Assembling Fluid Flow Directing Devices, E.g., Stators, Diaphragms, Nozzles Patents (Class 29/889.22)
  • Patent number: 10876417
    Abstract: An airfoil assembly may include a shroud and an airfoil. The shroud may include a first attachment arm, a second attachment arm, and a shroud rail extending from a first surface of the shroud. A first channel may be defined between the first attachment arm, the first surface, and the shroud rail and a second channel may be defined between the second attachment arm, the first surface, and the shroud rail. The airfoil may extend from a second surface of the shroud opposite the first surface. In various embodiments, a height of the shroud rail, as measured from the first surface of the shroud, is non-uniform.
    Type: Grant
    Filed: August 17, 2017
    Date of Patent: December 29, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: William R. Edwards, Charles H. Warner
  • Patent number: 10823112
    Abstract: A method for manufacturing a cascade for a thrust reverser for a jet engine includes forming a strip assembly. The strip assembly includes a strong back member which includes a length. The strip assembly includes a plurality of first vane members which extend from a first side of the strong back member in a first direction nonparallel relative to the length of strong back member wherein the plurality of the first vane members are spaced apart from one another along the length of the strong back member.
    Type: Grant
    Filed: May 25, 2017
    Date of Patent: November 3, 2020
    Assignee: THE BOEING COMPANY
    Inventors: Naimishkumar Harpal, Chen Chuck, Zachariah VanDeMark, Tunde A. Olaniyan, Minkoo Han
  • Patent number: 10697471
    Abstract: An annular array of turning vanes 200 is provided in a duct 100 of a gas turbine engine 10. The annular array of turning vanes 200 comprises aerodynamic vanes 220 and strut-vanes 240. The strut-vanes 240 have greater chord length and extend further axially downstream than the aerodynamic vanes 220. The leading edge of the strut-vanes 240 is upstream of the trailing edge of the aerodynamic vanes 220. The strut-vanes provide flow turning. The arrangement allows the duct 100 to be axially short.
    Type: Grant
    Filed: February 28, 2018
    Date of Patent: June 30, 2020
    Assignee: Rolls-Royce PLC
    Inventors: Richard Northall, Anthony J. Rae, Michael S. Krautheim, Alastair D. Walker, Jonathan F. Carrotte, Ian Mariah
  • Patent number: 10697302
    Abstract: An aerofoil member that extends between radially inner and radially outer endwalls which define a gas annulus of the compressor. Aerofoil member has a leading edge, a trailing edge, a pressure surface and a suction surface such that successive cross-sections through the aerofoil member transverse to the radial direction provide respective aerofoil sections. The external shape of the aerofoil member is defined by the stacking of the aerofoil sections on a stacking axis which passes through a reference point common to each aerofoil section. The aerofoil member has lean produced by the projection of the stacking axis onto a plane normal to the engine axis intersecting a first one of the endwalls at an angle of from 5° to 25° to the circumferential direction direction such that the pressure surface faces the first endwall.
    Type: Grant
    Filed: May 14, 2018
    Date of Patent: June 30, 2020
    Assignee: Rolls-Royce plc
    Inventors: James V. Taylor, Robert J. Miller
  • Patent number: 10690349
    Abstract: A fuel injector for a gas turbine combustor includes side wall fuel injection bodies extending between opposite end walls. Each side wall fuel injection body defines a fuel plenum and includes an outer surface defining fuel injection ports in communication with the fuel plenum. One or more fuel injection bodies extending between the end walls are positioned between the side wall fuel injection bodies. Each fuel injection body defines a fuel plenum and includes an outer surface defining fuel injection ports in fluid communication with the fuel plenum. A conduit fitting coupled to the frame is fluidly connected to the respective fuel plenums. The fuel injection ports fluidly communicate with air flow paths defined between the fuel injection bodies and the side wall fuel injection bodies. A combustor for a gas turbine includes a liner and an axial fuel staging system with the present fuel injector.
    Type: Grant
    Filed: September 1, 2017
    Date of Patent: June 23, 2020
    Assignee: General Electric Company
    Inventors: Jayaprakash Natarajan, Seth Reynolds Hoffman, Ronnie Ray Pentecost, Wei Zhao
  • Patent number: 10646970
    Abstract: A boost control device for a turbocharger, assembled at room temperature, may not be geometrically optimal at turbocharger operating temperature. The geometric deviation in the boost control device introduced by the heating of the turbocharger to operating temperature, or during welding of the boost control device, is corrected by producing a first turbocharger at room temperature, determining the geometry of the deviation at operating temperature, producing a distance element that will introduce an equal and opposite deviation, introducing the equal and opposite deviation via the distance element in second and subsequent turbochargers, whereby thermal deviation and corrective deviation offset so that the turbocharger is geometrically accurate at operating temperature.
