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1. 发明授权

US10928069B2 Small exit duct for a reverse flow combustor with integrated fastening elements 有权
公开(公告)号：US10928069B2
公开(公告)日：2021-02-23
申请号：US15185310
申请日：2016-06-17
申请人： Pratt & Whitney Canada Corp.
发明人： Honza Stastny , Robert Sze
IPC分类号： F23R3/60 , F23R3/54
摘要： The described reverse flow combustor of a gas turbine engine includes inner and outer combustor liners defining a combustor chamber therewithin. A large exit duct and a small exit duct are disposed at downstream ends of the outer and inner liner respectively. The small exit duct includes an annular ring removably mounted to a support element of the gas turbine engine by one or more fastening elements that are integrally formed with the annular ring. The fastening elements are mountable with corresponding features of the support element and removably fastened thereto.

2. 发明授权

US10767512B2 Particle-trapping device for a turbomachine and turbomachine with such a device 有权
公开(公告)号：US10767512B2
公开(公告)日：2020-09-08
申请号：US15758337
申请日：2016-09-08
申请人： SAFRAN HELICOPTER ENGINES
发明人： Amaury Paillard , Stephane Pascaud
IPC分类号： B01D39/00 , F01D25/32 , F02C3/14 , F02C7/052 , F23R3/04 , F23R3/54
摘要： The invention relates to a particle-trapping device (2) for a turbomachine, said particles being contained in an air stream flowing inside a turbomachine, in particular the air stream flowing in the bypass region (17) of the combustion chamber (13) of said turbomachine. The device is characterized in that it comprises: —at least two particle deflectors (3, 3a, 3b, 3c), —a member (5) for collecting and storing the particles deflected by said deflector, —and means (6) for attaching said trapping device (2) to a part of the turbomachine.

3. 发明授权

US10690345B2 Combustor assemblies for use in turbine engines and methods of assembling same 有权
公开(公告)号：US10690345B2
公开(公告)日：2020-06-23
申请号：US15203110
申请日：2016-07-06
申请人： General Electric Company
发明人： Joseph Douglas Monty , John Carl Jacobson , Stephen John Howell
IPC分类号： F23R3/00 , F02C3/04 , F23R3/54 , F02C7/18
摘要： A combustor assembly for use in a gas turbine engine includes a combustor liner that defines a combustion chamber and includes an axial combustion portion and a curved transition portion. The combustion liner also includes an inner surface and an outer surface and a first plurality of cooling channels defined between the inner and outer surfaces. The combustor assembly also includes a sleeve substantially circumscribing the combustor liner such that an annular cavity is defined between the combustor liner and the sleeve. The sleeve includes a second plurality of cooling channels defined therethrough that are configured to channel a fluid against the combustor liner outer surface.

4. 发明授权

US10465907B2 System and method having annular flow path architecture 有权
公开(公告)号：US10465907B2
公开(公告)日：2019-11-05
申请号：US14849552
申请日：2015-09-09
申请人： General Electric Company
发明人： Nan Zong , Ahmed Mostafa ELKady , Mark Anthony Mueller , Pradeep Naik , Gerardo Antonio Salazar Lois , Rishikesh Prakash Karande , Jeffrey Michael Martini
IPC分类号： F23R3/04 , F23R3/00 , F23R3/10 , F23R3/28 , F23R3/44 , F23R3/46 , F04D29/54 , F23R3/50 , F23R3/54
摘要： A system including an annular combustor having a first liner wall disposed circumferentially about an axis, a combustion chamber disposed circumferentially about the first liner wall, and a second liner wall disposed circumferentially about the combustion chamber. The annular combustor is configured to direct a combustion gas flow in a downstream direction through the combustion chamber away from a head end toward a turbine. The system also includes a supply passage configured to supply a fluid flow from a compressor to the combustion chamber. The supply passage has a flow path architecture having a turning portion that turns the fluid flow from a compressor discharge direction to an upstream direction generally opposite the downstream direction of combustion gas flow.

5. 发明申请

US20180266278A1 PARTICLE-TRAPPING DEVICE FOR A TURBOMACHINE AND TURBOMACHINE WITH SUCH A DEVICE 审中-公开
公开(公告)号：US20180266278A1
公开(公告)日：2018-09-20
申请号：US15758337
申请日：2016-09-08
申请人： SAFRAN HELICOPTER ENGINES
发明人： Amaury PAILLARD , Stephane PASCAUD
IPC分类号： F01D25/32 , F02C3/14 , F02C7/052 , F23R3/04 , F23R3/54
摘要： The invention relates to a particle-trapping device (2) for a turbomachine, said particles being contained in an air stream flowing inside a turbomachine, in particular the air stream flowing in the bypass region (17) of the combustion chamber (13) of said turbomachine. The device is characterized in that it comprises:—at least two particle deflectors (3, 3a, 3b, 3c),—a member (5) for collecting and storing the particles deflected by said deflector,—and means (6) for attaching said trapping device (2) to a part of the turbomachine.

