Having Mounting Or Supporting Structure Patents (Class 60/796)
For motor (Class 60/797)
Having ease of assembly or disassembly feature (Class 60/798)
  • Combustor wall apparatus with parts joined by mechanical fasteners
    Patent number: 8408010
    Abstract: A lower cost combustor is formed from a series of sheets of metal that are secured by mechanical fasteners. An increase in diameter of the combustor is achieved through the provision of securing rings to which the sheets of metal are secured.
    Type: Grant
    Filed: February 4, 2009
    Date of Patent: April 2, 2013
    Assignee: Rolls-Royce PLC
    Inventors: Ian Murray Garry, Michael Lawrence Carlisle
  • Structural reinforcement strut for gas turbine case
    Patent number: 8408011
    Abstract: A gas turbine engine case having a working fluid flow, includes inner and outer case portions defining an annular duct for directing the working fluid flow, and a plurality of struts positioned within the annular duct and extending between the inner and outer case portions. The struts are welded to the inner and outer case portions with a first weld along a peripheral line of the respective struts and with second weld, of fillet type, in selected locations for additionally connecting a portion of each strut to the respective inner and outer case portions.
    Type: Grant
    Filed: April 30, 2009
    Date of Patent: April 2, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Mike Fontaine, Rene Paquet, Jean Fournier
  • Seal assembly for use with turbine nozzles
    Patent number: 8403634
    Abstract: A retaining seal assembly for use in a gas turbine engine is provided. The retaining seal assembly comprises an outer retaining ring coupled to an aft end of a gas turbine engine combustor. A turbine nozzle is coupled to the outer retaining ring and comprises an outer band. The outer band comprises a leading edge and an opposing trailing edge that defines a slot. A retention seal comprises a first end positioned within the slot, a generally opposing second end that contacts the outer retaining ring, and a body extending between the first end and the second end. The body further comprises an insertion portion positioned within a passage formed in the outer band. The retention seal is fabricated from a resilient material and is configured to facilitate coupling the turbine nozzle to the outer retaining ring.
    Type: Grant
    Filed: August 24, 2011
    Date of Patent: March 26, 2013
    Assignee: General Electric Company
    Inventors: Brian P. Arness, John E. Greene, Sze Bun B. Chan
  • Casing of a gas turbine engine having a radial spoke with a flow guiding element
    Patent number: 8402769
    Abstract: A section of a gas turbine engine including a radial spoke is provided. The spoke includes an aerodynamic shape with a leading side and a trailing side and, extending from the leading side to the trailing side, a first side and a second side, opposite the first side. The spoke also includes at least one flow guiding element arranged on at least the first side.
    Type: Grant
    Filed: January 25, 2008
    Date of Patent: March 26, 2013
    Assignee: Siemens Aktiengesellschaft
    Inventor: John David Maltson
  • AXIAL BOLTING ARRANGEMENT FOR MID TURBINE FRAME
    Publication number: 20130067930
    Abstract: A mid turbine frame of a gas turbine engine has a plurality of circumferentially spaced load transfer spokes extending radially between outer and inner cases. The load transfer spokes have a circumferentially enlarged inner end which is mounted to the inner case by a plurality of axially disposed fasteners extending through the inner case and spokes.
    Type: Application
    Filed: September 15, 2011
    Publication date: March 21, 2013
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventor: Vincent PARADIS
  • Continuous composite fan duct and thrust reverser
    Patent number: 8398017
    Abstract: A duct having a continuous C-shaped cross section slidably attached to a strut supporting an aircraft engine. The duct may comprise an inner wall, an outer wall, a first end wall, a second end wall, at least one slider, a thrust reverser, and an outer cowl panel of a thrust reverser. The inner wall may comprise a forward section and an aft section. The aft section may be integral with the first end wall, the second end wall, the outer wall, and the at least one slider. The forward section may comprise a right half and a left half which may be pivotally attached to the strut and may pivot to an open position when the rest of the fan duct is slid aftward away from the engine. The duct, excluding the forward section of the inner wall, may slide aftward on its at least one slider, providing engine access.
    Type: Grant
    Filed: February 4, 2009
    Date of Patent: March 19, 2013
    Assignee: Spirit AeroSystems, Inc.
    Inventor: John M. Welch
  • Annular gas turbine engine case and method of manufacturing
    Patent number: 8397383
    Abstract: The method is used for making an annular gas turbine engine case from a preform. The method comprises comprising flowforming at least one section of the preform, and then outwardly bending at least one portion of the perform.