    Type: Grant
    Filed: February 25, 2018
    Date of Patent: May 12, 2020
    Assignee: BorgWarner Inc.
    Inventors: Matthias Ruh, Michael Stilgenbauer
  • Patent number: 10605351
    Abstract: A turbo fan engine includes a housing that supports a compressor section. At least one compressor hub is within the compressor section. A compressor shaft is arranged in the compressor section. An epicyclic gear train is coupled to the compressor shaft. At least one compressor hub and the compressor shaft are coupled at a common attachment point. The epicyclic gear train includes a carrier. A sun gear and intermediate gears are arranged about and intermeshing with the sun gear. The intermediate gears are supported by the carrier. A baffle is supported relative to the carrier and includes a lubrication passage near at least one of the sun gear and intermediate gears for directing a lubricant on at least one of the sun gear and the intermediate gears.
    Type: Grant
    Filed: November 9, 2017
    Date of Patent: March 31, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: William P. Sheridan, Michael E. McCune
  • Patent number: 10598036
    Abstract: An assembly for a turbine engine includes a case, a guide vane arrangement and a flexible seal ring. The case extends circumferentially around an axis, and includes a first seal land. The guide vane arrangement is located radially within the case, and includes a second seal land. The seal ring at least partially seals a gap between the first seal land and the second seal land. The seal ring includes a first leg and a second leg that is connected to the first leg at a corner of the seal ring. The first leg is axially engaged with the first seal land. The second leg is axially engaged with the second seal land.
    Type: Grant
    Filed: March 12, 2014
    Date of Patent: March 24, 2020
    Assignee: United Technologies Corporation
    Inventors: Jorge I. Farah, Andrew D. Burdick
  • Patent number: 10502233
    Abstract: A system for an inlet guide vane shroud and baffle assembly includes a shroud. The shroud includes a first end configured to couple to an annular support member of the gas turbine engine, and a second end. The shroud also includes a distal end including an axially aft extending lip, and a seal assembly configured to form a seal with an annular set of rotating teeth on a rotor of the gas turbine engine. The shroud further includes an arcuate shroud body extending between the distal end and the second end. The shroud and baffle assembly also includes a baffle coupled to an aft side of the shroud. The baffle includes a radially outward end coupled to the aft side, a radially inward end coupled to the axially aft extending lip, and an arcuate baffle body extending there between. Both the shroud and the baffle extend circumferentially about a central axis.
    Type: Grant
    Filed: October 28, 2016
    Date of Patent: December 10, 2019
    Assignee: General Electric Company
    Inventors: Marcin Jacek Lobocki, Wiktor Karol Wardecki, Joseph Charles Kulesa, Maciej Staszewski
  • Patent number: 10287906
    Abstract: A gas turbine engine includes a blade track, a support assembly, and a seal system. The blade track is arranged around a central axis of the gas turbine engine to direct gasses through the gas turbine engine. The support assembly is arranged around the blade track to support the blade track relative to the central axis. The seal system is configured to block fluid communication between pressurized cavities formed in the support assembly.
    Type: Grant
    Filed: May 24, 2016
    Date of Patent: May 14, 2019
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Edward C. Rice, Daniel K. Vetters
  • Patent number: 10253646
    Abstract: An assembly for operating a device, such as a variable vane, has an arm, a stem to which the arm is connected, the stem having a slot, and a member having a tab which fits into the slot.
    Type: Grant
    Filed: June 4, 2014
    Date of Patent: April 9, 2019
    Assignee: United Technologies Corporation
    Inventors: Bernard W. Pudvah, Eugene C Gasmen, Christopher St. Mary, Stanley Wiecko
  • Patent number: 10247039
    Abstract: The invention relates to an assembly which includes: two rotationally symmetrical components (10, 20) for supporting the blades of a turbine engine, arranged one inside the other concentrically about a turbine engine axis, and a system (30) for locking the components (10, 20) such as to prevent the relative translation of same in the axial and radial directions relative to said axis, the system including a slotted ring (40) comprising a U-shaped cross-section suitable for receiving one end of the components (10, 20), the assembly being characterized in that the ring (40) and one of the components (10, 20) are shaped such as to allow the ring to be interlocked on the component, and in that the locking system (30) also includes a member for stopping the rotation of the ring relative to the component with which the latter is interlocked. The invention further relates to a method for assembling such an assembly.
