponding to a second vertically-oriented joint between the turbine combustor casing section and the turbine stage casing section.Type: GrantFiled: August 28, 2013Date of Patent: November 4, 2014Assignee: General Electric CompanyInventors: John Raymond Hess, Netaji Haribhau Mane, Gregory Allan Crum, Jason Allen Seale, David William Hogg
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Publication number: 20140318149Abstract: A fire-resistant seal for a propulsion assembly which includes a pylon, an O-duct type nacelle of a turbojet engine. The nacelle includes an inner fixed nacelle structure and a combustion gas ejection primary nozzle, and the fire-resistant seal is placed in an annular sector defined by the inner fixed nacelle and the gas ejection primary nozzle. In particular, the fire-resistant seal includes a plurality of baffles, and the plurality of baffles are longitudinally disposed so as not to interfere each other during a longitudinal translational movement of the inner fixed nacelle structure relative to the combustion gas ejection primary nozzle.Type: ApplicationFiled: July 7, 2014Publication date: October 30, 2014Inventors: Jean-Bernard Guillon, Alexandre Phi, Stéphane Beilliard
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Publication number: 20140318148Abstract: The present invention relates to a combustion chamber for a gas turbine with a combustion chamber head and a heat shield which are designed in one piece, with the heat shield being provided with at least one recess, in which is arranged a burner or an annular sleeve enclosing the burner, with a burner seal being provided between the heat shield and the burner, characterized in that the heat shield is provided in the area of the recess with an annular groove, in which is arranged at least one elastic sealing element forming the burner seal.Type: ApplicationFiled: April 29, 2014Publication date: October 30, 2014Applicant: Rolls-Royce Deutschland Ltd & Co KGInventors: Carsten CLEMEN, Michael EBEL
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Patent number: 8869536Abstract: A liner stop for retaining a flow sleeve relative to a combustion liner in a combustor is disclosed. The liner stop includes a female component defining a recess and a male component comprising a protrusion, the protrusion insertable in the female component. The liner stop further includes an insert disposable between the female component and the male component, the insert comprising a surface protrusion configured to interfere with one of the female component or the male component.Type: GrantFiled: July 26, 2012Date of Patent: October 28, 2014Assignee: General Electric CompanyInventors: Robert Wade Clifford, Jonathan Hale Kegley
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Patent number: 8869539Abstract: An arrangement for connecting at least one duct with an air-distribution casing, the at least one duct including two sidewalls opposite one another and including a peripheral wall connecting edges of the two sidewalls. The arrangement includes a connecting tube that extends through the casing, passes through an orifice associated with each of the two sidewalls, and is connected to the at least one duct. A system controlling clearance of a turbo engine and a turbo engine can include air-injection ducts connected to the distribution casing by such an arrangement.Type: GrantFiled: June 29, 2012Date of Patent: October 28, 2014Assignee: SnecmaInventor: Luc Henri Claude Daguenet
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Patent number: 8869538Abstract: A gas turbine engine is disclosed having a compressor, combustor, and turbine and a flow path therethrough. A flow path member is disposed between an inner surface of the flow path and a rotating shaft that couples the compressor and turbine. The flow path member directs a cooling fluid along a path to cool a portion of the gas turbine engine between the inner surface and the rotating shaft. The flow path member is retained to permit radially free motion and can also be retained to permit axially free motion. The flow path member can have feed holes that permit the cooling fluid to pass.Type: GrantFiled: December 22, 2011Date of Patent: October 28, 2014Assignee: Rolls-Royce North American Technologies, Inc.Inventors: Sujit Nanda, Todd S. Taylor, Brad Farris