    Type: Grant
    Filed: October 2, 2006
    Date of Patent: March 19, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Barry Barnett, Steven Hunt, Czeslaw Wojtyczka
  • Combustion chamber and gas turbine installation
    Patent number: 8393161
    Abstract: A combustion chamber having a burner and a burner insert surrounding the burner while leaving a gap open towards the combustion chamber interior is provided. The burner insert comprises a carrier and a burner insert wall located in front of the carrier towards the combustion chamber interior, wherein a flow passage connected to a cooling-fluid source is formed between the carrier and the burner insert wall. The flow passage opens out into the gap between the burner and the burner insert and is otherwise sealed off from the combustion chamber interior.
    Type: Grant
    Filed: September 21, 2006
    Date of Patent: March 12, 2013
    Assignee: Siemens Aktiengesellschaft
    Inventor: Uwe Gruschka
  • Fuel delivery system with reduced heat transfer to fuel manifold seal
    Patent number: 8393154
    Abstract: A gas turbine engine fuel supply assembly which includes a fuel manifold mounted to a casing surrounding a combustor of the engine, and a plurality of fuel nozzles mounted to the fuel manifold. A mating interface between the fuel nozzles and the fuel manifold has at least one sealing element, and at least one aperture defined in the fuel nozzle proximate to the mating interface. The aperture is a non fuel conveying passage, and reduces conductive heat transfer to the sealing element by preventing a direct conductive heat transfer path between a hot region of the fuel nozzle and the sealing element.
    Type: Grant
    Filed: February 12, 2009
    Date of Patent: March 12, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Victor Gandza
  • GAS DUCT FOR A GAS TURBINE AND GAS TURBINE HAVING SUCH A GAS DUCT
    Publication number: 20130055725
    Abstract: A gas duct for a gas turbine through which exhaust gases from the gas turbine are discharged to an outside includes a concentric inner casing and an outer casing disposed at a distance from the inner casing and concentrically encompassing the inner casing. A plurality of radial support struts interconnect the inner casing and the outer casing. Each of the support struts, the inner casing and the outer casing each have a heat-resistant lining disposed so as to provide protection against heat from the exhaust gases. The heat-resistant the linings of each of the support struts, the inner casing and the outer casing are divided in each case into a plurality of separate segments that are fastened to a support structure in an arrangement that provides an individual entirely or almost stress-free thermal expansion of each of the plurality of separate segments in an expansion plane.
    Type: Application
    Filed: September 4, 2012
    Publication date: March 7, 2013
    Applicant: ALSTOM TECHNOLOGY LTD
    Inventors: Marc Rauch, Tobias Steffen, Joachim Krautzig, Amin Busekros, Juergen Pacholleck
  • TURBOMACHINE LOAD MANAGEMENT ASSEMBLY
    Publication number: 20130042629
    Abstract: An example turbomachine load management assembly includes a support rod extending from a first rod end to a second rod end that is moveable radially relative to a fan duct, a bearing housing, or both, when the support rod is coupling the fan duct and the bearing housing.
    Type: Application
    Filed: August 17, 2011
    Publication date: February 21, 2013
    Inventors: David T. Feindel, Paul W. Palmer, Jonathan P. Burt, Raymond N. Frick
  • GAS TURBINE ENGINE INTERNAL COMPARTMENT STRUCTURE HAVING EGRESS FEATURE
    Publication number: 20130042628
    Abstract: A gas turbine engine includes a gas turbine engine internal compartment structure having an integral passageway. Wiring is routed through the integral passageway of the gas turbine engine internal compartment structure.
    Type: Application
    Filed: August 17, 2011
    Publication date: February 21, 2013
    Inventor: Russell B. Witlicki
  • GAS TURBINE ENGINE ACCESSORY MOUNT
    Publication number: 20130042630
    Abstract: A gas turbine engine accessory mount comprises a bracket fixedly attached to the engine's case, a link adapted for connection to the accessory and bracket and a fastener such as a pin disposed with a frangible fuse bushing, the pin and fuse bushing being received within aligned apertures in the link and bracket such that deflections and distortions of the engine case due to abnormal operating conditions of the engine such as a rotor imbalance due to separation of a blade therefrom, result in a shearing of the fuse busing thereby dissipating energy associated with the case deflections and distortions and isolating the fastener, link and accessory from the case deflections and distortions.
    Type: Application
    Filed: August 19, 2011
    Publication date: February 21, 2013
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: Marc J. Muldoon
  • Cooling air system for mid turbine frame
    Patent number: 8371127
    Abstract: A mid turbine frame is disposed between high and low pressure turbine assemblies. A cooling air system defined in the mid turbine frame of a gas turbine engine includes internal cavities for containing pressurized cooling air to cool the inter-turbine duct and the hollow struts, and discharges the used cooling air to further cool respective high and low pressure turbine assemblies.