    Type: Grant
    Filed: August 11, 2014
    Date of Patent: April 2, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Patrice Jean-Marie Rosset, Coralie Guerard, Helene Condat, Sebatien Prestel
  • Patent number: 10047958
    Abstract: A combustor wall is provided for a turbine engine and includes a combustor shell and a heat shield. The heat shield is attached to the shell with first and second cavities extending between the shell and the heat shield. The first cavity fluidly couples apertures defined in the shell with the second cavity. The second cavity fluidly couples the first cavity with apertures defined in the heat shield. The shell and the heat shield converge toward one another about the second cavity.
    Type: Grant
    Filed: October 6, 2014
    Date of Patent: August 14, 2018
    Assignee: United Technologies Corporation
    Inventors: Nurhak Erbas-Sen, Frank J. Cunha
  • Patent number: 9918394
    Abstract: A robot system includes a robot and a robot control apparatus. The robot control apparatus is connected to the robot for controlling the robot and includes a casing and a display unit movable with respect to the casing and displaying information. The casing has a plurality of attachment parts to which the display unit is attached. The plurality of attachment parts are provided on first and second surfaces of the casing, and the first surface is not parallel to the second surface.
    Type: Grant
    Filed: December 8, 2015
    Date of Patent: March 13, 2018
    Assignee: Seiko Epson Corporation
    Inventors: Sho Nakano, Ryosuke Teranaka
  • Patent number: 9874106
    Abstract: A number of variations may include a product comprising: a vane lever comprising a first end, a second end, a top surface, and a bottom surface; an opening which extends through the second end and which is defined by an inner surface, and wherein a perimeter of the inner surface comprises a plurality of vertical flutes which extend a length of the inner surface and which are constructed and arranged to displace a material of a vane shaft.
    Type: Grant
    Filed: October 21, 2015
    Date of Patent: January 23, 2018
    Assignee: BorgWarner Inc.
    Inventors: Matthew King, Elias Morgan, Greg Williams
  • Patent number: 9840923
    Abstract: A guide vane arrangement of a gas turbine and a method of manufacturing a guide vane arrangement of a gas turbine are provided herein. The guide vane arrangement includes a first guide vane device including a first radially inner platform and a first number of first airfoils, and a second guide vane device including a second radially inner platform and a second number of second airfoils. The first guide vane device and the second guide vane device are arranged along a circumferential direction of the turbine, wherein the first number of the first airfoils differs to the second number of the second airfoils. The first guide vane device is designed with a higher heat resistance than the second guide vane device.
    Type: Grant
    Filed: August 22, 2013
    Date of Patent: December 12, 2017
    Assignee: Siemens Aktiengesellschaft
    Inventors: Stephen Batt, Richard Bluck, David Butler
  • Patent number: 9840928
    Abstract: An axial flow turbine diaphragm is constructed without welding or other metal fusion or melting techniques. Static blade units are attached to inner and outer diaphragm rings by radially inner platform portions that engage the radially inner ring, and radially outer platform portions that engage the radially outer ring, the inner platform portions being elongate in the circumferential direction of the turbine diaphragm and the outer platform portions being elongate in a direction compatible with the stagger angle of the aerofoils. The outer circumference of the radially inner ring has a blade unit retaining feature of complementary shape and orientation to the inner platform portions of the static blade units, and the inner circumference of the radially outer ring is provided with a plurality of blade unit retaining features of complementary shape and orientation to corresponding outer platform portions of the static blade units.
    Type: Grant
    Filed: April 16, 2013
    Date of Patent: December 12, 2017
    Assignee: General Electric Technology GmbH
    Inventors: Angus Robert Brummitt-Brown, Kanu Mistry, Adrian Clifford Lord
  • Patent number: 9816387
    Abstract: An airfoil fairing shell for a gas turbine engine includes an airfoil section between an outer vane endwall and an inner vane endwall, at least one of the outer vane endwall and the inner vane endwall including a radial attachment face, a suction side tangential attachment face, a pressure side tangential attachment face, and an axial attachment face.
    Type: Grant
    Filed: September 1, 2015
    Date of Patent: November 14, 2017
    Assignee: United Technologies Corporation
    Inventors: Jesse M Carr, Bryan P Dube
  • Patent number: 9784119
    Abstract: It is provided with: a variable nozzle mechanism section 23; an opening degree regulating member 43 for regulating an angle of a nozzle vane 19a by bringing an outer peripheral surface 41 of an inner cylinder of a bearing housing 13 to which a nozzle mount is affixed and an inner peripheral surface of a lever plate 33 into contact; and a discharge recess 47 for discharging soot which accumulates in the gap between an inner peripheral end portion of the lever plate 33, the nozzle mount 21, and the bearing housing 13 to the inner peripheral end portion of the lever plate 33.
