Combustor Liner Patents (Class 60/752)
  • Patent number: 10787998
    Abstract: A cooling mechanism includes a bottom wall (22) in contact with a combustion chamber, an upper wall (30), and a cooling passage (40) arranged between the bottom wall (22) and the upper wall (30). The cooling passage (40) includes a first passage (50) extending to a first direction, a second passage (60) extending to the first direction, and a connection section (70) connected with the first passage (50) and the second passage (60). The second passage (60) is arranged to have an offset to the first passage (50) in a second direction perpendicular to the first direction and along the bottom wall (22).
    Type: Grant
    Filed: March 9, 2016
    Date of Patent: September 29, 2020
    Assignees: MITSUBISHI HEAVY INDUSTRIES, LTD., JAPAN AEROSPACE EXPLORATION AGENCY
    Inventors: Daiki Watanabe, Masaki Adachi, Hiroyuki Kobayashi, Akihide Kurosu, Hideto Kawashima, Nobuki Negoro
  • Patent number: 10787928
    Abstract: A casing for use in a turbofan engine is provided. The casing includes an inner hub, an intermediate casing positioned radially outward from the inner hub, an outer casing positioned radially outward from the intermediate casing, and a plurality of struts spaced circumferentially about the inner hub and extending between the inner hub and the outer casing. At least one strut of the plurality of struts includes a flow channel extending therethrough. The casing also includes a fluid scoop defined within the inner hub, and a collector that couples the fluid scoop in flow communication with the flow channel.
    Type: Grant
    Filed: November 30, 2016
    Date of Patent: September 29, 2020
    Assignees: General Electric Company, GE Avio, S.r.l.
    Inventors: Andrew Michael Tompkins, Brandon Wayne Miller, Donald Albert Bradley, Michele Gravina, Daniel Alan Niergarth, Lorenzo Cipolla
  • Patent number: 10760430
    Abstract: A hot gas path (HGP) component of an industrial machine includes primary and secondary cooling pathways. A body includes an internal cooling circuit carrying a cooling medium. A primary cooling pathway is spaced internally in the body and carries a primary flow of a cooling medium from an internal cooling circuit. A secondary cooling pathway is in the body and in fluid communication with an internal cooling circuit. The secondary cooling pathway is fluidly incommunicative and spaced internally from the primary cooling pathway. In response to an overheating event occurring, the secondary cooling pathway opens to allow a secondary flow of cooling medium through to the outer surface of the body and/or the primary cooling pathway. The primary flow flows in the primary cooling pathway prior to the overheating event, and the secondary flow of cooling medium does not flow until after an opening of the secondary cooling pathway.
    Type: Grant
    Filed: May 31, 2017
    Date of Patent: September 1, 2020
    Assignee: General Electric Company
    Inventors: Benjamin Paul Lacy, Brian Peter Arness, Victor John Morgan, Stephen William Tesh
  • Patent number: 10753608
    Abstract: A structure is provided for a turbine engine. The structure includes a shell with a first surface, and a heat shield with a textured second surface and a textured third surface. The texture of a portion of the second surface is different than the texture of a portion of the third surface. The first surface and the second surface define a first cooling cavity between the shell and the heat shield. The first surface and the third surface define a second cooling cavity between the shell and the heat shield.
    Type: Grant
    Filed: November 21, 2014
    Date of Patent: August 25, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Frank J. Cunha, Stanislav Kostka, Jr.
  • Patent number: 10753611
    Abstract: A combustor includes a combustor shell, an inner liner disposed inside the combustor shell and having an inner surface defining a cavity configured to receive hot combustion gases from a combustion chamber of the combustor, and an outer surface, the combustor shell and the inner liner defining an annular flow channel therebetween, and a segment carrier operatively connected to the inner liner and operative to receive an upper portion of the inner liner, the segment carrier and the inner liner defining a purging cavity therebetween. The inner liner includes a plurality of impingement jet holes configured to direct a flow of cooling air from the annular flow channel to the purging cavity.
    Type: Grant
    Filed: October 5, 2017
    Date of Patent: August 25, 2020
    Assignee: GENERAL ELECTRIC CORPORATION GMBH
    Inventors: Andrey Sedlov, Igor Baibuzenko, Vladimir Vassiliev
  • Patent number: 10739001
    Abstract: A combustor for a gas turbine engine including a combustor liner support shell with a furrow formed therein; a forward liner panel mounted to the support shell via a multiple of studs, the forward liner panel including a forward liner panel rail the extends into the furrow; and an aft liner panel mounted to the support shell via a multiple of studs downstream of the forward liner panel, the aft liner panel including an aft liner panel rail that extends into the furrow.