    Type: Grant
    Filed: October 1, 2009
    Date of Patent: February 12, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Pierre-Yves Legare
  • MOVABLE STRUT COVER FOR EXHAUST DIFFUSER
    Publication number: 20130031913
    Abstract: A strut cover for use in a gas turbine engine having structure defining an annular flow path for receiving exhaust gas from a turbine section of the engine. The strut cover is located downstream from a last row of blades of the turbine section and extends radially through the flow path between inner and outer walls. The strut cover includes an upstream section and a downstream section. The upstream section defines a leading edge for the strut cover and is supported on a pivot axis for pivotal movement about the pivot axis. The downstream section defines a trailing edge for the strut cover and includes an upstream end positioned adjacent to a downstream end of the upstream section. The downstream section is stationary relative to the inner and outer walls to define a predetermined flow angle for directing exhaust gases flowing from the upstream section and passing through the diffuser.
    Type: Application
    Filed: August 2, 2011
    Publication date: February 7, 2013
    Inventor: David A. Little
  • Mid-turbine frame buffer system
    Patent number: 8366382
    Abstract: A mid-turbine frame buffer system for a gas turbine engine includes a mid-turbine frame that supports a shaft by a bearing. An air compartment and a bearing compartment are arranged radially inward of the mid-turbine frame. The bearing compartment is arranged within the air compartment and includes first and second contact seals arranged on either side of the bearing. The air compartment includes multiple air seals. A high pressure compressor is fluidly connected to the air compartment and is configured to provide high pressure air to the air compartment. A method of providing pressurized air to a buffer system includes sealing a bearing compartment with contact seals, surrounding the bearing compartment with an air compartment, and supplying high pressure air to the air compartment.
    Type: Grant
    Filed: January 31, 2012
    Date of Patent: February 5, 2013
    Assignee: United Technologies Corporation
    Inventors: Marc J. Muldoon, Gregory E. Reinhardt
  • Truss-shaped engine pylon and method of making same
    Patent number: 8353476
    Abstract: An aircraft engine pylon comprises a top wall, a bottom wall, a left side wall, and a right side wall. The left side wall includes a left truss structure along with a left upper ledge and a left lower ledge. The right side wall includes a right truss structure along with a right upper ledge and a right lower ledge. The top wall is joined with the left upper ledge and the right upper ledge and an upper truss structure is formed in the left upper ledge, the right upper ledge, and the top wall. The bottom wall is joined with the left lower ledge and the right lower ledge and a lower truss structure is formed in the left lower ledge, the right lower ledge, and the bottom wall.
    Type: Grant
    Filed: November 23, 2009
    Date of Patent: January 15, 2013
    Assignee: Spirit AeroSystems, Inc.
    Inventors: Gordon R. Crook, Randall R. West, George Larimore Huggins
  • Combustor assembly for use in a turbine engine and methods of fabricating same
    Patent number: 8353165
    Abstract: A combustor assembly that includes a casing that includes a plenum, a combustor liner positioned within the plenum and defining a combustion chamber there within, and a transition piece that includes a forward portion that is coupled to the combustion liner and an aft portion that extends from the forward portion. The aft portion includes a transition piece frame. The transition piece frame includes an upstream surface, a downstream surface, and a radially inner surface extending between the upstream and downstream surfaces. The radially inner surface includes a leading edge that extends between the radially inner surface and the upstream surface. A plurality of first cooling passages extend from the upstream surface to the downstream surface. Each of the first cooling passages is oriented obliquely with respect to the leading edge from the upstream surface towards the downstream surface.
    Type: Grant
    Filed: February 18, 2011
    Date of Patent: January 15, 2013
    Assignee: General Electric Company
    Inventors: Kevin Weston McMahan, Ronald James Chila
  • SUPPORT ASSEMBLY FOR TRANSITION DUCT IN TURBINE SYSTEM
    Publication number: 20130008177
    Abstract: A support assembly for a turbine system is disclosed. The support assembly includes a transition duct extending between a fuel nozzle and a turbine section. The transition duct has an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis. The support assembly further includes a plurality of protrusions extending from the transition duct. The plurality of protrusions are configured to allow movement of the transition duct about at least one axis.