    Type: Grant
    Filed: September 7, 2012
    Date of Patent: October 10, 2017
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Naoto Tashiro, Yasuaki Jinnai, Hiroyuki Arimizu
  • Patent number: 9739156
    Abstract: A turbine or compressor stage of a gas turbine, the rotor blade having a radially outer shroud (1) which has a sealing fin array having a first sealing fin (3.1) and a second sealing fin (3.2) which is adjacent to the first sealing fin and connected thereto by a first groove base (10) having a circumferential region (13) of maximum radial height, which is located at a first circumferential position is provided. The sealing fin array has a third sealing fin (3.3) adjacent to the second sealing fin and opposite to the first sealing fin, the third sealing fin being connected to the second sealing fin by a second groove base (20) having a circumferential region (23) of maximum radial height, which is located at a second circumferential position different from the first circumferential position.
    Type: Grant
    Filed: November 21, 2014
    Date of Patent: August 22, 2017
    Assignee: MTU Aero Engines GmbH
    Inventors: Alexander Boeck, Sven Schmid
  • Patent number: 9702264
    Abstract: Three or more attachment pins are arranged on a right lateral surface of a nozzle ring at intervals. All the attachment pins are placed outside support holes in the nozzle ring in radial directions of the nozzle ring. A guide ring is provided across right lateral surfaces of the attachment pins. A first side guide member to support a right lateral surface of a drive ring in away that allows the right lateral surface to be in sliding contact therewith is provided to the right of the guide ring. A second side guide member to support a left lateral surface of the drive ring in a way that allows the left lateral surface to be in sliding contact therewith is provided to the left of the guide ring.
    Type: Grant
    Filed: April 25, 2014
    Date of Patent: July 11, 2017
    Assignee: IHI Corporation
    Inventors: Takafumi Ueda, Akira Iwakami, Naoki Tokue, Masaru Nishioka
  • Patent number: 9664064
    Abstract: An exhaust-gas turbocharger (1) having a turbine (2) which is provided with a variable turbine geometry (18) and/or a wastegate; and having an actuator (11) which is connected to the variable turbine geometry (18) and/or the wastegate via a coupling rod (14). The coupling rod (14) is connected at its end regions (21, 22) at one side to a pin of the actuator (11) by means of a lock washer (25) and at the other side to a pin (33) of an adjusting shaft (5) of the variable turbine geometry (18) and/or of the wastegate by means of a lock washer (26). The lock washers (25, 26) are integrated in the coupling rod (14).
    Type: Grant
    Filed: July 24, 2012
    Date of Patent: May 30, 2017
    Assignee: BorgWarner Inc.
    Inventors: Michael Stilgenbauer, Nico Kanoffsky
  • Patent number: 9546571
    Abstract: A turbine engine includes a vane and a case with a flange ring. The flange ring defines a channel that extends axially into a side of the flange ring to a channel end surface. The vane has a mounting lug that projects into the channel. The mounting lug includes a lug end surface that extends radially between substantially parallel lug side surfaces, where the lug end surface is engaged with the channel end surface.
    Type: Grant
    Filed: August 22, 2012
    Date of Patent: January 17, 2017
    Assignee: United Technologies Corporation
    Inventor: Mark E. Simonds
  • Patent number: 9506365
    Abstract: Embodiments of a gas turbine engine component having sealed stress relief slots are provided, as are embodiments of a gas turbine engine containing such a component and embodiments of a method for fabricating such a component. In one embodiment, the gas turbine engine includes a core gas flow path, a secondary cooling flow path, and a turbine nozzle or other gas turbine engine component. The component includes, in turn, a component body through which the core gas flow path extends, a radially-extending wall projecting from the component body and into the secondary cooling flow path, and one or more stress relief slots formed in the radially-extending wall. The stress relief slots are filled with a high temperature sealing material, which impedes leakage between the second cooling and core gas flow paths and which fractures to alleviate thermomechanical stress within the radially-extending wall during operation of the gas turbine engine.
    Type: Grant
    Filed: April 21, 2014
    Date of Patent: November 29, 2016
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Jason Smoke, Bradley Reed Tucker, Ardeshir Riahi, Ed Zurmehly, Alexander MirzaMoghadam
  • Patent number: 9347327
    Abstract: A system and method for repairing a turbine. The method includes applying a coating on an outer surface of a tenon that extends from a stator vane. The tenon may be inserted at least partially into an opening defined by an inner shroud segment of the turbine. A bushing may be inserted at least partially into the opening in the inner shroud segment of the turbine such that the tenon becomes at least partially disposed within an opening defined by the bushing. A bolt may be inserted through the opening in the bushing and at least partially into an opening defined by the tenon. The bolt may be threadably engaged with the tenon.
