公开(公告)号：EP3279435A3

公开(公告)日：2018-05-16

申请号：EP17184335.2

申请日：2017-08-01

申请人： United Technologies Corporation

发明人： JOHNSON, Javier N. ,  BATES, Chris ,  BEACH, Eric ,  FARAH, Jorge I.

IPC分类号： F01D5/18 ,  F02K3/10 ,  F23R3/20

CPC分类号： F23R3/20 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/185 ,  F01D9/041 ,  F01D9/06 ,  F02K3/10 ,  F05D2220/32 ,  F05D2230/12 ,  F05D2230/20 ,  F05D2230/22 ,  F05D2230/31 ,  F05D2230/53 ,  F05D2240/12 ,  F05D2260/20 ,  F05D2260/232 ,  F05D2300/17 ,  F23R3/286

摘要： An aerospace component (102) includes a wall (122) with an integral longitudinal wall passage (120) formed therein, the integral longitudinal wall passage (120) including at least one entrance aperture (126) and at least one exit aperture (132), the exit aperture (132) transverse to the integral longitudinal wall passage (120). The aerospace component (102) may be additively manufactured.

公开(公告)号：EP2837883B1

公开(公告)日：2018-04-04

申请号：EP13180642.4

申请日：2013-08-16

申请人： Ansaldo Energia Switzerland AG

发明人： Gao, Xianfeng ,  Benz, Urs ,  Theuer, Andre ,  Kulkarni, Rohit

IPC分类号： F23C7/00 ,  F23R3/20 ,  F23R3/28 ,  F23R3/34

CPC分类号： F23R3/42 ,  F02C3/14 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/201 ,  F05D2260/232 ,  F23C7/004 ,  F23D2900/14004 ,  F23D2900/14021 ,  F23R3/20 ,  F23R3/28 ,  F23R3/286 ,  F23R3/346 ,  F23R3/36 ,  F23R3/46 ,  F23R2900/00014 ,  F23R2900/03041 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03341

摘要： Second stage can annular burner arrangement of a sequential gas turbine comprising: a combustion zone; a center body (101) burner, located upstream of the combustion zone, and having an annular duct with a mixing zone having a cross section area; intermediate lobes (102) which are arranged with respect to the center body (101) burner as bond-bridge in circumferential direction, perpendicular or quasi-perpendicular and in longitudinal or quasi-longitudinal direction to the main mass flow, and which are actively connected to the cross section area of the mixing zone. Cooling air (104) is guided through a number of pipes within the lobes (102) to the center body and cools beforehand at least the front section (201) of the center body (101) based on impingement cooling (203). Subsequently, the impingement cooling air cools the middle face (204) and back face (202) of the center body (101) based on convective and/or effusion cooling (205). At least the back face (202) of the center body includes on the inside at least one damper (300).

公开(公告)号：EP3246559A1

公开(公告)日：2017-11-22

申请号：EP17171460.3

申请日：2017-05-17

申请人： Airbus DS GmbH

发明人： Gotzig, Ulrich ,  Wurdak, Malte

IPC分类号： F02K9/64

CPC分类号： F02K9/64 ,  C25B1/04 ,  C25B15/08 ,  F02K9/425 ,  F02K9/44 ,  F02K9/95 ,  F05D2220/80 ,  F05D2240/35 ,  F05D2260/232 ,  Y02E60/366

摘要： Ein Raketenantriebssystem (10) umfasst eine Brennkammer (12), ein mit der Brennkammer (12) verbundenes Wasserstoff-Sauerstoff-Zufuhrsystem (14), das dazu eingerichtet ist, Wasserstoff und Sauerstoff in die Brennkammer (12) zu leiten, und ein mit der Brennkammer (12) verbundenes Kühlmittelzufuhrsystem (16), das dazu eingerichtet ist, ein brennbares Kühlmittel in die Brennkammer (12) zu leiten. Ein Zündsystem (18) des Raketenantriebssystems (10) ist dazu eingerichtet, eine Verbrennung des Wasserstoff-Sauerstoff-Kühlmittel-Gemischs in der Brennkammer (12) zu initiieren.