    Type: Application
    Filed: July 5, 2011
    Publication date: January 10, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Jeffrey Scott LeBegue, Kevin Weston McMahan, Ronnie Ray Pentecost, James Scott Flanagan
  • ULTRA HIGH TEMPERATURE CIRCUIT COUPLING
    Publication number: 20130008179
    Abstract: An inductance-stable ultra high temperature circuit coupling transformer (50) used to transmit and receive alternating current power and/or data signals (29?, 33?). Primary (30?) and secondary (34?) windings are formed on nanostructured laminated (31?) primary and secondary steel cores (32?) having a Curie temperature exceeding an ultra high operating temperature. The operating range can extend from ambient to 250° C. or to in excess of 550° C. or up to 700° C. with a change in inductance of less than 10% in various embodiments.
    Type: Application
    Filed: July 6, 2011
    Publication date: January 10, 2013
    Inventors: David J. Mitchell, Cora Schillig, Rod Waits, Anand A. Kulkarni
  • GAS TURBINE SHROUD ARRANGEMENT
    Publication number: 20130008176
    Abstract: A system for supporting a shroud used in an engine has a shroud positioned radially outboard of a rotor, which shroud has a plurality of circumferentially spaced slots; a forward support ring for supporting the shroud; the forward support ring having a plurality of spaced apart first tabs on a first side for functioning as anti-rotation devices; the forward support ring having a plurality of spaced apart second tabs on a second side; and the second tabs engaging the slots in the shroud and circumferentially supporting the shroud.
    Type: Application
    Filed: July 5, 2011
    Publication date: January 10, 2013
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jun Shi, Kevin E. Green, Paul F. Croteau
  • SUPPORT ASSEMBLY FOR TRANSITION DUCT IN TURBINE SYSTEM
    Publication number: 20130008178
    Abstract: A support assembly for a turbine system is disclosed. The support assembly includes a transition duct extending between a fuel nozzle and a turbine section. The transition duct has an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis. The support assembly further includes an annular contact member extending from the transition duct. The contact member is configured to allow movement of the transition duct about at least one axis.
    Type: Application
    Filed: July 5, 2011
    Publication date: January 10, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Jeffrey Scott LeBegue, Kevin Weston McMahan, Ronnie Ray Pentecost, James Scott Flanagan
  • Fail safe extended torque box strut-to-wing mount
    Patent number: 8342444
    Abstract: An apparatus for mounting an aircraft engine to a wing includes a torque box strut for supporting the engine and a mounting system for attaching the torque box strut to the wing. The mounting system has an aft mounting system for attaching the torque box strut to the wing and that has at least one active aft link for attaching the torque box strut to the wing during normal aircraft operation, and at least one aft link catcher for attaching the torque box strut to the wing upon a failure of one of the at least one active aft link. The mounting system has a forward mounting system for attaching the torque box strut to the wing and that has at least one active forward link for attaching the torque box strut to the wing during normal aircraft operation, and at least one forward link catcher for attaching the torque box strut to the wing upon a failure of one of the at least one active forward link.
    Type: Grant
    Filed: December 16, 2008
    Date of Patent: January 1, 2013
    Assignee: The Boeing Company
    Inventors: Scott Hartshorn, Dean Leon Parham, Donald T. Powell
  • Forward sleeve retainer plate and method
    Patent number: 8327646
    Abstract: In a combustor section, wherein a forward sleeve is disposed to encircle a leading end of an impingement sleeve comprised of first and second impingement sleeve parts abutted along a longitudinal junction thereof, a retainer member disposed to overlie the longitudinal junction. The retainer member is welded to at least one of said forward sleeve and the impingement sleeve. The retainer member has first and second axial end edges disposed transverse to the longitudinal junction, and at least one of the axial end edges has a cutout defined therein and disposed to overlie the longitudinal junction.
    Type: Grant
    Filed: February 22, 2010
    Date of Patent: December 11, 2012
    Assignee: General Electric Company
    Inventors: Thomas Edward Johnson, James Thomas Brown
  • Combustor liner with integrated anti-rotation and removal feature
    Patent number: 8327648
    Abstract: A combustor liner for a gas turbine engine including first and second annular liner portions engaged to one another with an interference fit. The first liner portion includes at least one anti-rotation feature extending therefrom and engaging the second liner portion and having a threaded hole defined therethrough at least substantially perpendicularly to an adjacent radially extending surface of the second liner portion for threadingly receiving a pushing tool for pushing against that surface.
    Type: Grant
    Filed: December 9, 2008
    Date of Patent: December 11, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Stephen Phillips, Kenneth Parkman, Bhawan B. Patel, Pierrot Duchesne
  • MOUNT DEVICE FOR TRANSITION DUCT IN TURBINE SYSTEM
    Publication number: 20120304665
    Abstract: A mount device and mounting assembly for a turbine system are disclosed. The mounting assembly includes a transition duct extending between a fuel nozzle and a turbine section. The transition duct has an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The mounting assembly further includes a mount device connecting the transition duct to the turbine section. The mount device is configured to allow movement of the outlet about at least two axes.