    Type: Grant
    Filed: May 21, 2013
    Date of Patent: May 24, 2016
    Assignee: Dresser-Rand Company
    Inventors: Justin C. Armstrong, Graham D. Sherlock, Greg T. Snyder, David L. Bollinger, Paul V. Sickles, David L. Sanchez, Dillon R. Jourde
  • Patent number: 9279171
    Abstract: Processes for the production of nickel-titanium mill products are disclosed. A nickel-titanium alloy workpiece is cold worked at a temperature less than 500° C. The cold worked nickel-titanium alloy workpiece is hot isostatic pressed (HIP'ed).
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: March 8, 2016
    Assignee: ATI PROPERTIES, INC.
    Inventors: Brian Van Doren, Scott Schlegel, Joseph Wissman
  • Patent number: 9255586
    Abstract: Provided is a diffuser block used to form a diffuser with a plurality of the diffuser blocks, the diffuser block including: a body having a tube shape including an inner space provided inside the body, an inlet through which a fluid flows into the inner space and an outlet through which the fluid flows out of the inner space; and a first vane portion which protrudes toward the inner space from one side of the body.
    Type: Grant
    Filed: November 2, 2012
    Date of Patent: February 9, 2016
    Assignee: Hanwha Techwin Co., Ltd.
    Inventor: Jin-Soo Lee
  • Patent number: 9198332
    Abstract: A cooling type switching element module includes an outer conductor pipe, an inner conductor pipe that transmits electric power in conjunction with the outer conductor pipe, and first and second switching elements. The first switching elements are provided on outer surfaces of the outer conductor pipe, and the second switching elements are provided on outer surfaces of a projecting portion of the inner conductor pipe. A coolant flows within the inner conductor pipe, and outside the outer conductor pipe. The first and second switching elements are cooled from both sides by the coolant flowing within the inner conductor pipe, and by the coolant flowing outside the outer conductor pipe. By employing the above-described structure, it is possible to provide a switching element module having a cooling function, in which improved cooling performance, improved electrical performance, and downsizing are achieved.
    Type: Grant
    Filed: December 31, 2013
    Date of Patent: November 24, 2015
    Assignee: TOYOTA JIDOSHA KABUSHIKI KAISHA
    Inventors: Hiroshi Osada, Masanori Usui, Takahide Sugiyama, Tomoyuki Shoji, Satoshi Hirose, Makoto Imai, Norimune Orimoto
  • Patent number: 9103229
    Abstract: An arrangement is provided for controlling a variable position of vanes at a turbine in a flow channel of a turbine. The arrangement includes a nozzle ring carrying a set of vanes, each of the vanes being connected to a vane pin housed in the nozzle ring. A rotational position of the vanes is accomplished via a vane displacement drive train including a pivotally supported pivot axle, a first actuator arm arranged on the pivot axle, which first arm is connectable to a drive actuator, a second actuator arm arranged on the pivot axle, which second arm is connected to a pin engaged with an unison ring for pivoting the unison ring, and a vane arm being connected to each vane pin and the unison ring for displacement of the vanes via pivotal displacement of the unison ring, and wherein a stop screw is arranged for limiting the pivotal displacement of the vanes.
    Type: Grant
    Filed: December 7, 2009
    Date of Patent: August 11, 2015
    Assignee: Volvo Lastvagnar AB
    Inventor: Pontus Eriksson
  • Publication number: 20150125289
    Abstract: A part of a turbomachine distributor, including an outer platform, an inner platform, at least one blade interspaced circumferentially about a longitudinal axis of the part, radial ends of the at least one blade being respectively fixed to the inner platform and to the outer platform, and a fastening element extending from the outer platform, for fastening the part to a casing of the turbomachine. The fastening element includes, on ends thereof arranged on either side of the longitudinal axis, two separate fastening tabs for fastening the part to the casing, the cumulated sum of lengths of the two fastening tabs in relation to length of the fastening element according to a transverse axis of the part being between 25% and 35%.
    Type: Application
    Filed: May 6, 2013
    Publication date: May 7, 2015
    Applicant: SNECMA
    Inventors: Sabine Maltaverne, Denis Aydin, Bruno Richard
  • Publication number: 20150125288
    Abstract: A variable geometry turbocharger includes a vane pack having rotatable vanes constrained by a pair of vane rings connected by a plurality of spacer connectors. The spacer connectors can include a spacer body for maintaining a minimum spacing between the vane rings. The spacer connectors are configured for bayonet mounting to at least one of the vane rings. To that end, the spacer connectors can include shaft portions extending from opposing sides of the spacer body. A plurality of transverse protrusions can extend outwardly from each shaft portion. Each shaft portion can be received in a respective in a vane ring. The spacer connectors can be rotated such that the transverse protrusions are offset from aperture portions that allow passage of the transverse portions, thereby retaining the vane rings in place in spaced relation. Such a system avoids close tolerances, press fits, expensive bolted joints or weld processes.