6. 发明授权

US09982893B2 Combustor arrangement including flow control vanes 有权
公开(公告)号：US09982893B2
公开(公告)日：2018-05-29
申请号：US15506055
申请日：2014-09-05
申请人： Siemens Energy, Inc.
发明人： Jose L. Rodriguez , Matthew J. Golsen
IPC分类号： F23R3/04 , F23R3/42 , F23R3/54
CPC分类号： F23R3/425 , F23R3/04 , F23R3/54 , F23R2900/03043 , F23R2900/03045
摘要： A combustor assembly (17) including guide vanes (44) located between an inner cylinder (24) and a flow sleeve (25). Each guide vane (44) includes a circumferentially angled flow directing portion (60) adjacent to a leading edge (46). The leading edge (46) of at least one guide vane (44) can be located radially inward along the longitudinal axis (54) relative to the leading edge (46) of at least one other of the guide vanes (44). The length of the guide vanes (44) may vary, and the circumferential spacing between a first pair of the guide vanes (44) can be different from a spacing between a second pair of the guide vanes (44).

7. 发明授权

US09982890B2 Combustor dome heat shield 有权
公开(公告)号：US09982890B2
公开(公告)日：2018-05-29
申请号：US14085011
申请日：2013-11-20
申请人： Pratt & Whitney Canada Corp.
发明人： Michael Papple , Robert Sze , Sri Sreekanth
IPC分类号： F23R3/16 , F23R3/00 , F01D5/18 , F23R3/54 , F23R3/60 , F23R3/50 , F23R3/28 , F23R3/36 , F23R3/04 , F23R3/20 , F23R3/14 , F23R3/06
CPC分类号： F23R3/16 , F01D5/186 , F01D5/187 , F23R3/002 , F23R3/005 , F23R3/007 , F23R3/04 , F23R3/045 , F23R3/06 , F23R3/14 , F23R3/20 , F23R3/28 , F23R3/283 , F23R3/36 , F23R3/50 , F23R3/54 , F23R3/60 , F23R2900/00001 , F23R2900/00005 , F23R2900/00012 , F23R2900/00017 , F23R2900/00018 , F23R2900/00019 , F23R2900/03042 , F23R2900/03044 , F23R2900/03045 , Y02T50/675
摘要： A combustor heat shield has lips with fins distributed on the lips. The lip-fins have an extended end portion projecting rearwardly from the back face of the heat shield. Impingement jets may be directed against the rearwardly extended end portions of the lip-fins to enhance cooling. The heat shield may define a fuel nozzle opening surrounded by a rail on the back side of the heat shield. Impingement holes or slots may be defined in the rail for allowing cooling air passing therethrough to impinge upon the lip-fins.

8. 发明授权

US09933164B2 Annular turbomachine combustion chamber 有权
公开(公告)号：US09933164B2
公开(公告)日：2018-04-03
申请号：US15120015
申请日：2015-01-27
申请人： SAFRAN HELICOPTER ENGINES
发明人： Nicolas Savary , Patrick Berteau , Bernard Carrere , Jean-Marc Dubourdieu , Ludovic Naudot
IPC分类号： F23R3/52 , F23R3/58 , F02C7/20 , F23R3/50 , F23R3/54 , F23R3/28 , F23R3/42 , F23R3/48 , F23C5/02 , F23R3/46 , F23R3/56 , F23R3/60 , F23D11/10 , F23R3/00
CPC分类号： F23R3/52 , F02C7/20 , F05D2230/50 , F05D2230/51 , F05D2230/64 , F05D2230/642 , F05D2240/35 , F05D2240/90 , F05D2260/30 , F23C5/02 , F23D11/103 , F23R3/002 , F23R3/007 , F23R3/28 , F23R3/283 , F23R3/42 , F23R3/425 , F23R3/46 , F23R3/48 , F23R3/50 , F23R3/54 , F23R3/56 , F23R3/58 , F23R3/60 , F23R2900/00005 , F23R2900/00017 , F23R2900/00018 , F23R2900/00019
摘要： An annular combustion chamber (10) for a turbomachine (100), the combustion chamber presenting an axial direction (X), a radial direction, and an azimuth direction, and comprising a first annular wall (12) and a second annular wall (14), each wall delimiting at least a portion of the volume of the annular combustion chamber (10), the first and second walls (12, 14) presenting complementary fitting elements (12d, 14d), the first wall (12) presenting at least one first through hole (12f), while the second wall (14) presents at least one second through hole (14f), the combustion chamber (10) also having at least one pin (18) engaged in a pair of holes comprising a first hole (12f) and a second hole (14f), said pin (18) locking the fitting of the first and second walls (12, 14).