摘要翻译： 的火箭发动机系统（10）包括燃烧室（12），具有连接到其适于直接氢气和氧气进入所述燃烧室（12）中的氢 - 氧进料系统（14）的燃烧室（12），并与 燃烧室（12）连接的冷却剂供应系统（16）适于将可燃性冷却剂导入燃烧室（12）中。 火箭推进系统（10）的点火系统（18）构造成启动燃烧室（12）中的氢 - 氧 - 冷却剂混合物的燃烧。

公开(公告)号：EP3080400A4

公开(公告)日：2017-10-18

申请号：EP14869842

申请日：2014-12-02

申请人： UNITED TECHNOLOGIES CORP

发明人： ZELESKY MARK F ,  WINTER MICHAEL ,  CODERRE PAUL E ,  SYKES RICHARD L

IPC分类号： F01D5/08 ,  F01D5/34 ,  F02C7/16

CPC分类号： F01D5/088 ,  F01D5/181 ,  F01D5/34 ,  F02C3/04 ,  F02C7/16 ,  F05D2220/32 ,  F05D2240/81 ,  F05D2260/207 ,  F05D2260/208 ,  F05D2260/232 ,  Y02T50/676

摘要： A gas turbine engine rotor includes a rotor that provides a cooling cavity. The cooling cavity has a first chamber and a second chamber that are fluidly connected to one another by a passageway. At least one of the first and second rotor portions is configured to support a blade that is fluidly isolated from the cavity. A phase change material is arranged in the cavity. The phase change material is configured to be arranged in the first chamber in a first state and in the second chamber in the second state. The passageway is configured to carry the phase change material between the second and first chambers once changed between the first and second states.

公开(公告)号：EP3184747A1

公开(公告)日：2017-06-28

申请号：EP16203123.1

申请日：2016-12-09

申请人： General Electric Company

发明人： LACY, Benjamin Paul

IPC分类号： F01D9/02 ,  F02C3/16 ,  F01D5/14 ,  F23R3/20

CPC分类号： F01D25/12 ,  F01D5/185 ,  F01D9/023 ,  F01D9/041 ,  F01D9/065 ,  F02C3/04 ,  F02C3/14 ,  F02C7/222 ,  F02C7/224 ,  F05D2220/32 ,  F05D2240/123 ,  F05D2240/124 ,  F05D2240/35 ,  F05D2260/202 ,  F05D2260/232 ,  F05D2260/601 ,  F23R3/20 ,  F23R3/34

摘要： A gas turbine 12 that includes a row of circumferentially spaced stator blades 17 in a turbine. Each of the stator blades may include an airfoil 120 defined between a concave pressure side face 126 and a laterally opposed convex suction side face 127. At least one of the stator blades within the row may include a fuel injector 51 that includes: a transverse nozzle 119 extending through the airfoil between an inlet formed through the pressure side face and an outlet formed through the suction side face of the airfoil; and a fuel channel formed through the airfoil of the stator blade, the fuel channel having an upstream end, at which an inlet port fluidly connects the fuel channel to a fuel supply, and a downstream end, at which an outlet port fluidly connects the fuel channel to the transverse nozzle.