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Publication number: 20140311161Abstract: A method for creating a connecting element, arranged between two components of a structure, or a turbojet engine structure, which is subjected to compressive and/or tensile loadings and which includes a hollow shaft immersed, at least partially, in a stream of air flowing between the two components, the method including: dimensioning a width of the main cross section associated with the shaft of the connecting element in a direction orthogonal to the longitudinal axis of the shaft according to desired mechanical strength and desired mass, and according to characteristics of the airstream; and working an external surface of the shaft of the connecting element, at least over part of this surface, to give it a surface finish with an arithmetic mean roughness at least equal to 20 microns, to reduce drag of the connecting element thus dimensioned by comparison with a smooth connecting element of the same diameter.Type: ApplicationFiled: December 10, 2012Publication date: October 23, 2014Applicant: SNECMAInventors: Francois Robert Bellabal, Eric De Vulpillieres
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Publication number: 20140311160Abstract: A hybrid turbomachine enclosure includes a plurality of walls interconnected to form an interior configured and disposed to receive a turbomachine, the plurality of walls including a first wall having a panel on frame construction and a hybrid wall including a first portion having a panel on frame structure and a second portion having a stiffened frame panel structure.Type: ApplicationFiled: August 6, 2013Publication date: October 23, 2014Applicant: General Electric CompanyInventors: Kiran Swarup Kasturi, Antoine Hochar, Dinesh Venugopal Setty
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Patent number: 8864067Abstract: An auxiliary power unit is composed of a gas turbine engine, a gearbox, and a gearbox driven generator. A mount bracket is mechanically attached to the gearbox. The bracket is for connecting to an aircraft strut system. The aircraft strut system connects to the aircraft structure. The mount bracket has an upper mechanical attachment point and a lower mechanical attachment point to the gearbox. The gearbox includes an oil reservoir, and the lower attachment point is beneath the oil level within the oil reservoir such that said lower attachment point will be cooled by oil in the oil reservoir.Type: GrantFiled: May 31, 2012Date of Patent: October 21, 2014Assignee: Hamilton Sundstrand CorporationInventors: Melissa A. Bell, Michael J. Rollins, Jason Peel, Greg R. Giddings
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Patent number: 8863527Abstract: A combustor liner for a turbine engine is disclosed herein. The combustor liner includes an inner liner surface operable to define at least part of a combustion chamber in a turbine engine. The inner liner surface extends along a portion of a chordal arc on a first side of the chordal arc. The combustor liner also includes a bearing surface operable to support a floating dome panel. At least part of the bearing surface is spaced from the chordal arc on a second side of the chordal arc opposite the first side.Type: GrantFiled: April 30, 2009Date of Patent: October 21, 2014Assignee: Rolls-Royce CorporationInventors: Marcus Timothy Holcomb, Todd Taylor, Randall E. Yount
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Publication number: 20140305129Abstract: Support strut assembly for supporting a casing of a functional unit of gas turbine is provided having a strut body for supporting the casing to ground, a ball pivot element mounted to the strut body and a rocker lever mounted to the ball pivot element. The rocker lever inserts into a bearing bore of a support body as part of the casing or ground, the rocker lever inserts into the bearing bore via clearance fit so a pivotal point is generated at a first contact area between the rocker lever and an inner surface of the bearing bore, the rocker lever pivots within the bearing bore around the pivotal point. An elastomeric springing damping element is mounted to the rocker lever between the rocker lever and the a support body providing centering force and damping pivoting of the rocker lever with respect to the support body around the pivotal point.Type: ApplicationFiled: September 13, 2012Publication date: October 16, 2014Applicant: SIEMENS AKTIENGESELLSCHAFTInventors: Colm Keegan, Kevin Scott, Neil Simmons
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Publication number: 20140305134Abstract: A rigid raft is provided for a gas turbine engine. The raft has an electrical system and/or a fluid system embedded in the material of the raft. The raft further has one or more first mounts for mounting the raft to the gas turbine engine, and one or more second mounts for mounting a gas turbine engine component to the raft. The raft further has one or more tethers which extend between respective first and second mounts and are embedded in the material of the raft.Type: ApplicationFiled: March 31, 2014Publication date: October 16, 2014Inventors: Ashan AMARASINGHE, Michael Christopher WILLMOT
