Combustor Liner Patents (Class 60/752)
  • Patent number: 10352244
    Abstract: A gas turbine combustor comprising a plurality of cooling air passages (27A) through which bled pressurized air flows from downstream of a combustion gas flow toward upstream, the plurality of cooling air passages (27A) being disposed in a wall portion (26) side by side and aligned in a flow direction of a combustion gas; wherein the plurality of cooling air passages (27A) are divided via a passage transition groove portion (33) into upstream cooling air passages (27A1) disposed closer to bled pressurized air inlet holes (30a) and downstream cooling air passages (27A2) disposed closer to bled pressurized air outlet holes (30b), and center lines (C1) of the upstream cooling air passages are non-collinear with center lines (C2) of the downstream cooling air passages.
    Type: Grant
    Filed: April 25, 2014
    Date of Patent: July 16, 2019
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Yoshiaki Yamaguchi, Satoshi Mizukami, Tomoyuki Hirata, Junichiro Masada, Tetsu Konishi, Kazumasa Takata, Hiroyuki Yamazaki, Takuya Suzuki, Shinya Ishikawa
  • Patent number: 10337738
    Abstract: A rich-quench-lean combustor assembly for a gas turbine engine includes a fuel nozzle and a dome, the fuel nozzle attached to the dome. The combustor assembly additionally includes a liner attached to or formed integrally with the dome, the liner and the dome together defining at least in part a combustion chamber. Additionally, the liner extends between a forward end and an aft end. The liner includes a plurality of quench air jets positioned between the forward end and aft end and defines a forward section extending from the quench air jets to the dome. The dome and the forward section of the liner are configured to be cooled substantially by one or both of impingement cooling or convective cooling.
    Type: Grant
    Filed: June 22, 2016
    Date of Patent: July 2, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Gregory Allen Boardman, Pradeep Naik, Allen Michael Danis
  • Patent number: 10337737
    Abstract: A gas turbine engine includes a combustor having a combustor tile assembly with improved cooling air flow channels and enhanced cooling efficiency. A method of manufacturing same is provided which increases production capabilities and the geometric configurations of the exit ports which in turn improve the hot side operating temperature of the tiles in the combustion chamber.
    Type: Grant
    Filed: June 29, 2016
    Date of Patent: July 2, 2019
    Assignee: Rolls-Royce Corporation
    Inventors: John D. Holdcraft, Jack D. Petty, Sr.
  • Patent number: 10323847
    Abstract: A tripod joint assembly for connecting first and second overlapping panel segments of a flowpath liner in a gas turbine engine includes a threaded fastener extending through an opening in the first overlapping panel segment and adjacent to an outer segment edge of the second overlapping panel segment disposed on the first overlapping segment. The assembly further includes a tripod plate having first and second plate edges and an access hole therebetween. The first plate edge contacts the first overlapping panel segment, the second plate edge contacts the outer segment edge of the second overlapping panel segment. The access hole is disposed around the threaded fastener. First and second washers are disposed around the threaded fastener, the first washer on the tripod plate opposite to the overlapping panel segments, and the second washer on the first washer opposite to the tripod plate. A threaded locknut secures the assembly.
    Type: Grant
    Filed: December 30, 2015
    Date of Patent: June 18, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Eric Robert Oswald, Scott Patrick Ryczek, Tod Kenneth Bosel, Robert Czachor
  • Patent number: 10317080
    Abstract: A liner panel for use in a combustor for a gas turbine engine includes a forward region including a multiple of effusion passages each directed at an orientation consistent with a local swirl direction of combustion gases. Another liner panel for use in a combustor for a gas turbine engine includes a forward region forward of a dilution passage and an aft region aft of the forward region. The forward region includes a multiple of effusion passages each directed generally circumferentially. The aft region includes a multiple of effusion passages each directed at an orientation generally axially. A method of cooling a wall assembly within a combustor of a gas turbine engine includes orienting a multiple of effusion passages within a forward region consistent with a local swirl direction of combustion gases.
    Type: Grant
    Filed: December 3, 2014
    Date of Patent: June 11, 2019
    Assignee: United Technologies Corporation
    Inventors: John S. Tu, Jr., Timothy S. Snyder, James B. Hoke, James P. Bangerter, Dennis J. Duhamel, David A. Burns
  • Patent number: 10309314
    Abstract: A heat shield for a combustor of a gas turbine engine includes a cold side opposite a hot side, the cold side defines a grommet that surrounds an igniter aperture, the grommet includes a multiple of fins.