    Type: Application
    Filed: June 3, 2011
    Publication date: December 6, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Jeffrey Scott LeBegue, Kevin Weston McMahan, Ronnie Ray Pentecost, James Scott Flanagan
  • SYSTEM FOR MOUNTING COMBUSTOR TRANSITION PIECE TO FRAME OF GAS TURBINE ENGINE
    Publication number: 20120304664
    Abstract: A system includes a combustor transition piece configured to mount between a combustor and a turbine of a gas turbine engine. The combustor transition piece includes a hollow body with an internal flow passage extending from an upstream end portion to a downstream end portion. The combustor transition piece also includes an aft frame coupled to the downstream end portion of the hollow body, an aft flange coupled to the aft frame, and a mounting lug removably coupled to the aft frame at a first joint. The mounting lug is configured to removably couple to a mounting bracket at a second joint.
    Type: Application
    Filed: June 2, 2011
    Publication date: December 6, 2012
    Applicant: General Electric Company
    Inventors: David William Cihlar, Patrick Benedict Melton, John Drake Vanselow
  • Transition duct assembly
    Patent number: 8322146
    Abstract: A transition duct assembly with a thermally free aft frame and mounting system for use in a gas turbine engine are disclosed. The aft frame is capable of adjusting to thermal gradients while the mounting system provides for at least transverse movement of the transition duct during engine assembly. The mounting system also provides a means for raising the natural frequency of the transition duct outside of the engine's dynamic excitation ranges.
    Type: Grant
    Filed: August 22, 2008
    Date of Patent: December 4, 2012
    Assignee: Alstom Technology Ltd
    Inventors: Hany Rizkalla, Stephen W. Jorgensen, Peter Stuttaford, Plazi Ricklin, David John Henriquez
  • THERMOCOUPLE WELL FOR A TURBOMACHINE
    Publication number: 20120297792
    Abstract: A turbomachine includes a nozzle. The nozzle includes an end portion and an airfoil portion. A diaphragm is mounted to the end portion of the nozzle in a wheel space portion of the turbomachine. The diaphragm includes an external surface and an internal surface. The diaphragm also includes at least one thermocouple well receiving portion formed in one of the external surface and the internal surface. A thermocouple well is mounted in the at least one thermocouple well receiving portion. The thermocouple well includes a first end exposed to the wheel space portion of the turbomachine and a second end exposed at the internal surface of the diaphragm.
    Type: Application
    Filed: May 27, 2011
    Publication date: November 29, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Daniel Jackson Dillard, Gregory Thomas Foster, George Martin Gilchrist, III
  • INTEGRATED CERAMIC MATRIX COMPOSITE ROTOR DISK GEOMETRY FOR A GAS TURBINE ENGINE
    Publication number: 20120297790
    Abstract: A CMC disk for a gas turbine engine includes a CMC hub defined about an axis and a multiple of CMC airfoils integrated with the CMC hub.
    Type: Application
    Filed: May 26, 2011
    Publication date: November 29, 2012
    Inventors: Ioannis Alvanos, Gabriel L. Suciu
  • CERAMIC MATRIX COMPOSITE TURBINE EXHAUST CASE FOR A GAS TURBINE ENGINE
    Publication number: 20120297791
    Abstract: A turbine exhaust case for a gas turbine engine includes a multiple of CMC turbine exhaust case struts between a CMC core nacelle aft portion and a CMC tail cone.
    Type: Application
    Filed: May 26, 2011
    Publication date: November 29, 2012
    Inventors: Gabriel L. Suciu, Ioannis Alvanos, Brian D. Merry
  • THERMALLY COMPLIANT SUPPORT FOR A COMBUSTION SYSTEM
    Publication number: 20120291452
    Abstract: A support structure in a gas turbine combustor end cap (24) including a bracket (60) with a first leg (61) and a second leg (62) forming a generally trapezoidal geometry. Each leg has a first end (61A, 62A) attached to an inner concentric ring (46), and a second end (61B, 62B) attached to a crossbar (65). The crossbar is attached to an outer concentric ring (48). A circular array of such brackets interconnects the two concentric rings (46, 48). Each leg has at least one curved middle portion (63, 64), such as an arcuate or sinusoidal curve at a midpoint on the length of each leg. This shape provides flexibility in a radial direction that accommodates differential thermal expansion of the concentric rings while providing a rigid connection in an axial direction.