    Type: Application
    Filed: April 22, 2013
    Publication date: May 7, 2015
    Applicant: BorgWarner Inc.
    Inventor: George E. Heddy, III
  • Patent number: 9022733
    Abstract: A turbine nozzle element including an inner annular platform sector, an outer annular platform sector, and at least one vane extending between the platform sectors and connected to both of them. The nozzle element includes a single piece of composite material including fiber reinforcement densified by a matrix that is at least partially ceramic, and the fiber reinforcement includes a fiber structure that is woven by three-dimensional or multi-layer weaving, and that presents continuity throughout the volume of the nozzle element and throughout the periphery of the vane.
    Type: Grant
    Filed: June 9, 2010
    Date of Patent: May 5, 2015
    Assignees: SNECMA, SNECMA Propulsion Solide
    Inventors: Dominique Coupe, Guillaume Jean-Claude Robert Renon
  • Publication number: 20150110602
    Abstract: The invention relates to an instrumented airfoil for mounting in a flow passage through a turbine, compressor, or module of a turbine engine. An instrumentation member is attached to an airfoil and includes information-obtaining means received in a cutout formed in the airfoil and projecting relative to the leading edge or the trailing edge. According to the invention, the instrumentation member also comprises a holder portion that is united with the information-obtaining means and that is attached to the cutout in such a manner that its surface is in alignment respectively with the suction side wall, the pressure side wall, and the leading edge or the trailing edge of the airfoil, the transitions between these respective surfaces not presenting any setbacks.
    Type: Application
    Filed: October 15, 2014
    Publication date: April 23, 2015
    Applicant: SNECMA
    Inventors: Gabrijel RADELJAK, Pascal COUHIER, Benedicte LELEU, Frederic Raymond Jean MIROUDOT, Sebastien HAMEAU, Antoine Jean JAUSOVEC
  • Publication number: 20150107110
    Abstract: A welding method including the steps of: providing, in a first position, a weld target assembly having a welding region and a weld tab located adjacent the welding region, the weld tab changeable from a first physical configuration to a second physical configuration when subject to a first type of weld operation; performing a first weld process on the welding region and weld tab; moving the assembly from the first to a second position; providing safeguard apparatus for cooperating with the weld tab to: prevent the assembly from moving to the second position when the first weld procedure did not include the first type of weld operation; and permit the assembly be moved to the second position when the first weld procedure included the first type of weld operation. The assembly includes a sub-assembly having a foot member and blade portion welded together, thereby ultimately forming an output guide vane.
    Type: Application
    Filed: October 8, 2014
    Publication date: April 23, 2015
    Inventor: Matthew David CURREN
  • Patent number: 9009966
    Abstract: The construction of an internal/external single expansion ramp nozzle (nxSERN), and method of designing the same, is provided. Initial design parameters for primary stream construction are selected and additional parameters are determined by isentropic relations using the selected design parameters and Prandtl-Meyer function. The nozzle throat input and output angles are determined and used to define an initial portion of the nozzle primary stream lower expansion surface. The nozzle primary stream upper expansion surface and an aft portion of the primary stream lower expansion surface are defined using a method of characteristics. Initial and aft portions of the primary stream lower expansion surface are then connected by a straight line to define the primary stream nozzle.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: April 21, 2015
    Assignee: Northrop Gurmman Systems Corporation
    Inventors: Shane Bunnag, Gordon Hall, Kelly Strominger, John Tapee, Trajaen J. Troia
  • Patent number: 9011085
    Abstract: A Ceramic Matrix Composites (CMC) airfoil for a gas turbine engine includes at least one CMC ply which defines a suction side, an outer platform, a pressure side and an inner platform with a continuous “I”-shaped fiber geometry.
    Type: Grant
    Filed: May 26, 2011
    Date of Patent: April 21, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Ioannis Alvanos
  • Publication number: 20150101338
    Abstract: Exhaust centerbody (12?) for a turbine engine, comprising a truncated downstream part (26), which is connected to an upstream part (24) by an annular ridge (22) marking a discontinuity between the outer surfaces of the upstream and downstream parts, the outer surface of the downstream part having a substantially conical general shape, of which the tip (29) is oriented downstream and is positioned in the region of the axis A, the axial half-section of this outer surface defining a line of which the upstream end part is substantially tangential to a straight line (28) passing through the above-mentioned ridge and forming a non-zero angle ? with a tangent (30) to the outer surface of the upstream part, in the region of the ridge, and of which the downstream end part is substantially tangential to a straight line (32) passing through the above-mentioned tip and forming a non-zero angle ? with the axis A.
