公开(公告)号：US20160108818A1

公开(公告)日：2016-04-21

申请号：US14876550

申请日：2015-10-06

Applicant: ROLLS-ROYCE PLC

Inventor： Paul FLETCHER ,  John Richard WEBSTER ,  Anthony John MORAN

IPC: F02C7/22 ,  F01D25/18 ,  G06F17/50 ,  F23R3/28 ,  F16L9/127 ,  F02C7/04 ,  F01D25/04

CPC classification number: F02C7/222 ,  F01D25/04 ,  F05D2240/35 ,  F05D2260/96 ,  F05D2260/98 ,  F05D2300/174 ,  F05D2300/175 ,  F05D2300/501 ,  F16L9/02 ,  Y02T50/671

Abstract: A fluid conduit for a gas turbine engine. The conduit includes a superelastic material such as TNTZ or Ti2448. The conduit is installed such that at least part of the conduit is subject to a stress which lies in one of a superelastic and a plastic region of the material in use.

Abstract translation: 用于燃气涡轮发动机的流体导管。 导管包括超弹性材料，例如TNTZ或Ti2448。 导管被安装成使得导管的至少一部分受到位于使用中的材料的超弹性和塑性区域之一的应力。

公开(公告)号：US20160053721A1

公开(公告)日：2016-02-25

申请号：US14815115

申请日：2015-07-31

Applicant: ROLLS-ROYCE PLC

Inventor： Paul FLETCHER ,  Anthony John MORAN ,  Malcolm Laurence HILLEL ,  Philip Patrick WALSH

IPC: F02K3/02 ,  F02K3/04 ,  F01D17/16 ,  F02K3/115

CPC classification number: F02C9/18 ,  F02C9/54

Abstract: A gas turbine engine (20) comprising a variable geometry engine compressor (24), a variable geometry engine turbine (30) coupled to the engine compressor (24) and a combustor (28). The combustor (28) has an inlet (34) arranged to receive air from a first engine compressor outlet (34), and an outlet arranged to deliver combustion products to the engine turbine (30); a combustor bypass passage (50) having an inlet (53) arranged to receive air from a second engine compressor outlet (53), and an outlet (54) in fluid communication with a main fluid flow path downstream of a combustion zone (46, 48) of the combustor (28), and upstream of a turbine inlet (31); wherein the combustor bypass passage (50) comprises a bypass control valve (52) configured to selectively modulate the ratio of air flowing to the combustor inlet (34) to air flowing through the bypass passage (50).

Abstract translation: 一种燃气涡轮发动机（20），包括可变几何发动机压缩机（24），耦合到发动机压缩机（24）的可变几何发动机涡轮机（30）和燃烧器（28）。 燃烧器（28）具有设置成从第一发动机压缩机出口（34）接收空气的入口（34）和布置成将燃烧产物输送到发动机涡轮机（30）的出口; 具有布置成从第二发动机压缩机出口（53）接收空气的入口（53）的燃烧器旁路通道（50）和与燃烧区（46,46）下游的主流体流动路径流体连通的出口（54） （28）的上游和涡轮机入口（31）的上游; 其中所述燃烧器旁路通道（50）包括旁通控制阀（52），所述旁路控制阀（52）构造成选择性地调节流过所述燃烧器入口（34）的空气与流过所述旁路通道（50）的空气的比例。

公开(公告)号：US20150082798A1

公开(公告)日：2015-03-26

申请号：US14470325

申请日：2014-08-27

Applicant: ROLLS-ROYCE PLC

Inventor： Paul Allan HUCKER ,  Alan Philip GEARY ,  Anthony John MORAN ,  Jonathan Mark GREGORY

IPC: F23R3/00 ,  F01D25/14

CPC classification number: F23R3/002 ,  F01D25/145 ,  F16B33/002 ,  F16B37/048 ,  F16B41/002 ,  F23R3/007 ,  F23R3/60 ,  F23R2900/00017 ,  F23R2900/00018 ,  F23R2900/00019 ,  F23R2900/03041 ,  F23R2900/03044

Abstract: A tile for attaching to a wall of a gas turbine engine. The tile has a main body. The tile also has a bridging structure that projects outwardly from the main body and has a hole configured to receive an elongate fastener so that the tile can be attached to the wall of the gas turbine engine by passing the elongate fastener through a hole in the wall of the gas turbine engine and the hole in the bridging structure.

Abstract translation: 用于附接到燃气涡轮发动机的壁的瓦片。 瓷砖有一个主体。 瓦片还具有从主体向外突出的桥接结构，并且具有构造成接收细长紧固件的孔，使得瓦可以通过使细长紧​​固件穿过壁中的孔而附接到燃气涡轮发动机的壁 的燃气涡轮发动机和桥接结构中的孔。

公开(公告)号：US20150021117A1

公开(公告)日：2015-01-22

申请号：US14314821

申请日：2014-06-25

Applicant: ROLLS-ROYCE PLC

Inventor： Jochen RUPP ,  Anthony John MORAN

IPC: F02K1/34

CPC classification number: F02K1/34 ,  F23R3/002 ,  F23R2900/00014

Abstract: A duct and a method for damping pressure waves caused b thermoacoustic instability, the duct comprising: a locking Helmholtz resonator positioned on the circumference of the duct, the locking Helmholtz resonator tuned to a first frequency, and one or more damping Helmholtz resonators positioned on the circumference of the duct at or adjacent to 90 and/or 270 degrees from the locking Helmholtz resonator, wherein the damping Helmholtz resonators are tuned to a second frequency which is different from the first frequency of the locking Helmholtz resonator.