    Type: Grant
    Filed: February 14, 2017
    Date of Patent: August 11, 2020
    Assignee: Raytheon Technologies Corporation
    Inventor: Steven W. Burd
  • Patent number: 10731858
    Abstract: A combustor of a gas turbine engine includes a multiple of liner panels mounted to the support shell, at least one of the multiple of liner panels includes a first impingement cavity that operates at a first pressure and a second impingement cavity that operates at a second pressure different than the first pressure. A method of cooling a wall assembly within a combustor of a gas turbine engine includes directing air through a support shell and a liner panel that defines a first impingement cavity and a second impingement cavity. The first impingement cavity operates at a first pressure and the second impingement cavity operates at a second pressure that is different than the first pressure.
    Type: Grant
    Filed: September 16, 2014
    Date of Patent: August 4, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Lee E. Bouldin, Jonathan J. Eastwood, Dennis M. Moura, Monica Pacheco-Tougas
  • Patent number: 10697635
    Abstract: Components for gas turbine engines having a hot side surface, a cold side surface, the cold side surface receiving cooling impingement at one or more cold locations, and at least one thermal transfer feature located between the hot side surface and the cold side surface within the component and arranged such that a condenser section of the thermal transfer feature is located proximate at least one of the cold locations and an evaporator section of the thermal transfer feature is located away from the cold location.
    Type: Grant
    Filed: March 20, 2017
    Date of Patent: June 30, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Matthew Robert Pearson
  • Patent number: 10690059
    Abstract: A gas turbine includes a plurality of combustors and a turbine with a sealing arrangement between aft frames of the combustors and a first stage nozzle of the turbine. The sealing arrangement includes first and second circumferential outer seals with a radial side seal therebetween, the outer seals include circumferential extensions with an installation clearance, and the side seal includes a leaf that obstructs the installation clearance. The sealing arrangement also includes a notch on the side seal that forms a sliding joint with extensions of the first and second outer seals.
    Type: Grant
    Filed: September 26, 2016
    Date of Patent: June 23, 2020
    Assignee: General Electric Company
    Inventors: Jesse Ellis Barton, Richard Martin DiCintio, Elizabeth Angelyn Monaghan
  • Patent number: 10690348
    Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a shell and a heat shield that is attacked to the shell. The heat shield includes a rail and a cooling element connected to the rail in a cavity. The cavity extends in a vertical direction between the shell and the heat shield. The cavity fluidly couples a plurality of apertures in the shell with a plurality of apertures in the heat shield.
    Type: Grant
    Filed: November 4, 2014
    Date of Patent: June 23, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Dennis M. Moura, Monica Pacheco-Tougas, Jonathan J. Eastwood, Lee E. Bouldin
  • Patent number: 10690006
    Abstract: A case is provided for a gas turbine engine. The case includes a wall defining a through-hole. The case also includes first and second pockets adjacent to, and on opposite sides, of the through hole. A method of reducing stress in a case of a gas turbine engine is also provided that includes reducing stress about a through-hole by providing a concavity on each side of the through-hole.
    Type: Grant
    Filed: September 12, 2014
    Date of Patent: June 23, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Hoyt Y. Chang, Jr., Yusuke Ichihashi, Yohei Fujimoto, Timothy Dale
  • Patent number: 10684017
    Abstract: An annular grommet is provided for a wall assembly of a combustor section of a gas turbine engine. The annular grommet includes a wall that at least partially defines a chamber. A wall assembly within a gas turbine engine includes a liner panel with a hot side and a cold side. The wall assembly also includes an annular grommet with a passage wall and a flange wall transverse to the passage wall. The annular grommet includes a chamber therein. A method of cooling a wall assembly within a gas turbine engine includes injecting air through a chamber in an annular grommet.
    Type: Grant
    Filed: October 21, 2014
    Date of Patent: June 16, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Dennis M. Moura, Jonathan J. Eastwood, Lee E. Bouldin
  • Patent number: 10670267
    Abstract: A combustor liner for a gas turbine is provided. The combustor liner comprises a wall and a plurality of airflow injection holes in the wall arranged in a circumferentially-extending row, the plurality of airflow injection holes including a plurality of circular first airflow injection holes and at least one non-circular second airflow injection hole.