    Type: Application
    Filed: July 24, 2014
    Publication date: April 16, 2015
    Applicant: SNECMA
    Inventors: Guillaume POUYAU, Nicolas Sirvin
  • Publication number: 20150075168
    Abstract: A strip seal arrangement for turbine components employs acoustic damping. A sealing plate having a front face adjacent a combustion chamber and a back face facing away from a combustion chamber configured to have one or more holes of a predefined cross-sectional area. Containers having predefined volumes are attached to the back face of the sealing plate such that the one or more holes are in fluidic communication with the one or more containers thereby creating at least one acoustic damper. The side edges of the sealing plate fit into a slots of burner front panels, creating a seal between the panels.
    Type: Application
    Filed: September 26, 2014
    Publication date: March 19, 2015
    Inventors: Jeffrey DE JONGE, Andreas Huber, Bruno Schuermans, Urs Benz
  • Patent number: 8966910
    Abstract: A turbine assembly includes a fuel nozzle configured to mix fuel and air and a transition nozzle oriented to receive the fuel and air mixture from the fuel nozzle. The transition nozzle includes a transition portion and a nozzle portion integrally formed with the transition portion. The transition nozzle includes a plurality of openings oriented to channel air to facilitate cooling the transition portion and/or the nozzle portion. The transition portion is oriented to channel combustion gases towards the nozzle portion.
    Type: Grant
    Filed: June 21, 2011
    Date of Patent: March 3, 2015
    Assignee: General Electric Company
    Inventors: Kevin Weston McMahan, Ronald James Chila, David Richard Johns
  • Patent number: 8966756
    Abstract: A method of assembling gas turbine engine front architecture includes positioning inner and outer fairings relative to one another. Multiple vanes are arranged circumferentially between the inner and outer fairings. A liquid sealant is applied around a perimeter of the vanes to seal between the vanes and at least one of the fairings.
    Type: Grant
    Filed: January 20, 2011
    Date of Patent: March 3, 2015
    Assignee: United Technologies Corporation
    Inventors: Steven J. Feigleson, Dennis R. Tremblay, William R. Edwards
  • Publication number: 20150052750
    Abstract: A method and tooling for assembling a guide vane stage that includes an inner shroud and an outer shroud that are coaxial and interconnected by radial airfoils, the method including holding plates pressed against an outer surface of the inner shroud so that the plates cover gaps formed between openings in the inner shroud and the airfoils at least in part and in a manner that is leaktight, and applying a sealing resin to the inner surface of the inner shroud so that the resin fills the gaps and so that radially inner ends of the airfoils are embedded in the resin.
    Type: Application
    Filed: April 12, 2013
    Publication date: February 26, 2015
    Applicant: SNECMA
    Inventors: Romain Rene Marcel Chardonnet, Patrick Gilbert Petit, Alain Martinez
  • Publication number: 20150050135
    Abstract: A stator blade diaphragm ring includes a plurality of stator blades each having a root and a radial pin receiver. The diaphragm ring further includes a first ring having a plurality of slots, wherein each slot is engaged by the root of one of the plurality of stator blades and a second ring having a plurality of radial through passageways, wherein each radial through passageway is aligned with the radial pin receiver of one of the plurality of stator blades. The diaphragm also includes a plurality of pins, wherein each pin extends from one of the radial through passageways into the radial pin receiver of one of the plurality of stator blades.
    Type: Application
    Filed: April 2, 2013
    Publication date: February 19, 2015
    Inventors: Marco Grilli, Enrico Giusti, Enzo Imparato
  • Patent number: 8950069
    Abstract: A low leakage, integral fixed vane system for a gas turbine engine compression system which can accommodate the latest 3-D aerodynamic airfoil geometries and provide endwall ovalization control. A unitized construction wherein the vanes are integral with the case wall in the compression system.
    Type: Grant
    Filed: December 21, 2007
    Date of Patent: February 10, 2015
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Robert A. Ress, Jr.
  • Publication number: 20150033729
    Abstract: A flow control assembly for controlling cooling flow of a turbine engine is provided. The flow control assembly includes a first flow control device having a first sidewall and a second sidewall. The first sidewall is coupled to a compressor vane and is configured to define a first flow path from a compressor to a turbine vane. The second sidewall is coupled to a compressor vane and is configured to define a second flow path from the compressor to a turbine blade. A second flow control device is coupled to the compressor and includes an orifice device coupled to the compressor vane and a meter device coupled to the orifice, wherein the orifice is configured to direct a cooling flow to the meter device. A controller is configured to control the meter device to facilitate regulating the cooling flow into at least one of the first flow path and the second flow path.
