公开(公告)号：US06837683B2

公开(公告)日：2005-01-04

申请号：US10291408

申请日：2002-11-12

Applicant: Geoffrey M Dailey

Inventor： Geoffrey M Dailey

IPC: F01D5/18 ,  F01D5/08

CPC classification number: F01D5/187 ,  F05D2260/201 ,  F05D2260/202

Abstract: A gas turbine engine blade or vane comprises inner linked chambers. A chamber adjacent the leading edge is provided with an inlet for receiving cooling fluid and a chamber adjacent the trailing edge is provided with an outlet for exhausting cooling fluid. The chambers are arranged in series from the leading edge to the trailing edge so as to direct cooling fluid within the aerofoil blade or vane from the leading edge region to the trailing edge region.

Abstract translation: 燃气涡轮发动机叶片或叶片包括内连接室。 邻近前缘的腔室设置有用于接收冷却流体的入口，并且与后缘相邻的腔室设置有用于排出冷却流体的出口。 这些室从前缘到后缘串联布置，以便将机翼叶片或叶片内的冷却流体从前缘区域引导到后缘区域。

公开(公告)号：US06334297B1

公开(公告)日：2002-01-01

申请号：US09624331

申请日：2000-07-24

Applicant: Geoffrey M Dailey ,  Anthony Pidcock ,  Desmond Close

Inventor： Geoffrey M Dailey ,  Anthony Pidcock ,  Desmond Close

IPC: F02C718

CPC classification number: F23R3/04 ,  F23R3/346 ,  F23R2900/03041 ,  Y02T50/675

Abstract: A combustor arrangement (8) for a gas turbine engine (3) comprising a combustion chamber, fuel nozzles(52a,52b), and a bled diffuser (7) located upstream of said combustion chamber to, in use, direct an airflow from an upstream compressor (6) into the combustor (8). The fuel nozzles (52a,52b) arranged in use to supply fuel into the combustion chamber where it is mixed and combusted with the airflow from the compressor (6). The bled diffuser (7) adapted to bleed off a portion of said airflow from a main airflow into the combustion chamber. At least one bleed duct (46) is connected to the bled diffuser (7) to return and direct the air bled from the diffuser (7) to a main gas flow through the engine (3) at a location downstream of the fuel supply means (52a,52b). The bled air from the diffuser (7) preferably providing cooling of a part of the gas turbine engine (3), for example part of the turbine (10) or combustor outlet vane (58), downstream of the combustor (8).

Abstract translation: 一种用于燃气涡轮发动机（3）的燃烧器装置（8），其包括燃烧室，燃料喷嘴（52a，52b）和位于所述燃烧室上游的流体扩散器（7），在使用中，引导来自 上游压缩机（6）进入燃烧器（8）。 燃料喷嘴（52a，52b），其布置成用于将燃料供应到燃烧室中，在该燃烧室中与来自压缩机（6）的气流混合并燃烧。 流血扩散器（7）适于将一部分所述气流从主气流排出到燃烧室中。 至少一个排放管道（46）连接到排放的扩散器（7），以在燃料供应装置的下游位置返回并引导从扩散器（7）排出的空气通过发动机（3）的主气体流 （52a，52b）。 来自扩散器（7）的排出的空气优选地提供燃气涡轮发动机（3）的一部分的冷却，例如在燃烧器（8）下游的涡轮机（10）或燃烧器出口叶片（58）的一部分。

公开(公告)号：US06264428B1

公开(公告)日：2001-07-24

申请号：US09480691

申请日：2000-01-11

Applicant: Geoffrey M Dailey ,  Peter A Evans ,  Richard A B McCall

Inventor： Geoffrey M Dailey ,  Peter A Evans ,  Richard A B McCall

IPC: F01D518

CPC classification number: F01D5/187 ,  Y02T50/673 ,  Y02T50/676

Abstract: A hollow cooled aerofoil blade (10) is provided with a central, lengthways extending plenum (16) and has pressure and suction flanks (20,15). The suction flank (15) has lengthways extending passages (21) therein that direct cooling air from the root region (13) into the central plenum (16). From the central plenum, the cooling air flows through a first set of apertures (27) into lengthways extending passages (28) in the pressure flank (20). The cooling air then flows through a second set of apertures (30) in the pressure flank to provide film cooling of the pressure flank (20) external surface.