摘要翻译： 燃气涡轮机12包括涡轮机中的一排周向隔开的定子叶片17。 每个定子叶片可以包括限定在凹形压力侧面126和横向相对的凸形吸力侧面127之间的翼型件120.该排内的定子叶片中的至少一个可以包括燃料喷射器51，该燃料喷射器51包括：横向喷嘴 119在穿过压力侧面形成的入口和穿过翼型的吸力侧面形成的出口之间穿过翼型件延伸; 以及通过定子叶片的翼型形成的燃料通道，燃料通道具有上游端和下游端，在该上游端处，入口端口将燃料通道流体连接至燃料供应源，在该下游端处，出口端口流体连接燃料 通道到横向喷嘴。

公开(公告)号：EP3181820A1

公开(公告)日：2017-06-21

申请号：EP16202771.8

申请日：2016-12-07

申请人： United Technologies Corporation

发明人： SPANGLER, Brandon W. ,  KOHLI, Atul

IPC分类号： F01D5/18

CPC分类号： F01D5/188 ,  F01D9/02 ,  F01D11/08 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/126 ,  F05D2240/127 ,  F05D2240/35 ,  F05D2250/14 ,  F05D2250/25 ,  F05D2260/2212 ,  F05D2260/22141 ,  F05D2260/232 ,  F23R3/002 ,  F23R3/04

摘要： A component of a gas turbine engine, the component having: an internal cooling cavity extending through an interior of the component; a baffle insert (32) configured to be inserted into the internal cooling cavity; a plurality of trip strips (40) extending upwardly from an exterior surface of the baffle insert; and at least one rib extending upwardly from the exterior surface (38) of the baffle insert, wherein the plurality of trip strips and the at least one rib (42) are spaced from an interior surface of the internal cooling cavity.

摘要翻译： 燃气涡轮发动机的部件，所述部件具有：延伸穿过所述部件的内部的内部冷却腔; 挡板插入件（32），其构造成插入所述内部冷却腔中; 多个脱扣条（40），从挡板插入件的外表面向上延伸; 以及至少一个从挡板插件的外表面（38）向上延伸的肋，其中多个跳闸条和至少一个肋（42）与内部冷却腔的内表面间隔开。

公开(公告)号：EP3055534A4

公开(公告)日：2017-06-07

申请号：EP14852169

申请日：2014-05-23

申请人： UNITED TECHNOLOGIES CORP

发明人： ROBERTS LAWRENCE P

IPC分类号： F02C7/12 ,  F01D25/12 ,  F01D25/18 ,  F01P11/00 ,  F02C7/06

CPC分类号： F02C7/14 ,  F01D25/12 ,  F01D25/18 ,  F02C7/224 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2260/98 ,  Y02T50/675

摘要： A single, unitary thermal management system (TMS) manifold for a gas turbine engine is provided which comprises one or more interfaces for mounting various thermal management system components directly to the TMS manifold. The TMS manifold also defines fluid passages for transferring fuel, engine lubricant or generator oil from one component to another component. Packing numerous fuel system and lubricating system components within the TMS manifold reduces cost and weight and simplifies maintenance.

摘要翻译： 提供用于燃气涡轮发动机的单个单一热管理系统（TMS）歧管，其包括用于将各种热管理系统部件直接安装到TMS歧管的一个或多个接口。 TMS歧管还定义了用于将燃料，发动机润滑油或发电机油从一个组件传输到另一个组件的流体通道。 在TMS歧管内包装大量的燃油系统和润滑系统部件，降低了成本和重量，简化了维护。

公开(公告)号：EP3164577A1

公开(公告)日：2017-05-10

申请号：EP15738213.6

申请日：2015-06-30

申请人： General Electric Company

发明人： LEAMY, Kevin Richard ,  BREIG, Benjamin Paul ,  EPSTEIN, Michael Jay ,  PARRILIA, Javier Armando ,  HURT, Matthew John ,  BRINSON, Thomas Edward ,  FLEMING, Andrew James ,  WILMOT, George Eugene