Abstract translation: 用于阻尼压力波的管道和方法引起热声不稳定性，该管道包括：位于管道圆周上的锁定亥姆霍兹共振器，调谐到第一频率的锁定亥姆霍兹共振器和位于 管道的90度和/或270度与锁定亥姆霍兹共振器相邻，其中阻尼亥姆霍兹共振器被调谐到与锁定亥姆霍兹共振器的第一频率不同的第二频率。

公开(公告)号：US20220099025A1

公开(公告)日：2022-03-31

申请号：US17476174

申请日：2021-09-15

Applicant: ROLLS-ROYCE plc

Inventor： Jonathan F. CARROTTE ,  Anthony John MORAN ,  Mark BREND ,  Mark CASSELL ,  Maxwell WILLIAMS

IPC: F02C7/22 ,  F02C7/04 ,  F23R3/04

Abstract: A direct injection fuel system is shown for injecting hydrogen fuel into a gas turbine combustor. The fuel injection system includes a plurality of fuel injector blocks. Each fuel injector block includes a fuel admission duct having an inlet for receiving hydrogen fuel from a fuel supply, an outlet for delivering hydrogen fuel into the combustor and a central axis extending from said inlet to said outlet. Each fuel injector block also includes an air admission duct located around the periphery of the fuel admission duct, having an inlet for receiving air from a diffuser and an outlet for delivering air into the combustor for mixing with the hydrogen fuel.

公开(公告)号：US20140157781A1

公开(公告)日：2014-06-12

申请号：US14090755

申请日：2013-11-26

Applicant: Rolls-Royce PLC

Inventor： Anthony John MORAN ,  Christopher Luke FORD ,  Jonathan Frederick CARROTTE ,  Alastair Duncan WALKER

IPC: F23R3/02

CPC classification number: F23D11/383 ,  F05D2250/14 ,  F05D2250/141 ,  F23D2900/11101 ,  F23D2900/11403 ,  F23R3/02 ,  F23R3/14 ,  F23R3/16 ,  F23R3/286 ,  F23R3/343

Abstract: A gas turbine engine lean burn fuel injector includes a fuel injector head which has a first air swirler, a second air swirler arranged around the first air swirler, a pilot fuel injector arranged radially between the first air swirler and the second air swirler. A third air swirler arranged around the second air swirler, a fourth air swirler arranged around the third air swirler and a main fuel injector arranged radially between the third air swirler and the fourth air swirler. A shroud is arranged around the fourth air swirler. A downstream end of the shroud is generally circular in cross-section in a plane perpendicular to the axis (Y) of the fuel injector head and an upstream end of the shroud is generally elliptical in cross-section in a plane perpendicular to the axis (Y) of the fuel injector head.

Abstract translation: 燃气涡轮发动机贫燃燃料喷射器包括燃料喷射器头，其具有第一空气旋流器，布置在第一空气旋流器周围的第二空气旋流器，在第一空气旋流器和第二空气旋流器之间径向布置的引燃燃料喷射器。 围绕第二空气旋流器布置的第三空气旋流器，围绕第三空气旋流器布置的第四空气旋流器和在第三空气旋流器和第四空气旋流器之间径向布置的主燃料喷射器。 围绕第四个空气旋流器布置一个护罩。 护罩的下游端在垂直于燃料喷射器头部的轴线（Y）的平面中具有大致圆形的横截面，并且护罩的上游端在垂直于轴线的平面中的横截面为大致椭圆形（ Y）。

公开(公告)号：US20140090395A1

公开(公告)日：2014-04-03

申请号：US14033878

申请日：2013-09-23

Applicant: ROLLS-ROYCE PLC

Inventor： Ajith APPUKUTTAN ,  Andrew Martin ROLT ,  Anthony John MORAN

IPC: F02C7/141

CPC classification number: F02C7/141 ,  F02C7/185 ,  F02C7/224 ,  F05D2260/213 ,  F05D2270/303 ,  Y02T50/671 ,  Y02T50/675 ,  Y02T50/676

Abstract: A cooling system for a gas turbine engine (10). The system is comprises a fuel air heat exchanger (78) comprising a fuel passage (80) in thermal contact with an engine cooling air passage (82). The system further comprises a fuel deoxygenator (72) located upstream of the fuel air heat exchanger (78) configured to deliver deoxygenated fuel to the fuel air heat exchanger fuel passage (80). The system includes a valve (84) configured to moderate engine cooling air flow to the engine cooling air passage (82).

Abstract translation: 一种用于燃气涡轮发动机（10）的冷却系统。 该系统包括燃料空气热交换器（78），其包括与发动机冷却空气通道（82）热接触的燃料通道（80）。 该系统还包括位于燃料空气热交换器（78）上游的燃料脱氧器（72），其构造成将脱氧燃料输送到燃料空气热交换器燃料通道（80）。 该系统包括构造成调节发动机冷却空气流到发动机冷却空气通道（82）的阀（84）。