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Patent number: 8851417Abstract: A shear pin connection for use in a difficult to access location has a bolt head to be positioned at an inner end of a bearing. A bushing is received between the bolt and an inner periphery of the bearing. A lock member is positioned between an inner end of the bushing and the bolt head. The lock member is radially expandable, and has a free radially outer dimension that is smaller than an inner dimension of the inner bore. The lock member is expandable to have an expanded radially outer dimension that is greater than the inner dimension of the inner bore. A nut is tightened on the outer end of the bolt. The nut causes the bushing to move relative to the bolt, and causes the lock member to expand radially. A shackle connection for a gas turbine engine and an aircraft are also disclosed.Type: GrantFiled: August 7, 2012Date of Patent: October 7, 2014Assignee: United Technologies CorporationInventor: David F. Sandy
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Patent number: 8851416Abstract: An aircraft nacelle that makes it possible to channel a stream of air in a longitudinal direction and that includes at least two panels (50, 50?) placed end to end in the longitudinal direction, each including a so-called aerodynamic surface (52, 52?) that is in contact with the air stream and an edge (54, 54?) that is in contact with the edge of the other panel, characterized in that at least one of the panels includes—at its edge (54, 54?)—at least one partition (58) that projects relative to the edge that extends in the direction of the edge of the other panel, in a manner that is secant to the aerodynamic surface and in a plane that contains the longitudinal direction, so as to limit the circulation of air between the edges of the panels.Type: GrantFiled: October 11, 2011Date of Patent: October 7, 2014Assignee: Airbus Operations (S.A.S.)Inventors: Alain Porte, Jacques Lalane, Frederic Chelin, Thierry Surply
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Publication number: 20140290268Abstract: A gas turbine engine includes a fan, an engine static structure, a geared architecture to drive the fan and supported relative to the static structure, a fan drive turbine to drive the geared architecture, a first member secured to the geared architecture, and a second member secured to the engine static structure and configured to cooperate with the first member to limit movement of the geared architecture relative to the static structure. A fan drive gear system and method are also disclosed.Type: ApplicationFiled: June 17, 2014Publication date: October 2, 2014Inventors: James B. Coffin, Alessio Pescosolido
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Patent number: 8844297Abstract: A gas turbine includes a gas turbine body in which a rotor is rotated with the energy of combustion gas produced by combustion of fuel to take out rotational energy from the rotor, an inlet casing that is attached to the gas turbine body and that guides the air to a compressor section compressing the air, an air intake chamber that is connected to the inlet casing and that guides the air taken in from the atmosphere to the gas turbine body, and a notch so formed in the air intake chamber as to cover the entire range where the rotor passes or exists when the rotor is moved.Type: GrantFiled: January 8, 2009Date of Patent: September 30, 2014Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Kenichi Arase, Yasuro Sakamoto, Shinya Hashimoto
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Patent number: 8844862Abstract: This invention relates to an aft pylon fairing for the suspension system of an aircraft engine, comprising a main structure extending along a longitudinal direction of said fairing and integrating two side panels connected to each other, the fairing also comprising a heat protection deck mounted on said main structure through connection means comprising tabs designed to deform to accompany displacement of the deck relative to the main structure, if there is differential thermal expansion between these two entities.Type: GrantFiled: October 16, 2012Date of Patent: September 30, 2014Assignee: Airbus Operations (S.A.S.)Inventor: Frédéric Journade