IPC分类号： F01D13/02 ,  B64D13/00 ,  B64D13/06 ,  F01D17/08 ,  F01D17/10 ,  F01D25/12 ,  F02C6/08 ,  F02C7/18

CPC分类号： B64D13/08 ,  B64D13/006 ,  B64D13/06 ,  B64D2013/0618 ,  B64D2013/0648 ,  B64D2013/0688 ,  F01D13/02 ,  F01D17/08 ,  F01D17/10 ,  F01D17/14 ,  F01D25/12 ,  F02C6/08 ,  F02C7/185 ,  F02C7/32 ,  F02C9/18 ,  F05D2220/3216 ,  F05D2220/323 ,  F05D2260/211 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2260/606 ,  F05D2270/301 ,  F05D2270/303 ,  Y02T50/56 ,  Y02T50/675 ,  Y02T50/676

摘要： Airplanes and jet engines are provided that includes an engine compressor; a combustor in flow communication with the engine compressor; an engine turbine in flow communication with the combustor to receive combustion products from the combustor; and a bleed air cooling system in fluid communication with bleed air from the engine compressor. The bleed air cooling system can include a first precooler in fluid communication with the bleed air from the engine compressor; a cooling system turbine in fluid communication with and downstream from the first precooler; and a discharge conduit from the cooling system turbine that is configured to be in fluid communication with at least one of an aircraft thermal management system and an aircraft environmental control system. Methods are also described for providing cooling fluid from a jet engine.

摘要翻译： 提供的飞机和喷气发动机包括发动机压缩机; 与发动机压缩机流体连通的燃烧器; 与所述燃烧器流体连通以接收来自所述燃烧器的燃烧产物的发动机涡轮; 以及与来自发动机压缩机的排气流体连通的排气冷却系统。 排气冷却系统可以包括与来自发动机压缩机的排气流体连通的第一预冷器; 与所述第一预冷器流体连通且在所述第一预冷器下游的冷却系统涡轮; 以及来自冷却系统涡轮机的排放管道，其被配置为与飞机热管理系统和飞机环境控制系统中的至少一个流体连通。 还描述了用于从喷气发动机提供冷却流体的方法。

公开(公告)号：EP2426314A3

公开(公告)日：2017-04-05

申请号：EP10157027.3

申请日：2010-03-19

申请人： General Electric Company

发明人： Davis, Lewis Berkley, Jr. ,  Garcia-Crespo, Andres ,  Gilchrist, III, George M. ,  Toprani, Amit S.

IPC分类号： F01D5/08 ,  F01D25/12 ,  F02C3/34 ,  F02C7/18

CPC分类号： F01D25/12 ,  F01D5/081 ,  F02C1/08 ,  F02C3/34 ,  F02C6/18 ,  F02C7/18 ,  F05D2260/232

摘要： A turbine power generation system with enhanced cooling provided by a stream of carbon dioxide (46) from a carbon dioxide source (44) and a method of using a stream of carbon dioxide (46) to cool hot gas path components. The turbine power generating system includes a compressor (12), a combustor (66), a turbine (14), a generator (16), and at least one shaft (20) linking the compressor (12) and turbine (14) and generator (16) together such that mechanical energy produced from the turbine (14) is used to drive the compressor (12) and the generator (16). Carbon dioxide that is sequestered from the exhaust (26) of the turbine (14) may be stored and injected back into the turbine to cool hot gas path components of the turbine (14).

公开(公告)号：EP2546472B1

公开(公告)日：2017-01-04

申请号：EP12162781.4

申请日：2012-03-30

申请人： United Technologies Corporation

发明人： Murphy, Michael J.

IPC分类号： F02C7/14 ,  F02C7/18 ,  F01D17/08 ,  F01D25/12 ,  F01D17/14

CPC分类号： F02C7/14 ,  F01D17/085 ,  F01D17/148 ,  F01D25/12 ,  F02C7/185 ,  F02C9/18 ,  F02K3/075 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2270/303 ,  Y02T50/675

摘要： A thermal management system (68) for a gas turbine engine (20) includes a first heat exchanger (HX1) and a second heat exchanger (HX2) in communication with a bypass flow through an inlet (70). A valve (72) is operable to selectively communicate the bypass flow to either the first heat exchanger or the second heat exchanger through the inlet.