    Type: Grant
    Filed: February 25, 2014
    Date of Patent: June 4, 2019
    Assignee: United Technologies Corporation
    Inventors: James B. Hoke, James P. Bangerter
  • Patent number: 10281153
    Abstract: A combustor assembly includes a first combustion chamber member and a second combustion chamber member. The first and second combustion chamber members are each formed of a CMC material and include adjacently positioned coupling flanges. A mounting assembly includes a pair of mounting flanges positioned on opposite sides of the coupling flanges of first and second combustion chamber members. An attachment member of the mounting assembly clamps the pair of mounting flanges together to mount the first and second combustion chamber members.
    Type: Grant
    Filed: February 25, 2016
    Date of Patent: May 7, 2019
    Assignee: General Electric Company
    Inventors: David Andrew Hannwacker, Stephen John Howell
  • Patent number: 10267520
    Abstract: Combustor panel bodies with first and second sides, a pin array of cooling pins extending from the first side, with each pin extending a first height from the first side and having a pin diameter, each pin separated from adjacent pins by a pin array separation distance. A structural protrusion extending from the first side with no pins located at a position within a flashing distance that is equal to a protrusion separation distance plus one half of the pin diameter. A location of the pin is measured from a center point of the pin to a closest point on the exterior surface of the structural protrusion. A pin array scallop is integrally formed with the structural protrusion forming a reduction in material such that each pin of the array that is closest to the structural protrusion is positioned the pin array separation distance from the structural protrusion.
    Type: Grant
    Filed: August 11, 2017
    Date of Patent: April 23, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jason Shenny, Jeffrey T. Morton, Alberto A. Mateo
  • Patent number: 10267521
    Abstract: A gas turbine engine combustor has a dome and a shell extending axially from the dome. The dome and the shell cooperates to define a combustion chamber. A dome heat shield is mounted to the dome inside the combustion chamber. A front heat shield is mounted to the shell inside the combustion chamber. The dome heat shield and the front heat shield have axially overlapping portions cooperating to define a flow guiding channel. The flow guiding channel has a length (L) and a height (h). The length (L) is at least equal to the height (h).
    Type: Grant
    Filed: April 13, 2015
    Date of Patent: April 23, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Michael Papple, Robert Sze
  • Patent number: 10260749
    Abstract: A combustion chamber wall is hollow, has a first surface and a second surface and includes a plurality of polyhedron shaped chambers defined by a matrix of integral interconnected walls. The walls of the chambers in a first layer define the first surface of the combustion chamber wall and the walls of the chambers in a third layer define the second surface of the combustion chamber wall. The chambers are fluidly interconnected by apertures extending through the integral interconnected walls of the chambers for the flow of coolant there-between. The walls of the chambers in the first layer have apertures extending there-through to supply coolant into the first layer and the walls of the chambers in the third layer have apertures extending there-through to supply coolant from the third layer into the combustion chamber. The combustion chamber wall is manufactured by additive layer manufacture.
    Type: Grant
    Filed: January 29, 2015
    Date of Patent: April 16, 2019
    Assignee: ROLLS-ROYCE plc
    Inventor: Stephen Charles Harding
  • Patent number: 10240790
    Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall, which includes a shell and a heat shield. The heat shield includes a base and a plurality of panel rails. The panel rails are connected to the base and extend vertically to the shell. The panel rails include first and second rails. A vertical height of the first rail at a first location is less than a vertical height of the second rail at a second location.
    Type: Grant
    Filed: October 31, 2014
    Date of Patent: March 26, 2019
    Assignee: United Technologies Corporation
    Inventors: Jonathan J. Eastwood, Dennis M. Moura
  • Patent number: 10234140
    Abstract: A liner panel is provided for use in a gas turbine engine. The liner panel includes an intermediate rail that extends from a cold side of a liner panel. The liner panel also includes a multiple of heat transfer augmentors, which generally decrease in height with respect to a distance from the intermediate rail.
    Type: Grant
    Filed: December 31, 2014
    Date of Patent: March 19, 2019
    Assignee: United Technologies Corporation
    Inventors: Frank J. Cunha, Stanislav Kostka
  • Patent number: 10215039
    Abstract: A ducting arrangement (12) for a combustion turbine engine is provided. The arrangement includes a ceramic liner (22) defining a hot gas path throughout a length of the ducting arrangement. A cooling sleeve (24) is disposed circumferentially outwardly onto the ceramic liner along the length. A metallic support frame (26) is disposed circumferentially outwardly onto the cooling sleeve along the length. The cooling sleeve may be structured with structural features along the length for biasing against the ceramic liner and the metallic support frame to resiliently accept mechanical and thermal growth induced loading that develops between the ceramic liner and the metallic support frame during operating conditions of the combustion turbine engine.