9. 发明授权

US09423132B2 Ultra low emissions gas turbine combustor 有权
标题翻译：超低排放燃气轮机燃烧器
公开(公告)号：US09423132B2
公开(公告)日：2016-08-23
申请号：US12926322
申请日：2010-11-09
申请人： Axel Lars-Uno Eugen Axelsson , Martin Beran , Ekaterina Sinkevich
发明人： Axel Lars-Uno Eugen Axelsson , Martin Beran , Ekaterina Sinkevich
IPC分类号： F23R3/14 , F23R3/16 , F23R3/54 , F23R3/28
CPC分类号： F23R3/14 , F23D2900/14021 , F23R3/16 , F23R3/286 , F23R3/54 , F23R2900/03044
摘要： The gaseous fuel-fired can combustor for a gas turbine include a generally cylindrical housing, and a generally cylindrical liner disposed coaxially within the housing to define with the housing a radial outer flow passage for combustion air, the-liner also defining inner combustion and a dilution zone, the dilution zone being axially distant a closed housing end relative to the combustion zone. A fuel/air mixing apparatus disposed at the closed housing end includes a plurality of swirl vanes defining passages each having constant cross-section flow areas along the vanes, and an increasing aspect ratio from the passage inlet to the outlet. An impingement cooling sleeve coaxially disposed in the combustion air passage between the housing and the liner cools the portion of the liner defining the combustion zone. Channeling apparatus is disposed between a downstream end region of the sleeve and the mixing apparatus and includes a diffuser section with a ratio of the outlet flow area to the inlet flow area in a range of 1.3-1.5.
摘要翻译：用于燃气轮机的气体燃料燃烧罐式燃烧器包括大致圆柱形的壳体以及同轴地设置在壳体内的大致圆柱形的衬套，以与壳体一起限定用于燃烧空气的径向外部流动通道，衬套还限定内部燃烧和稀释区域相对于燃烧区域轴向地远离封闭的壳体端部。设置在封闭的壳体端部处的燃料/空气混合设备包括多个涡流叶片，其限定通道，每个叶片具有沿着叶片的恒定横截面流动面积，以及从通道入口到出口的增加的纵横比。同轴地设置在壳体和衬套之间的燃烧空气通道中的冲击冷却套筒冷却限定燃烧区域的衬套的部分。引导装置设置在套筒的下游端区域和混合装置之间，并且包括具有在1.3-1.5范围内的出口流动面积与入口流动面积的比率的扩散器部分。

10. 发明授权

US09322557B2 Combustor and method for distributing fuel in the combustor 有权
标题翻译：用于在燃烧器中分配燃料的燃烧器和方法
公开(公告)号：US09322557B2
公开(公告)日：2016-04-26
申请号：US13343926
申请日：2012-01-05
申请人： Jong Ho Uhm , Willy Steve Ziminsky , Thomas Edward Johnson , William David York
发明人： Jong Ho Uhm , Willy Steve Ziminsky , Thomas Edward Johnson , William David York
IPC分类号： F02C7/22 , F23R3/54 , F23R3/28 , F23R3/04
CPC分类号： F23R3/283 , F23D2209/10 , F23D2209/20 , F23R3/286 , F23R2900/03044
摘要： A combustor includes a tube bundle that extends radially across at least a portion of the combustor. The tube bundle includes an upstream surface axially separated from a downstream surface. A plurality of tubes extends from the upstream surface through the downstream surface, and each tube provides fluid communication through the tube bundle. A baffle extends axially inside the tube bundle between adjacent tubes. A method for distributing fuel in a combustor includes flowing a fuel into a fuel plenum defined at least in part by an upstream surface, a downstream surface, a shroud, and a plurality of tubes that extend from the upstream surface to the downstream surface. The method further includes impinging the fuel against a baffle that extends axially inside the fuel plenum between adjacent tubes.
摘要翻译：燃烧器包括径向延伸穿过燃烧器的至少一部分的管束。管束包括从下游表面轴向分离的上游表面。多个管从上游表面延伸穿过下游表面，并且每个管提供通过管束的流体连通。挡板在相邻管之间的管束内部轴向延伸。用于在燃烧器中分配燃料的方法包括使燃料流入至少部分地由上游表面，下游表面，护罩和从上游表面延伸到下游表面的多个管所限定的燃料增压室。该方法还包括将燃料撞击在相邻管之间的燃料增压室内轴向延伸的挡板。

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