    Type: Application
    Filed: September 23, 2011
    Publication date: November 22, 2012
    Inventors: Frank Moehrle, John Pula, Jeremy Lefler, Martin Konen
  • AUXILIARY POWER UNIT MOUNTING FEATURE
    Publication number: 20120291450
    Abstract: An auxiliary power unit assembly includes an auxiliary power unit with an auxiliary power unit exhaust duct, a bell mouth, and one or more bell mouth struts. The auxiliary power unit exhaust duct extends from the auxiliary power unit and has an aft end portion that is received within the bell mouth. The bell mouth struts extend from an inner surface of the bell mouth and extend generally radially toward the auxiliary power unit exhaust duct.
    Type: Application
    Filed: August 2, 2011
    Publication date: November 22, 2012
    Applicant: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Brian C. DeDe, Jack V. Vitale, Markissa Catherine Hiekel
  • STRUCTURAL FRAME FOR GAS TURBINE COMBUSTION CAP ASSEMBLY
    Publication number: 20120291451
    Abstract: An intermediate support frame (68) that spans an inner diameter of a support ring (48) of a gas turbine combustor cap assembly (24) at a position intermediate the length of the support ring. The intermediate support frame may have a central encirclement (72) that receives a central fuel pre-mix tube (44) of the combustor cap assembly, and may further have a circular array of outer stabilization rings (70) that each receive a respective outer pre-mix tube (42). The central pre-mix tube may be affixed to the central encirclement (72), for example by welding. The outer pre-mix tubes may be slidably engaged in the outer stabilization rings (70), providing lateral stability while allowing differential thermal expansion.
    Type: Application
    Filed: September 21, 2011
    Publication date: November 22, 2012
    Inventors: Frank Moehrle, Luis Estrada, Jeremy Lefler, Martin Konen
  • Turbofan mounting system
    Patent number: 8313293
    Abstract: A gas turbine engine has a rear mounting assembly incorporating a mounting apparatus attached to a bypass duct wall with a link device for transferring core portion related inertia-induced loads, from an MTF of the core portion in a short circuit across an annular bypass air passage to the bypass duct wall.
    Type: Grant
    Filed: May 15, 2009
    Date of Patent: November 20, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Jeffrey Bernard Heyerman, Bryan W. Olver, Bruce Fielding, Carl Smythe
  • Gas turbine engine systems involving I-beam struts
    Patent number: 8312726
    Abstract: Gas turbine engine systems involving I-beam struts are provided. In this regard, a representative strut assembly for a gas turbine engine includes a first I-beam strut having first and second flanges spaced from each other and interconnected by a web, the first strut exhibiting a twist along a length of the web.
    Type: Grant
    Filed: December 21, 2007
    Date of Patent: November 20, 2012
    Assignee: United Technologies Corp.
    Inventors: Joey Wong, Peter Chen, Dana P. Stewart, David N. Waxman, Michael A. Mike
  • Turbine wash port for a gas turbine engine
    Patent number: 8303243
    Abstract: An access conduit for access to the interior of a combustor for the washing of the turbine components of a gas turbine engine. The access conduit is secured between a gas generator case and a combustion chamber liner of the combustor. The access conduit has an open outer end accessible from an outer face of the gas generator case and an open inner end exiting in a combustion chamber through the liner. The access conduit has one or more openings disposed in a combustor gap between the gas generator case and the liner of the combustor. A plug is removably secured in the open outer end and extends into the access conduit to obstruct the one or more openings.
    Type: Grant
    Filed: January 15, 2009
    Date of Patent: November 6, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Jason Fish, Kian McCaldon
  • HEAD PART OF AN ANNULAR COMBUSTION CHAMBER
    Publication number: 20120272662
    Abstract: A head part (100) of an annular combustion chamber for a gas turbine, the head part comprising: an end wall (110) with a first opening (112) for accommodating a burner; a heat shield (120) covering a back side of the end wall which faces towards the combustion chamber, the heat shield comprising a second opening (124) for accommodating the burner; and a burner collar (130) adapted to fit within the second opening and receive the burner; wherein the head part of the annular combustion chamber is configured such that in an installed configuration the burner collar is fastened to the heat shield with one or more first fasteners (142) to form a sub assembly (140) and the heat shield of the sub assembly is fastened to the end wall with one or more second fasteners (144).