    Type: Grant
    Filed: July 12, 2016
    Date of Patent: February 26, 2019
    Assignee: SIEMENS ENERGY, INC.
    Inventor: Anthony L. Schiavo
  • Patent number: 10203114
    Abstract: A sleeve assembly for a combustion system is provided. The sleeve assembly includes a liner defining a combustion chamber having a flow axis and a primary combustion zone. The liner has a forward end and an aft end such that the liner circumscribes the flow axis. The sleeve assembly also includes a shell circumscribing the liner such that a cooling duct is defined between the liner and the shell. The shell includes a unisleeve having a forward end and an aft end. The aft end of the unisleeve is positioned axially upstream of the aft end of the liner, defining a gap between the aft end of the liner and the aft end of the unisleeve. The unisleeve is mounted to the liner at circumferentially spaced locations along an axial plane between the forward end and the aft end of the unisleeve.
    Type: Grant
    Filed: March 4, 2016
    Date of Patent: February 12, 2019
    Assignee: General Electric Company
    Inventors: David William Cihlar, Jonathan Hale Kegley, Andrew Grady Godfrey, Christopher Paul Willis
  • Patent number: 10197279
    Abstract: A rich-quench-lean combustor assembly for a gas turbine engine includes a fuel nozzle and a dome, the fuel nozzle attached to the dome. The combustor assembly additionally includes a liner attached to or formed integrally with the dome, the liner and the dome together defining at least in part a combustion chamber. The liner extends between a forward end and an aft end. The liner includes a plurality of quench air jets positioned between the forward end and aft end. The quench air jets include a plurality of primary stage air jets and a plurality of secondary stage air jets. The plurality of primary stage air jets are each spaced from the plurality of secondary stage air jets along the axial direction and together provide the combustion chamber with a quench airflow.
    Type: Grant
    Filed: June 22, 2016
    Date of Patent: February 5, 2019
    Assignee: General Electric Company
    Inventors: Gregory Allen Boardman, Pradeep Naik, Allen Michael Danis
  • Patent number: 10190504
    Abstract: A combustor seal for use between a downstream end of a combustor and a turbine vane includes a seal body and a plurality of seal alignment features. The plurality of seal alignment features projects from the seal body. The seal alignment features are arranged such that there is only one alignment of the combustor seal with the turbine vane.
    Type: Grant
    Filed: October 1, 2013
    Date of Patent: January 29, 2019
    Assignee: United Technologies Corporation
    Inventors: Kevin Joseph Low, Joey Wong
  • Patent number: 10184343
    Abstract: A system having an impingement sleeve configured to receive a cooling flow is provided. The impingement sleeve includes a column of ports extending from an outer surface of the impingement sleeve, wherein each port of the column of ports is configured to direct an impingement stream toward a heated structure, and each impingement stream includes a portion of the cooling flow. Further, one or more pins are disposed outside the outer surface relative to the cooling flow, wherein each pin of the one or more pins is coupled between pairs of ports of the column of ports.
    Type: Grant
    Filed: February 5, 2016
    Date of Patent: January 22, 2019
    Assignee: General Electric Company
    Inventors: Benjamin Paul Lacy, David Edward Schick, Sandip Dutta
  • Patent number: 10167781
    Abstract: An igniter assembly for a combustion system of a gas turbine engine is provided. The igniter assembly includes an igniter plug having a tip which, in use, is located at an aperture in a wall of a flame-tube of the combustion system such that the tip can provide an electrical discharge to ignite an air-fuel mixture within the flame-tube. The igniter assembly further includes a substantially annular igniter boss which locates on the wall of the flame-tube at the aperture to encircle the tip. The igniter boss has a slot formed therein at one side of the tip. An entrance of the slot receives air from outside the flame-tube and an exit of the slot delivers the air as a sheet-shaped flow over the tip. The slot is tapered such that the thickness of the slot narrows from its entrance to its exit.