    Type: Grant
    Filed: August 14, 2015
    Date of Patent: June 2, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Albert K. Cheung, Christos Adamopoulos
  • Patent number: 10648666
    Abstract: A wall assembly for use in a combustor of a gas turbine engine includes a transverse structure with at least one effusion passage that extends at an angle ? therethrough. The effusion passage includes an inlet in an outer periphery of a wall. A wall assembly within a gas turbine engine include a liner panel generally parallel to a support shell and a transverse structure with at least one effusion passage that extends at an angle ? therethrough. The effusion passage includes an inlet in an outer periphery of a wall that is transverse to the liner panel and the support shell.
    Type: Grant
    Filed: September 16, 2014
    Date of Patent: May 12, 2020
    Assignee: United Technologies Corporation
    Inventors: Lee E. Bouldin, Dennis M. Moura, Jonathan J. Eastwood, Monica Pacheco-Tougas
  • Patent number: 10634056
    Abstract: A combustor including: a transition piece having a cylindrical shape and including an inlet of combustion gas at one end and an outlet of the combustion gas at the other end and configured to allow the combustion gas flowing from the inlet to flow out from the outlet so as to introduce the combustion gas into a turbine; a cooling medium introduction unit introduced with the cooling medium and provided on an outer periphery portion in an outlet side of the transition piece; a cooling medium inlet configured to introduce the cooling medium into the cooling medium introduction unit; and a cooling portion, connected to the cooling medium introduction unit, provided on a portion from the outlet of the transition piece toward the inlet and configured to allow the cooling medium from the cooling medium introduction unit to pass through the outlet toward the inlet.
    Type: Grant
    Filed: December 1, 2015
    Date of Patent: April 28, 2020
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Satoshi Mizukami, Tetsu Konishi, Hiroyuki Yamazaki, Tomoharu Fujita
  • Patent number: 10634350
    Abstract: A combustion chamber includes at least one annular wall which includes at least one box like structure and each box like structure includes an inner wall, outer wall, upstream end wall and downstream end wall. The inner wall is spaced radially from the outer wall and the outer wall has a plurality of apertures for the supply of coolant into the box like structure. The inner wall, the outer wall, the upstream end wall and the downstream end wall are integral. The upstream end of the annular wall has features to secure the annular wall to an upstream ring structure and a downstream end of the annular wall has features to mount the annular wall on a downstream ring structure. The inner wall has at least one slot extending through the full thickness of the inner wall to accommodate differential thermal expansion between the inner wall and the outer wall.
    Type: Grant
    Filed: July 22, 2016
    Date of Patent: April 28, 2020
    Assignee: ROLLS-ROYCE plc
    Inventors: Stephen C Harding, Paul A Hucker, Giuseppe Rallo
  • Patent number: 10627110
    Abstract: A combustor cooling panel has a first channel and a second channel through which a cooling medium flows. Relative to an end zone in a longitudinal direction of the first channel, the second channel has: an overlapping zone that overlaps the end zone in an extension direction of the end zone by extending in the extension direction while being separated from the end zone in a circumferential direction intersecting the extension direction; and a non-overlapping zone that does not overlap the end zone in the extension direction. A bent portion that is bent toward the end zone in the circumferential direction is formed in the second channel.
    Type: Grant
    Filed: February 15, 2016
    Date of Patent: April 21, 2020
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventor: Hiroki Shibata
  • Patent number: 10584601
    Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a first plurality of openings and the first vane stage includes a second plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A first vane stage assembly and a method are also disclosed.
    Type: Grant
    Filed: August 30, 2017
    Date of Patent: March 10, 2020
    Assignee: United Technologies Corporation
    Inventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
  • Patent number: 10570742
    Abstract: The present disclosure relates to a gas turbine part, which can be exposed to high temperatures and centrifugal forces within a gas turbine. The gas turbine part can include plural sliced parts, wherein at least one of said sliced parts is made from a ternary ceramic called MAX phase, having the formula Mn+1AXn, where n=1, 2, or 3, M is an early transition metal such as Ti, V, Cr, Zr, Nb, Mo, Hf, Sc, Ta, and A is an A-group element such as Al, Si, P, S, Ga, Ge, As, Cd, In, Sn, Tl, Pb, and X is C and/or N.