    Type: Application
    Filed: April 19, 2012
    Publication date: November 1, 2012
    Applicant: ROLLS-ROYCE PLC
    Inventor: Richard G. MILBURN
  • METHOD AND ASSEMBLY FOR RETROFITTING A GAS TURBINE COMBUSTOR END COVER
    Publication number: 20120272660
    Abstract: A method for retrofitting an end cover of a turbine engine combustor. The method includes inserting a first insert into a opening formed in the end cover so a circular land on the insert centers the insert in the opening and an annular face on the insert engages a face of the opening. The first insert includes a cylindrical tip section opposite the base having a diameter smaller than a diameter of the opening. The base of the first insert is joined to the opening. The method includes inserting a second insert into the opening so an outer diameter of the second insert is positioned inside the diameter of the opening. The second insert has an inner land adapted to engage the outer diameter of the first insert to position the second insert relative to the first insert and the opening. The second insert is joined to the end cover.
    Type: Application
    Filed: April 29, 2011
    Publication date: November 1, 2012
    Applicant: PROENERGY SERVICES, LLC
    Inventor: Christopher Garrett
  • HEAD PART OF AN ANNULAR COMBUSTION CHAMBER
    Publication number: 20120272661
    Abstract: A head part of an annular combustion chamber for a gas turbine, the head part comprising: an end wall with a passage opening for accommodating a burner, the end wall comprising a back side which faces towards the combustion chamber; a burner collar adapted to fit within the passage opening and receive the burner, the burner collar comprising a protruding portion radially protruding from an outer surface of the burner collar; and a ring member for receiving the protruding portion of the burner collar; wherein the head part of the annular combustion chamber is configured such that in an installed configuration a radially outer portion of the ring member engages with the end wall and a radially inner portion of the ring member receives the protruding portion of the burner collar.
    Type: Application
    Filed: April 19, 2012
    Publication date: November 1, 2012
    Applicant: ROLLS-ROYCE PLC
    Inventor: Richard G. MILBURN
  • Gas turbine and method of forming combustor insertion hole of gas turbine
    Patent number: 8297037
    Abstract: A gas turbine includes a combustor, a combustor casing formed in a cylindrical shape to house the combustor therein, and a combustor insertion hole, which is a hole formed on a side periphery of the combustor casing, where a size thereof in a direction orthogonal to a circumferential direction of the combustor casing is formed larger than that in the circumferential direction of the combustor casing, and when the combustor inserted into the hole, a member moved together with the combustor, and the hole are viewed from a moving direction of the combustor, the hole includes an entire external form of the combustor and the member moved together with the combustor.
    Type: Grant
    Filed: December 1, 2008
    Date of Patent: October 30, 2012
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Sosuke Nakamura, Kenichi Arase, Norihiko Motoyama
  • Fuel injector bearing plate assembly and swirler assembly
    Patent number: 8291706
    Abstract: A bearing plate assembly for a turbine engine fuel injector includes a bearing plate 30, with an opening 80 bordered by a race 82. A swivel ball 90 nests inside the race and is rotatable relative thereto. A lock, which may be a tip bushing 108 resists disengagement of the swivel ball from the race. A fuel injector nozzle 38 extends through an opening 98 in the swivel ball. During engine operation, the ball can swivel inside the race to accommodate rotational movement of the nozzle about lateral and radial axes.
    Type: Grant
    Filed: June 11, 2009
    Date of Patent: October 23, 2012
    Assignee: United Technologies Corporation
    Inventors: Keith M. Tanner, Philip J. Kirsopp
  • Fastener assembly for connecting rocket engine nozzles
    Patent number: 8281603
    Abstract: A sliding connection between components of dissimilar materials includes a first mating surface formed on a first component and a second mating surface formed on a second component and configured to mate with the first mating surface. The first component is connected to the second component at the first and the second mating surfaces by a fastener including a shank, a sleeve received by the shank, and a resilient member received by the shank and contained by the sleeve. The resilient member is configured to press the first mating surface and the second mating surface against one another and to permit the first mating surface to slide against the second mating surface.
    Type: Grant
    Filed: August 11, 2008
    Date of Patent: October 9, 2012
    Assignee: United Technologies Corporation
    Inventor: Bradley C. Johnson
  • Circumferentially self expanding combustor support for a turbine engine
    Patent number: 8281602
    Abstract: A bullhorn or support for a turbine combustor is provided. The support maintains proper positioning of the transition element relative to the combustor while also allowing for certain movements of the support to alleviate mechanical stresses during turbine operation. The support is constructed from at least two pieces having an interlocking and releasable connection.
    Type: Grant
    Filed: September 11, 2009
    Date of Patent: October 9, 2012
    Assignee: General Electric Company
    Inventor: Richard Martin DiCintio
  • Gas-turbine combustion chamber with ceramic flame tube
    Patent number: 8281598
    Abstract: A gas turbine combustion chamber includes an essentially cylindrical flame tube 2, which is made of a ceramic material and circumferentially divided into several circumferential elements 10, 11, 12.