    Type: Grant
    Filed: September 30, 2015
    Date of Patent: January 1, 2019
    Assignee: ROLLS-ROYCE plc
    Inventor: Ian James Toon
  • Patent number: 10151241
    Abstract: A regenerative gas turbine combustor is provided that enable to reduce an amount of leakage of compressed air before preheating to compressed air after the preheating. The regenerative gas turbine combustor is such that a compressed air passage between a combustor inner cylinder 10 and a tail cylinder 12, and a combustor outer cylinder 7 is blocked by a division wall 15 at a position between a bleeding port 13 and an injection port 14, and compressed air is preheated in a regenerator 4 and then the compressed air thus preheated is burnt together with fuel. This combustor includes seal rings 17a-17c, a holder 16 installed on the inner circumferential portion of the division wall 15 and having ring grooves 25a-25c for holding the respective seal rings 17a-17c, and gaps 20 provided between the inner circumferential surfaces of the ring grooves 25a-25c and the outer circumferential surfaces of the seal rings 17a-17c.
    Type: Grant
    Filed: May 20, 2014
    Date of Patent: December 11, 2018
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Tatsuya Fukuda, Yasuyuki Watanabe, Hironori Tsukidate
  • Patent number: 10145251
    Abstract: A turbomachine includes a plurality of transition ducts disposed in a generally annular array. An outlet of each of the plurality of transition ducts is offset from an inlet along the longitudinal axis and the tangential axis. Each of the plurality of transition ducts further includes an upstream portion and a downstream portion, the upstream portion extending between the inlet and an aft end, the downstream portion extending between a head end and the outlet. The turbomachine further includes a support ring assembly downstream of the plurality of transition ducts along a hot gas path. The turbomachine further includes a plurality of support assemblies directly connecting the upstream portion of at least one transition duct of the plurality of transition ducts to the support ring assembly. Each of the plurality of support assemblies includes a rod extending between the upstream portion and the support ring assembly.
    Type: Grant
    Filed: March 24, 2016
    Date of Patent: December 4, 2018
    Assignee: General Electric Company
    Inventors: James Scott Flanagan, Kevin Weston McMahan, Jeffrey Scott LeBegue
  • Patent number: 10139112
    Abstract: The invention relates to an annular combustion chamber of a gas turbine having a machine axis. The combustion chamber includes at least two zones. A first zone receives the fuel/air mixture of a plurality of burners. A second zone guides the hot gases being produced by the burners from the first zone to an entrance of a turbine section of said gas turbine. An annular transition liner includes a plurality of liner segments located at the transition between said first zone and second zone. Each of the liner segments includes with respect to the axial hot gas flow a leading edge, a trailing edge, and two sidewalls, and is provided with axial mounting means at the leading and trailing edges, such that the liner segment can be installed in axial direction and is axially fixed by respective segments of the neighboring first zone.
    Type: Grant
    Filed: June 2, 2015
    Date of Patent: November 27, 2018
    Assignee: General Electric Company
    Inventors: Uwe Rüdel, Urs Benz, Christoph Appel, Ivan Lenuzzi
  • Patent number: 10132175
    Abstract: An arrangement (10) for delivering gases from combustors (15) to a first row of blades. The arrangement (10) includes at least an upstream flow path (60) including an aft first side wall (64) and a downstream flow path (62) including a forward second side wall (66). A convergence junction trailing edge (40) is defined at a downstream terminal edge (41) of the first side wall (64), and the second side wall (66) converges toward the first side wall (64) in the direction of the convergence junction trailing edge (40). An impingement sheet structure (78) is located between and provides impingement cooling air to the first and second side walls (64, 66). Openings (88) provide a cooling air passage between the first and second side walls (64, 66) and provide a flow of post impingement air into the gas path at the convergence junction trailing edge (40).
    Type: Grant
    Filed: October 7, 2014
    Date of Patent: November 20, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventor: David A. Little
  • Patent number: 10107496
    Abstract: A front panel for a combustor has a hot side and a cold side and at least one reception adapted for receiving a combustor part. The front panel has a double-wall design with a hot-side wall and a cold-side wall. The hot-side wall defines a hot-side downstream surface of the front panel. The cold-side wall defines a cold-side upstream surface of the front panel. The hot-side wall and the cold-side wall are axially spaced from one another, extend parallel to one another, and are connected to one another by an outer side wall.