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Publication number: 20140283528Abstract: To assemble an aftertreatment module for use in the treatment of exhaust gasses and the like, an aftertreatment brick is inserted into a sleeve opening in a sleeve and advanced toward an opposite end of the sleeve. To retain the aftertreatment brick in the sleeve, the end of the sleeve can include a stop flange and the aftertreatment brick can include a mantle flange. The stop flange and the mantle flange can abut against each other to prevent further movement of the aftertreatment brick through the sleeve. To seal against exhaust gasses leaking though the module, a gasket can be disposed between the stop flange and the mantle flange. Exterior ribs disposed around the aftertreatment brick can assist concentric alignment between the flanges and gasket.Type: ApplicationFiled: March 22, 2013Publication date: September 25, 2014Applicant: Caterpillar Inc.Inventors: Andrew M. Denis, Mirza P. Baig, Nilkanth N. Desai, Rick E. Jeffs, Kristian N. Engelsen, Pradyumna V. Rao, Ian Aguirre
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Patent number: 8840061Abstract: This strut (9), designed to support an aircraft turbojet engine, has, on the one hand, a connecting part (11) for connection between the casing (1) of the fan (3) or the casing of the gas generator (5) of the said turbojet engine and a wing of the said aircraft and, on the other hand, a Y-shaped box-section part (19), secured to the said connecting part (11) and designed to form the upper part of the inner fixed structure of the said nacelle.Type: GrantFiled: August 5, 2009Date of Patent: September 23, 2014Assignee: AircelleInventors: Pierre Caruel, Guy Bernard Vauchel
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Patent number: 8840059Abstract: This assembly comprises a first component (9), a second component (3), and a connecting device (19) for connecting these two components together, this device (19) being of the type that maintains the integrity of the surface of said second component (3), and the assembly being noteworthy in that said connecting device (19) comprises a structural skin (21) fixed to said first component (9) and a porous material (23) attached to this structural skin and fixed by contact to said second component (3).Type: GrantFiled: July 28, 2009Date of Patent: September 23, 2014Assignee: AircelleInventors: Guy Bernard Vauchel, Guillaume Ruckert
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Patent number: 8839629Abstract: An assembly is designed to attach hangers from which an aircraft propulsion unit is suspended. The propulsion unit is intended to be suspended from a structural element of the aircraft. The propulsion unit includes a turbojet engine having a longitudinal axis and the attachment assembly having a clevis mount for attaching the hangers to a casing of the propulsion unit. The clevis mount is fixed to the casing by means designed to form a connection between the clevis mount and the casing at the external periphery of the casing.Type: GrantFiled: April 15, 2013Date of Patent: September 23, 2014Assignees: Aircelle, SNECMAInventors: Herve Hurlin, Nicolas Dezeustre, Wouter Balk, Gilles Charier
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Publication number: 20140260316Abstract: A combustion system for a gas turbine engine including a combustor assembly comprising a combustor basket having a downstream terminal end, and a transition duct extending downstream from the combustor basket and having an upstream end located adjacent to the downstream terminal end of the combustor basket. A coupling is provided comprising an inlet ring adapter including a cylindrical sleeve extending downstream of the upstream end of the transition duct in overlapping relation to an inner surface of the transition duct. A spring clip assembly is mounted to the terminal end of the combustor basket. The spring clip assembly extends into engagement with and forms a seal on the cylindrical sleeve.Type: ApplicationFiled: March 14, 2013Publication date: September 18, 2014Inventors: Adam J. Weaver, Lashanda N. Oliver, Daniel W. Garan, Ashtad Kotwal
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Publication number: 20140260319Abstract: A gas turbine comprises a compressor discharge casing that is coupled to an outer turbine shell. The compressor discharge casing includes a combustor opening that extends through the compressor discharge casing and an outer mating surface that circumferentially surrounds the combustor opening. The outer turbine shell defines an inner mating surface. A combustion module extends through the combustor opening. The combustion module includes a forward end that is circumferentially surrounded by a mounting flange and an aft end that is circumferentially surrounded by an aft frame. The mounting flange extends circumferentially around the combustor opening. The mounting flange is coupled to the outer mating surface of the compressor discharge casing and the aft frame is coupled to the inner mating surface of the outer turbine shell.Type: ApplicationFiled: March 18, 2013Publication date: September 18, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Patrick Benedict Melton, Lucas John Stoia, Richard Martin DiCintio, Christopher Paul Willis