    Type: Grant
    Filed: February 19, 2009
    Date of Patent: October 9, 2012
    Assignee: Rolls-Royce Deutchland Ltd & Co KG
    Inventors: Miklos Gerendas, Sermed Sadig
  • Gas turbine engine fuel conveying member
    Patent number: 8276387
    Abstract: A fuel conveying member of a gas turbine engine is described and includes a fuel manifold defining an annular fuel flow passage through a body of the fuel manifold. A plurality of fuel nozzles extend from the manifold in fluid flow communication with the annular fuel flow passage. The fuel manifold includes integral attachment lugs thereon for mounting the fuel manifold within the gas turbine engine. The attachment lugs are adapted to receive pins therein and provide a mounting mechanism which allows for thermal expansion of the fuel manifold relative to a surrounding support structure to which the fuel manifold is mounted via the attachment lugs.
    Type: Grant
    Filed: February 4, 2011
    Date of Patent: October 2, 2012
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Lev Alexander Prociw, Harris Shafique, Jason Fish, Bhawan B. Patel
  • COMBUSTION CHAMBER HEAD WITH HOLDING MEANS FOR SEALS ON BURNERS IN GAS TURBINES
    Publication number: 20120240595
    Abstract: A combustion chamber head of a gas turbine has a base plate 113 provided with a centric recess 121 in which at least one burner 106 is arranged, with the base plate 113 being connected to walls of the combustion chamber 108 and to a burner seal 116 sealing the burner 106 towards the rim of the recess 121. The burner seal 116 is arranged upstream of the base plate 113 and can be brought into contact with a collar 118 provided on the base plate 113 and forming the rim of the centric recess 121. A holding element 117 of the burner seal 116 is formed as a ring and arranged upstream of the burner seal 116 and engages with at least one projection 114 of the base plate 113 in a tension-free state.
    Type: Application
    Filed: March 23, 2012
    Publication date: September 27, 2012
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Miklos GERENDAS
  • External fan duct casing in a turbomachine
    Patent number: 8272203
    Abstract: Twin-flow turbo-jet engine, comprising a cylindrical casing externally defining an annular flow space for a secondary flow, wherein the cylindrical casing is formed from a lattice framework and from removable cowling panels fixed to the framework, said framework comprising an upstream annular flange for fixing to an intermediate housing, a downstream annular flange for connecting to an exhaust housing and rigid beams parallel or inclined relative to the axis of the turbo-jet engine, connecting the two flanges to one another.
    Type: Grant
    Filed: July 22, 2008
    Date of Patent: September 25, 2012
    Assignee: Snecma
    Inventors: Jacky Raphael Michel Derenes, Delphine Edith Dijoud, Sebastien Regard
  • Apparatus and methods for fuel nozzle frequency adjustment
    Patent number: 8272224
    Abstract: A combustion liner cap assembly includes a cylindrical outer sleeve. The cylindrical outer sleeve includes a center fuel nozzle opening and a plurality of outer fuel nozzle openings spaced around the center fuel nozzle. A mounting flange assembly concentrically surrounds the cylindrical outer sleeve. A plurality of struts on an outer surface of the cylindrical outer sleeve support the mounting flange assembly. A plurality of flanges are on the outer surface of the cylindrical outer sleeve; and a plurality of support rods having first ends are adjustably supported by respective flanges. A combustor for a gas turbine includes a combustion liner cap assembly, a plurality of outer fuel nozzles supported in the plurality of outer fuel nozzle openings, and a center fuel nozzle supported in the center fuel nozzle opening. Second ends of the plurality of support rods adjustably contact the center fuel nozzle.
    Type: Grant
    Filed: November 2, 2009
    Date of Patent: September 25, 2012
    Assignee: General Electric Company
    Inventors: David Cihlar, Christopher Paul Keener
  • AFT FRAME AND METHOD FOR COOLING AFT FRAME
    Publication number: 20120234018
    Abstract: An aft frame and a method for cooling an aft frame are disclosed. In one embodiment, an aft frame for a transition piece in a combustor is disclosed. The combustor includes the transition piece and an impingement sleeve at least partially defining a flow path therebetween. The aft frame includes a body and a generally radially extending cooling passage defined in the body, the cooling passage comprising a first end configured to accept a coolant. The aft frame further includes an exhaust passage defined in the body, the exhaust passage including a first end in communication with the cooling passage and a second end configured for communication with the flow path for flowing the coolant therethrough.
    Type: Application
    Filed: March 16, 2011
    Publication date: September 20, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: David William Cihlar, Patrick Benedict Melton, David Leach, Kevin Weston McMahan