    Type: Grant
    Filed: September 29, 2015
    Date of Patent: October 23, 2018
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Ulrich Rathmann, Naresh Aluri, Kaspar Loeffel, Michael Huber
  • Patent number: 10094564
    Abstract: A combustor for a gas turbine engine including a combustor shell, a heat shield mounted to the combustor shell spaced-apart from the combustor shell to define an air gap therebetween, a core dilution passageway extending through the combustor shell and the heat shield, and a sub-chamber disposed within the air gap in fluid communication with the core dilution passageway. The sub-chamber is separated from a remainder of the air gap by at least one intermediate rail projecting across the air gap and forming an outer boundary of a peripheral area of the core dilution passageway. Impingement holes are formed through the combustor shell and in fluid communication with the sub-chamber. A method of cooling an area surrounding a dilution hole in a combustor is also presented.
    Type: Grant
    Filed: April 17, 2015
    Date of Patent: October 9, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Larry Lebel
  • Patent number: 10088161
    Abstract: A liner panel for use in a gas turbine engine. The liner panel has a hot side and a cold side. The liner panel includes a rail extending from the cold side and a multiple of studs extending from the cold side. At least one of the multiple of studs extends from, in part, the rail.
    Type: Grant
    Filed: August 29, 2014
    Date of Patent: October 2, 2018
    Assignee: United Technologies Corporation
    Inventors: Christopher Drake, Stanislav Kostka, Jr., Frank J. Cunha
  • Patent number: 10077903
    Abstract: Aspects of the disclosure are directed to a cooling design feature for inclusion in a liner of an aircraft, comprising: a plurality of angled holes, and at least one through hole separating all combinations of any two of the angled holes, wherein the at least one through hole is oriented at an angle that is substantially perpendicular to a surface of the liner, and wherein each of the plurality of angled holes are non-parallel to the at least one through hole.
    Type: Grant
    Filed: October 19, 2015
    Date of Patent: September 18, 2018
    Assignee: United Technologies Corporation
    Inventors: John S. Tu, James B. Hoke, Monica Pacheco-Tougas, Timothy S. Snyder, Dennis M. Moura, Anthony Van
  • Patent number: 10041675
    Abstract: A seal for sealing a combustor heat shield against an interior surface of a combustor shell, the seal comprising: an upstream rail and an downstream rail defining an intermediate groove therebetween, each rail having a sealing surface with a plurality of slots extending between an upstream wall surface and a downstream wall surface, the sealing surface conforming to the interior surface of the combustor shell and defining a leakage gap therebetween.
    Type: Grant
    Filed: June 4, 2014
    Date of Patent: August 7, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Larry Lebel, Michael Papple
  • Patent number: 9957893
    Abstract: A combustor (10) according to the invention includes: a combustor basket (14) in which compressed air and fuel are mixed with each other and the mixture is combusted; a transition piece (17) in which a tip portion of the combustor basket (14) is inserted with a gap (C) therebetween; a spring clip (19) that seals the gap between the combustor basket (14) and the transition piece (17); a throttle section (21) that is provided in an opening portion (Ck) of the gap (C) that is opened to the transition piece (17) on the tip side of the combustor basket (14), and narrows an opening area of the opening portion (Ck), compared to the base end side; and cooling device (22) for cooling the throttle section (21).
    Type: Grant
    Filed: March 14, 2012
    Date of Patent: May 1, 2018
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Satoshi Takiguchi, Keijiro Saito, Teruhiro Matsumoto, Kenji Sato, Hidenobu Tamai, Shigemi Mandai
  • Patent number: 9958159
    Abstract: A combustor assembly for a gas turbine engine includes a hanger and a combustor liner fixed to the hanger such as, for example, by an annular weld joint. The combustor liner has an inner surface extending along an axis and is operable to define either a radial outer boundary or a radial inner boundary of the combustion chamber. The combustor assembly also includes a heat shield at least partially overlapping and confronting the inner surface of the combustor liner along the axis, with the heat shield releasably engaged with the hanger.
    Type: Grant
    Filed: December 11, 2013
    Date of Patent: May 1, 2018
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Michel S. Smallwood, Mindi D. Wigal
  • Patent number: 9958163
    Abstract: A gas turbine combustor is provided in which product reliability and heat transfer promotion are compatible while suppressing an increase in pressure loss. In a gas turbine combustor comprising a combustor liner, an outer tube provided around an outer periphery of the combustor liner, and an annular flow passage in which a cooling medium (cooling air) flows and which is formed between an outer surface of the combustor liner and an inner surface of the outer tube, the outer tube includes an inner diameter reduced portion and a taper portion smoothly connecting the inner diameter reduced portion and an inner peripheral portion on an upstream side, and is provided at an inner surface of the taper portion with longitudinal vortex generating means generating a vortex that has a central rotation axis in a flowing direction of the cooling medium (cooling air).