    Type: Grant
    Filed: November 11, 2016
    Date of Patent: February 25, 2020
    Assignee: ANSALDO ENERGIA IP UK LIMITED
    Inventors: Hans-Peter Bossmann, Maryam Bharaini Hasani
  • Patent number: 10544942
    Abstract: A method for mounting a combustion chamber of a gas turbine engine, wherein an annular outer combustion chamber wall and an annular inner combustion chamber wall are brought in position with respect to one another and are connected to a head plate, and wherein subsequently a combustion chamber head is mounted, characterized in that the head plate is connected to the outer combustion chamber wall and the inner combustion chamber wall by means of rivets that are arranged in a circumferentially distributed manner, and that subsequently the combustion chamber head is brought in position and is screwed together by means of threaded bolts and nuts to the arrangement of head plate, outer combustion chamber wall and inner combustion chamber wall, which is pre-mounted by means of the rivet.
    Type: Grant
    Filed: December 9, 2016
    Date of Patent: January 28, 2020
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Carsten Clemen, Kay Heinze, Volker Herzog
  • Patent number: 10514169
    Abstract: A combustor liner for a gas turbine is provided. The combustor liner comprises a wall and a plurality of airflow injection holes in the wall arranged in a circumferentially-extending row, the plurality of airflow injection holes including a plurality of circular first airflow injection holes and at least one non-circular second airflow injection hole.
    Type: Grant
    Filed: August 14, 2015
    Date of Patent: December 24, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Albert K. Cheung, Christos Adamopoulos
  • Patent number: 10473330
    Abstract: A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a first liner panel side edge between a liner panel aft edge and a liner panel forward edge. The liner panel also includes a second liner panel side edge between the liner panel aft edge and the liner panel forward edge. The first and the second liner panel side edges are non-perpendicular to the liner panel forward and aft edge edges.
    Type: Grant
    Filed: November 18, 2014
    Date of Patent: November 12, 2019
    Assignee: United Technologies Corporation
    Inventors: Seth A. Max, Kevin J. Low
  • Patent number: 10473331
    Abstract: A combustor of a gas turbine engine may include a combustor shell, a first combustor panel coupled to the combustor shell, and a second combustor panel coupled to the combustor shell. The first combustor panel may have a first endrail and the second combustor panel may have a second endrail. An annular cooling cavity may be defined between the combustor shell and the first and second combustor panels and a channel may be defined between the first endrail and the second endrail, wherein direct line-of-sight through the channel from the annular cooling cavity to a combustor chamber is obstructed. Said differently, the interface between the adjacent endrails may be non-linear, in a direction from the annular cooling cavity to the combustor chamber.
    Type: Grant
    Filed: May 18, 2017
    Date of Patent: November 12, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: San Quach, Jeffrey T. Morton, Matthew D. Parekh
  • Patent number: 10473117
    Abstract: A turbine engine includes a diffuser connecting a compressor section and a turbine section. The diffuser includes a diffuser frame and multiple diffuser case sections are connected to the diffuser frame.
    Type: Grant
    Filed: July 22, 2015
    Date of Patent: November 12, 2019
    Assignee: United Technologies Corporation
    Inventors: Albert Veninger, Conway Chuong
  • Patent number: 10458652
    Abstract: A combustor adapted for use in a gas turbine engine is disclosed. The combustor includes a metallic shell forming a cavity and a ceramic liner arranged in the cavity of the metallic shell. The ceramic liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine. The ceramic liner includes a plurality of ceramic tiles mounted to the metallic shell and arranged to shield the metallic shell from heat generated in the combustion chamber.
    Type: Grant
    Filed: July 25, 2016
    Date of Patent: October 29, 2019
    Assignee: Rolls-Royce Corporation
    Inventors: Charles B. Graves, Russell N. Bennett, William G. Cummings, III, Jun Shi
  • Patent number: 10451277
    Abstract: A liner element for a gas turbine combustor having a structural wall with fixing apertures provided therethrough. The liner element has a unitary construction defining a cooling side and combustion side, and a plurality of effusion holes extending between a cooling side surface of the element and a combustion side surface of the element. The liner element is configured to be affixed to the structural wall of a combustor with its cooling side surface spaced from the wall to define a chamber between the cooling side surface and the wall, and the liner element further includes integrally formed and non-threaded protuberances on its cooling side, the protuberances being arranged to engage and extend through respective fixing apertures in the combustor wall. Also disclosed is a method of thermally insulating the liner element.