    Type: Application
    Filed: July 31, 2013
    Publication date: February 5, 2015
    Applicant: General Electric Company
    Inventors: Corey Bourassa, William Dwight Gerstler, Bruce Philip Biederman
  • Patent number: 8943689
    Abstract: A method for mounting an integral inner ring (10) of a turbocompressor stator to a guide vane ring (12) comprises the following steps: -Providing the guide vane ring (12) with an inner radius S; -Providing inner ring (10) with an outer radius R, which corresponds to the inner radius S; -Pre-tensioning inner ring (10) to an outer radius r that is smaller than the outer radius R of the untensioned inner ring (10); and -Relaxing inner ring (10) to the outer radius R.
    Type: Grant
    Filed: January 14, 2010
    Date of Patent: February 3, 2015
    Assignee: MTU Aero Engines GmbH
    Inventor: Frank Stiehler
  • Patent number: 8935853
    Abstract: An exemplary turbine engine assembly includes a first shaft that is rotatably driven by a second shaft of a gas turbine engine, a compressor hub driven by the second shaft, the compressor hub within a compressor section of the gas turbine engine, an epicyclic gear train that is driven by the first shaft, and a common attachment point that secures the first shaft and the compressor hub to the second shaft.
    Type: Grant
    Filed: December 11, 2013
    Date of Patent: January 20, 2015
    Assignee: United Technologies Corporation
    Inventors: William G. Sheridan, Michael E. McCune
  • Patent number: 8936431
    Abstract: A shroud for a turbine and a method of assembling is provided. The turbine includes a housing, a rotatable shaft and a bucket extending outward therefrom. The shroud includes an alignment member which is coupled to the housing, wherein the alignment member includes a first end, a second end and a body extending between the first and second ends. The second end includes an arcuate portion to facilitate fluid flow downstream from the bucket. The shroud further includes a seal coupled to the body to facilitate sealing a gap defined between the bucket and the body.
    Type: Grant
    Filed: June 8, 2012
    Date of Patent: January 20, 2015
    Assignee: General Electric Company
    Inventors: Rohit Chouhan, Sumeet Soni
  • Publication number: 20150003964
    Abstract: An arrangement for a turbomachine is provided. The arrangement includes a vane for directing a hot gas during the operation of the turbomachine, a stator ring for securing the vane, a heat shield for protecting the stator ring from the hot gas flow wherein the heat shield is arranged in downstream direction of the hot gas flow in front of the stator ring characterized in that the heat shield comprises a plurality of channels formed therein for directing a cooling air.
    Type: Application
    Filed: February 27, 2013
    Publication date: January 1, 2015
    Applicant: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Per Granberg, Janos Szijarto
  • Publication number: 20140356155
    Abstract: The present application provides a nozzle assembly for use in a turbine engine. The nozzle assembly may include a first nozzle cavity, a second nozzle cavity, a rib positioned between the first nozzle cavity and the second nozzle cavity, a first cavity insert with a first cavity insert configuration, a second cavity insert with a second cavity insert configuration, and a rib cap positioned on the rib. The rib cap may include a rib cap configuration such that only the first cavity insert with the first cavity insert configuration fits within the first nozzle cavity and only the second cavity insert with the second cavity insert configuration fits within the second nozzle cavity.
    Type: Application
    Filed: June 3, 2013
    Publication date: December 4, 2014
    Inventors: Charles Lewis Davis, III, Frederick James Brunner
  • Publication number: 20140352324
    Abstract: A pre-cooler system is provided and includes first and second pre-coolers, each of which is sized to handle demands of one downstream flow system, a piping system by which the first and second pre-coolers are receptive of compressed air from first and second turbine engines, respectively, and by which the first and second pre-coolers are both coupled to first and second downstream flow systems that are each configured to apply the demands of one downstream flow system to the first and second pre-coolers, a first pair of dual pressure regulator shut off valves (PRSOVs) disposed in parallel with each other and between the first turbine engine and the first downstream flow system, the first pair of dual PRSOVs being arranged in series with the first pre-cooler and a second pair of dual PRSOVs disposed in parallel with each other and between the second turbine engine and the second downstream flow system, the second pair of dual PRSOVs being arranged in series with the second pre-cooler.
    Type: Application
    Filed: May 29, 2013
    Publication date: December 4, 2014
    Applicant: HAMILTON SUNSTRAND CORPORATION
    Inventors: Jeffry Ernst, John M. Maljaian