    Type: Grant
    Filed: October 10, 2014
    Date of Patent: May 1, 2018
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Shohei Numata, Osami Yokota, Tetsuma Tatsumi, Akinori Hayashi
  • Patent number: 9903209
    Abstract: The invention refers to a rotor blade or guide vane airfoil for a gas turbine engine having a longitudinal axis and a source of cooling fluid. The airfoil has a pressure wall, a suction wall, a leading edge, a trailing edge and at least one cooling fluid flow passage. The cooling fluid flow passage is in fluid communication with the source of cooling fluid. Means for directing cooling fluid at least to the trailing edge are provided, whereas the cooling fluid flow passage including: a plurality of axially extending walls, each of the walls extending laterally between the pressure wall and suction wall. The plurality of walls are radially spaced within the cooling fluid flow passage such that adjacent pairs of walls define a channel. The axial spacing between the adjacent walls include in radial direction of the airfoil a pins and a ribs structure, wherein the pins holistic or approximately cover the axial height of the channel.
    Type: Grant
    Filed: December 18, 2014
    Date of Patent: February 27, 2018
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Joerg Krueckels, Marc Widmer
  • Patent number: 9903590
    Abstract: A double wall structured combustor having an outer wall having an inner surface and an outer surface and an inner wall comprising a plurality of tiles. Each tile has at least one interlocking member at a first wall and at least one interengaging member at a second wall. The interlocking member extending through an aperture in the outer wall, and the interengaging member at the second wall engaging with a cutaway section in the first wall of an adjacent tile. On assembly of the combustion chamber, the interlocking members and interengaging members of the tiles ensure lower profile fixings and an overall reduction in number of conventional fasteners used.
    Type: Grant
    Filed: December 3, 2014
    Date of Patent: February 27, 2018
    Assignee: ROLLS-ROYCE plc
    Inventors: Ian Murray Garry, Michael Lawrence Carlisle
  • Patent number: 9890953
    Abstract: A combined liner and panel for use in a gas turbine engine comprise a ceramic matrix composite panel having a plurality of extending members extending away from a face of ceramic matrix composite panel which will face hot products of combustion. A liner includes a plurality of spring members that apply a bias force biasing the extending members. The spring members bias the extending members on the panel in a direction away from the face of the panel which will face the hot products of combustion. A gas turbine engine, and a method of attaching a ceramic matrix composite panel to a liner are also disclosed.
    Type: Grant
    Filed: January 2, 2015
    Date of Patent: February 13, 2018
    Assignee: United Technologies Corporation
    Inventors: Jose E. Ruberte Sanchez, Timothy J. McAlice, Kevin L. Rugg
  • Patent number: 9885480
    Abstract: A combustion chamber of a combustor for a gas turbine is provided. A combustion chamber includes a plurality of segments arranged annularly about an axis of the combustion chamber, each segment comprising a radial inner wall portion and a radial outer wall portion, a first section comprising an opening for the installation of a burner, and a second section at which at least one airfoil extends between the radial inner wall portion and radial outer wall portion of the segment.
    Type: Grant
    Filed: December 21, 2012
    Date of Patent: February 6, 2018
    Assignee: Siemens Aktiengesellschaft
    Inventors: Magnus Hasselqvist, Frank Rubensdorffer
  • Patent number: 9840924
    Abstract: A gas turbine system (1) including a burner arrangement having a tubular combustion chamber (5), a turbine (6) and a transition duct (7) connecting the combustion chamber (5) and the turbine (6), wherein the transition duct (7) is provided with an axially extending cooling air channel (11). The transition duct (7) includes a plurality of axially extending cooling air channels, and wherein each cooling air channel (11) is provided with one single inlet (12) opened to the outside of the transition duct (7) and with one single outlet (12) opened to the inside of the transition duct (7).
    Type: Grant
    Filed: August 15, 2014
    Date of Patent: December 12, 2017
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Matthias Hase, Paul A. Sanders, Vaidyanathan Krishnan
  • Patent number: 9835332
    Abstract: A combustion chamber arrangement including an outer wall and an inner wall spaced from the outer wall and the outer wall supports the inner wall. The inner wall including at least one row of circumferentially arranged tiles. At least one tile in the at least one row of tiles having an L, or V, shaped downstream end and the downstream end of the tile in the row of tiles having a first portion extending from the downstream end of the tile towards and sealing with an inner surface of the outer wall and a second portion extending from the first portion in a downstream direction and away from the inner surface of the outer wall. The first portion of the downstream end of the tile having a plurality of apertures to supply coolant over an inner surface of the second portion of the downstream end of the tile.