    Type: Grant
    Filed: September 21, 2015
    Date of Patent: October 22, 2019
    Assignee: ROLLS-ROYCE plc
    Inventors: Paul Ian Chandler, Anthony Pidcock
  • Patent number: 10443848
    Abstract: A grommet assembly and method of design to enhance the flow coefficient, thereof, includes a shell having a first side and an opposite second side, and a chamfered grommet projecting through the shell along a centerline and including an annular first end surface spaced outward from the first side and a conical face spanning axially and radially inward from the annular first end surface and axially beyond the second side. The assembly may further include a panel spaced from the shell and defining a cooling cavity therebetween with the conical surface defining at least in-part a hole in fluid communication through the shell and panel and isolated from the cooling cavity. A plurality of cooling channels in the grommet are in fluid communication with the cooling cavity and communicate through the panel. The combination of the conical face and the cooling channels improve the discharge coefficient of the grommet while enhancing grommet cooling.
    Type: Grant
    Filed: April 2, 2015
    Date of Patent: October 15, 2019
    Assignee: United Technologies Corporation
    Inventors: Frank J. Cunha, Stanislav Kostka, Jr., Andreas Sadil
  • Patent number: 10443850
    Abstract: A combustion chamber for a turbomachine that includes a chamber end wall and a plurality of air and fuel injection systems distributed circumferentially about an axis of the combustion chamber. The combustion chamber includes, associated with each injection system, a guide device for guiding an airflow including at least one wall mounted on the injection system and projecting in the upstream direction, one wall acting as an obstacle to a circumferential flow of air around the axis. The one wall of the guide device for guiding the airflow has a shape substantially defining a quarter of a spheroid the interior volume of which forms a guide scoop for guiding the airflow feeding the combustion chamber.
    Type: Grant
    Filed: April 21, 2016
    Date of Patent: October 15, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Sebastien Alain Christophe Bourgois, Romain Nicolas Lunel, Clement Bernard, Frederic Dos Santos, Sebastien Loval
  • Patent number: 10443854
    Abstract: A premix pilot nozzle is disclosed herein. The premix pilot nozzle includes a nozzle body. The nozzle body includes a forward wall, an aft wall, an outer band that extends between the forward wall and the aft wall and a tip portion that extends axially downstream from the aft wall. The nozzle body further defines a fuel inlet plenum that extends coaxially within the nozzle body, a fuel distribution plenum that is defined within the nozzle body radially outwardly from and in fluid communication with the fuel inlet plenum, a plurality of premix passages that extend helically around the fuel inlet plenum within the fuel distribution plenum and a plurality of air passages annularly arranged around the plurality of premix passages. One or more premix passages of the plurality of premix passages are in fluid communication with the fuel distribution plenum.
    Type: Grant
    Filed: June 21, 2016
    Date of Patent: October 15, 2019
    Assignee: General Electric Company
    Inventors: Neal William Grooms, James Harper, Yon Han Chong
  • Patent number: 10415828
    Abstract: This invention relates to a refractory lining of a tube wall (2) for an incinerator including at least four refractory tiles (3) of ceramic material which are arranged next to and above one another, wherein the tiles at their rear side, which is facing the tube wall (2), are provided with a vertical insertion channel (10) for mounting the tiles upon the holders (7) of the tube wall, wherein a free space (11) is formed between the tiles (3) and the tube wall (2), which space is filled with a curable pouring compound, and wherein a spacer (20) is provided adjacent to four mutually adjoining edges (12) of the at least four refractory tiles (3). Alternative embodiments are characterized by the use of a head bolt, and/or wedge element (50) and/or a flip-element (60).
    Type: Grant
    Filed: June 4, 2015
    Date of Patent: September 17, 2019
    Assignee: HKH Development B.V.
    Inventors: Joseph Adrianus Maria Van Der Hoeff, John Koenders
  • Patent number: 10408451
    Abstract: A heat shield element for a heat shield has a support structure. The heat shield element includes a hot side which can be exposed to hot gas, a cold side opposite the hot side, and peripheral sides connecting the hot side to the cold side. The heat shield element can be fastened to the support structure of the heat shield with the cold side facing the support structure and has a height running vertically to the cold side. The height of the heat shield element increases in a rising direction, the rising portion of the heat shield element running in the rising direction substantially up to at least one peripheral side or up to a projection that extends the hot side over the base surface of the cold side.
    Type: Grant
    Filed: September 10, 2014
    Date of Patent: September 10, 2019
    Assignee: Siemens Aktiengesellschaft
    Inventors: Marco Larson, Marc Tertilt
  • 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: 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: 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: 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