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Publication number: 20140260315Abstract: A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes an end cover, a first plate, and multiple tubes. The multiple tubes are disposed and supported in a floating arrangement between the end cover and the first plate. Each tube includes a forward end adjacent the end cover and an aft end adjacent the first plate.Type: ApplicationFiled: March 12, 2013Publication date: September 18, 2014Applicant: General Electric CompanyInventors: James Harold Westmoreland, Gregory Allen Boardman, Patrick Benedict Melton
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Publication number: 20140260320Abstract: An improved fastening system and method overcomes traditional thermal mismatch that occurs with standard fastener systems that are employed in extreme temperature environments. The fastening system could employ a metallic fastener that is combined with metallic spacer, each of which having a differing thermal growth coefficient. This arrangement may reduce thermal expansion by several orders of magnitude over the range of temperatures where the thermal fastener can be applied. Such an improved fastening system may be employed in gas turbine machines and in other locations where it is desirable to improve fastening of objects in extreme temperature environments.Type: ApplicationFiled: December 12, 2013Publication date: September 18, 2014Applicant: Rolls-Royce CorporationInventors: Charles B. Graves, Jack D. Petty, SR.
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Publication number: 20140260317Abstract: An exit piece (66) with an inlet throat (67) that conducts a combustion gas flow (36A) in a path (82) from a combustor (63) to an annular chamber (68) that feeds the first blade section (37) of a gas turbine (26). The exit piece further includes an outlet portion (69) that forms a circumferential segment of the annular chamber. The outlet portion interconnects with adjacent outlet portions by hinges (78A, 78B, 80A, 80B). Each hinge may have a hinge axis (82A, 82B) parallel to a centerline (21) of the turbine. Respective gas flows (36A) are configured by an assembly (60) of the exit pieces to converge on the feed chamber (68) into a uniform helical flow that drives the first blade section with minimal circumferential variations in force.Type: ApplicationFiled: March 15, 2013Publication date: September 18, 2014Inventors: Richard C. Charron, William W. Pankey
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Publication number: 20140260321Abstract: A gas turbine engine static structure has a joint that includes at least two flanges. The first flange includes a face extending axially proud between radially spaced apart undercuts. The second flange abuts the face. Fasteners secure the flanges to one another through the face.Type: ApplicationFiled: March 13, 2014Publication date: September 18, 2014Applicant: United Technologies CorporationInventors: James L. McClellan, IV, Gary L. Grogg, Garth J. Vdoviak, JR.
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Publication number: 20140260318Abstract: A side seal slot extends along a one side of an aft frame for a combustion liner of a gas turbine. The side seal slot is at least partially defined between a downstream wall and an upstream wall that extend outward from the first side of the aft frame. A first segment of the upstream wall extends from an inner portion of the aft frame towards an outer portion of the aft frame at a first outward distance from the first side. A second segment of the upstream wall extends from the first segment to the outer portion of the aft frame at a second outward distance from the first side. The second segment of the upstream wall at least partially defines a side seal guide feature to allow for axial insertion of a bottom portion of a side seal into the side seal slot.Type: ApplicationFiled: March 18, 2013Publication date: September 18, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Christopher Paul Willis, Richard Martin DiCintio, Ronnie Ray Pentecost, Christopher Crookshanks
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Publication number: 20140260308Abstract: A retention system includes a structure clamp to connect the retention system to another structure; and a manifold clamp connected to the structure clamp, the manifold clamp including a trough to receive a pipe, a plurality of tube clamps with split cylinders extending through the trough, a collar to clamp around the pipe, and a spring to bias the trough from the collar.Type: ApplicationFiled: March 13, 2013Publication date: September 18, 2014Applicant: ECOSERVICES, LLCInventors: Kurt Dorshimer, William J. Welch, Robert M. Rice, Sebastian Nordlund, Wayne Zadrick