    Type: Grant
    Filed: August 13, 2014
    Date of Patent: December 5, 2017
    Assignee: ROLLS-ROYCE plc
    Inventors: Lisa Jane Jopp, Nathan Thomas Willis
  • Patent number: 9810097
    Abstract: A corrugated shield comprises a mounting base and a corrugated ring section. The mounting base is disposed at an aft end of the ring section for securing the shield ring section within a generally annular cavity. The generally annular cavity is defined at least in part by a hot fluid flow path boundary wall, and a radially adjacent and spaced apart cold fluid flow path boundary wall. The corrugated ring section is configured to substantially block a line of sight between the hot fluid flow path boundary wall and the cold fluid flow path boundary wall.
    Type: Grant
    Filed: September 14, 2015
    Date of Patent: November 7, 2017
    Assignee: United Technologies Corporation
    Inventors: Alisha M. Davis, Christina S. Liebel, Conway Chuong
  • Patent number: 9810154
    Abstract: A casing body for a hot gas flow includes an outer casing body having a hot gas side with a precisely prepared locating surface. A pin-type retainer is disposed on the locating surface, and an inner heat shield is disposed at a distance from the hot gas side of the outer casing body and fastened to the retainer.
    Type: Grant
    Filed: August 23, 2011
    Date of Patent: November 7, 2017
    Assignee: ANSALDO ENERGIA IP UK LIMITED
    Inventors: Marc Rauch, Peter Oskar Baldischweiler
  • Patent number: 9777925
    Abstract: There is provided a gas turbine combustor capable of improving cooling performance of a combustion chamber thereof and reducing the amount of NOx emissions.
    Type: Grant
    Filed: November 3, 2014
    Date of Patent: October 3, 2017
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Yoshitaka Hirata, Shohei Yoshida, Tomoki Uruno, Akinori Hayashi, Hirokazu Takahashi
  • Patent number: 9767384
    Abstract: A handheld scanner incorporates vision software to allow the handheld scanner to be trained for OCR. The handheld scanner can include a user interface to allow a user to associate an image of a mark with electronic data for the mark. The user interface, along with a range finder, can also be used to influence variables that affect the quality of an image scan, thereby improving the quality of results for the image scan and/or decode process.
    Type: Grant
    Filed: October 23, 2014
    Date of Patent: September 19, 2017
    Assignee: COGNEX CORPORATION
    Inventors: James A. Negro, Carl W. Gerst, III
  • Patent number: 9765969
    Abstract: An improved combustor for a gas turbine is operable to provide high combustion efficiency in a compact combustion chamber. The combustor includes a counter swirl doublet for improved fuel/air mixing. The enhanced combustor assembly and method of operation improves operation of the turbine.
    Type: Grant
    Filed: December 20, 2013
    Date of Patent: September 19, 2017
    Assignee: Rolls-Royce Corporation
    Inventors: Charles B. Graves, Donald M. Wicksall, Thomas F. Richardson, Jr.
  • Patent number: 9733141
    Abstract: A method of measuring a residence time in a gas-turbine engine is disclosed that includes measuring a combustor pressure signal at a combustor entrance and a turbine exit pressure signal at a turbine exit. The method further includes computing a cross-spectrum function between the combustor pressure signal and the turbine exit pressure signal, calculating a slope of the cross-spectrum function, shifting the turbine exit pressure signal an amount corresponding to a time delay between the measurement of the combustor pressure signal and the turbine exit pressure signal, and recalculating the slope of the cross-spectrum function until the slope reaches zero.
    Type: Grant
    Filed: April 23, 2015
    Date of Patent: August 15, 2017
    Assignee: The United States of America as Represented by the Administrator of National Aeronautics and Space Administration
    Inventor: Jeffrey H. Miles
  • Patent number: 9702258
    Abstract: A gas turbine engine which has at least a combustor section and a turbine cylinder section, wherein the combustor section includes a transition piece coupled to a vane carrier assembly, wherein the vane carrier assembly includes a plurality of holes that correspond with one or more holes of the transition piece, and wherein at least one of the pluralities of holes is adapted to receive a pin-type member therein for shifting the transition piece toward an upstream or downstream end. A system and method for shifting a transition piece in a gas turbine engine includes at least moving a pin-type member from a first position to a second position, where the movement shifts the transition piece in a direction towards an upstream end or a downstream end.
    Type: Grant
    Filed: July 1, 2014
    Date of Patent: July 11, 2017
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Clinton A. Mayer, William M. Kieffer, Paul G. Hicks
  • Patent number: 9677767
    Abstract: A combustion turbine engine combustor section includes a plurality of annularly arrayed combustors housed within paired combustor portals of a combustor casing. Each combustor portal has a corresponding top hat cover having a peripheral flange. The paired combustor portals are formed in combustor housings having a figure eight-shaped sleeve wall planform. The paired adjoining combustor portals share a common Siamesed portion of the sleeve wall. A combustor portal mating surface is formed on an axial distal end of the sleeve wall, having a figure eight planform and defining a first array of fastener receiving apertures. A top hat cover retention bracket assembly having a composite planform conforming to the combustor portal mating surface planform and a second array of apertures that conform to the first array pattern apertures, is placed over the peripheral flanges of the paired combustor top hat covers and secured by top hat cover fasteners.
    Type: Grant
    Filed: May 29, 2014
    Date of Patent: June 13, 2017
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Andrew Carlson, William W. Pankey
  • Patent number: 9625151
    Abstract: A combustor liner grommet is disclosed. The grommet may include a peripheral wall defining a hole in a combustor liner and further including at least one cooling air flow channel. The cooling air flow channel in the grommet wall may be a slot or a hole. The channel may increase cooling flow to the grommet and the combustor liner around the grommet to prevent cracking from heat stress.
    Type: Grant
    Filed: September 25, 2012
    Date of Patent: April 18, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jonathan M. Jause, Dennis John Duhamel, James B. Hoke, John S. Tu
  • Patent number: 9612017
    Abstract: A combustor for use in a gas turbine engine and methods for assembling the same are disclosed. The combustor includes an outer case and a combustion liner. The combustion liner is arranged radially inward of the outer case. The combustion liner is arranged to define an annular combustion chamber.
    Type: Grant
    Filed: April 24, 2015
    Date of Patent: April 4, 2017
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Daniel K. Vetters
  • Patent number: 9528701
    Abstract: A system for tuning a combustor of a gas turbine includes a flow sleeve having an annular main body. The main body includes an upstream end, a downstream end, an inner surface and an outer surface. A cooling channel extends along the inner surface of the main body. The cooling channel extends at least partially between the downstream end and the upstream end of the main body.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: December 27, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventor: Michael John Hughes
  • Patent number: 9518738
    Abstract: The present invention relates to a gas-turbine combustion chamber having a combustion chamber wall including a tile carrier, on which wall tiles are mounted at a distance to form an impingement cooling gap, where the tile carrier has impingement cooling holes and the tile is provided with effusion holes, where the tile has on its side facing the tile carrier a surface structure which raises from the surface of the tile and extends in the direction of the tile carrier.
    Type: Grant
    Filed: February 13, 2014
    Date of Patent: December 13, 2016
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Miklos Gerendas
  • Patent number: 9511447
    Abstract: A turbulator fabrication process and a fabricated article are provided. The turbulator fabrication process includes providing a system configured for directing a first fusion energy and a second fusion energy, positioning a turbulator material on a substrate, and directing the first fusion energy and the second fusion energy toward the turbulator material and the substrate. The directing of the first fusion energy and the second fusion energy modifies the turbulator material forming one or more turbulators on the substrate. The fabricated article includes a substrate and one or more turbulators formed on the substrate. Each of the one or more turbulators includes at least one root portion providing a concave transition between the substrate and the turbulator.
    Type: Grant
    Filed: December 12, 2013
    Date of Patent: December 6, 2016
    Assignee: General Electric Company
    Inventors: Dechao Lin, Srikanth Chandrudu Kottilingam, Yan Cui, David Vincent Bucci, Xiaoxue Diao
  • Patent number: 9500370
    Abstract: A fuel nozzle in a combustion turbine engine that includes: a fuel plenum defined between an circumferentially extending shroud and axially by a forward tube-sheet and an aft tube-sheet; and a mixing-tube that extends across the fuel plenum that defines a passageway connecting an inlet formed through the forward tube-sheet and an outlet formed through the aft tube-sheet, the mixing-tube comprising one or more fuel ports that fluidly communicate with the fuel plenum. The mixing-tube may include grooves on an outer surface, and be attached to the forward tube-sheet by a connection having a fail-safe leakage path.
    Type: Grant
    Filed: December 20, 2013
    Date of Patent: November 22, 2016
    Assignee: General Electric Company
    Inventor: Carl Robert Barker