Abstract translation: 中空的冷却机翼叶片（10）设置有中心的纵向延伸的气室（16）并具有压力和吸力侧面（20,15）。 吸力侧面（15）在其中具有纵向延伸的通道（21），其将冷却空气从根部区域（13）引导到中央增压室（16）中。 冷却空气从中央集气室经过第一组孔（27）流入压力侧面（20）中的纵向延伸通道（28）。 冷却空气然后流过压力侧面中的第二组孔（30），以提供压力侧面（20）外表面的膜冷却。

公开(公告)号：US07458766B2

公开(公告)日：2008-12-02

申请号：US11252714

申请日：2005-10-19

Applicant: Geoffrey M Dailey ,  Guy D Snowsill

Inventor： Geoffrey M Dailey ,  Guy D Snowsill

IPC: F03B11/00

CPC classification number: F01D15/08 ,  F01D5/082 ,  F01D5/087

Abstract: Efficient cooling of a stage of gas turbine engine turbine blades (36) is achieved by first reducing the pressure of the cooling air after it has been bled from the annulus of the compressor (12) by passing it through a diffuser (30), to a pressure magnitude lower than is required at entry to the turbine blades, then re-pressurizing the bled air up to the required entry pressure, by passing it through a radial compressor defined by a cowl (44) positioned in close spaced, co-rotational relationship with the downstream face of the associated turbine disk (34).

Abstract translation: 燃气涡轮发动机涡轮叶片（36）的阶段的有效冷却通过首先在冷却空气从压缩机（12）的环通过其通过扩散器（30）而被排出之后降低其压力 压力幅度低于进入涡轮机叶片所需的压力量级，然后通过使排气管通过由整流罩（44）限定的径向压缩机来重新加压出料空气直至所需的入口压力，该整流罩（44）以紧密间隔的共同旋转 与相关联的涡轮盘（34）的下游面的关系。

公开(公告)号：US06910855B2

公开(公告)日：2005-06-28

申请号：US09768591

申请日：2001-01-25

Applicant: Geoffrey M Dailey ,  Martin G Rose

Inventor： Geoffrey M Dailey ,  Martin G Rose

IPC: F01D5/14 ,  F01D9/04 ,  F01D17/16 ,  F02C9/22

CPC classification number: F01D17/167 ,  F01D5/146 ,  F01D9/041 ,  F02C9/22 ,  Y02T50/673

Abstract: Rotary apparatus (17) for a gas turbine engine (10) comprises a rotor assembly (63) and first and second stator assemblies (55, 59) mounted coaxially with respect to each other. Each vane (58, 62) has a leading edge and a trailing edge. The stator assemblies (55, 59) are circumferentially translatable relative to each other between a first condition in which each of the vanes (62) of the second stator assembly (59) is substantially aerodynamically aligned with a respective one of the vanes (58) of the first stator assembly (55), and a second condition in which the vanes (58, 62) of the first and second stator assemblies (55, 59) are out of aerodynamic alignment with each other. In the first condition, at least a part of each vane (62) of the second stator assembly (59) extends beyond the trailing edge of the respective vane (58) of the first stator assembly (55).

Abstract translation: 用于燃气涡轮发动机（10）的旋转装置（17）包括转子组件（63）和相对于彼此同轴安装的第一和第二定子组件（55,59）。 每个叶片（58,62）具有前缘和后缘。 定子组件（55,59）在其中第二定子组件（59）的每个叶片（62）与相应的一个叶片（58）基本上空气动力学对准的第一状态之间相对于彼此沿周向平移， 和第一和第二定子组件（55,59）的叶片（58,62）彼此脱离气动对准的第二状态。 在第一条件下，第二定子组件（59）的每个叶片（62）的至少一部分延伸超过第一定子组件（55）的相应叶片（58）的后缘。

公开(公告)号：US08973371B2

公开(公告)日：2015-03-10

申请号：US13224894

申请日：2011-09-02

Applicant: Jonathan M King ,  Crispin D. Bolgar ,  Guy D. Snowsill ,  Michael J. Sheath ,  Geoffrey M Dailey

Inventor： Jonathan M King ,  Crispin D. Bolgar ,  Guy D. Snowsill ,  Michael J. Sheath ,  Geoffrey M Dailey

IPC: F02C6/08 ,  F02C3/13 ,  F02C7/18 ,  F01D5/08 ,  F01D11/00 ,  F01D11/04 ,  F01D11/06

CPC classification number: F02C6/08 ,  F01D5/081 ,  F01D5/082 ,  F01D11/001 ,  F01D11/04 ,  F01D11/06 ,  F02C3/13 ,  F02C7/18

Abstract: A gas turbine engine comprising a turbine section cooling system and a method of cooling a turbine section of a gas turbine engine is provided. The gas turbine engine comprises in flow series a compressor section, a combustor, and a turbine section, the engine further comprising a turbine section cooling system. The turbine section cooling system including a first compressed air bleed arrangement and a second compressed air bleed arrangement. The first compressed air bleed arrangement bleeds a first flow of compressed air from a high pressure stage of the compressor section. The first flow of compressed air bypasses the combustor and arrives at the turbine section to form a sealing and/or cooling flow at a row of stator vanes upstream of an adjacent rotor disc. The second compressed air bleed arrangement bleeds a second flow of compressed air from one or more lower pressure stages of the compressor section. The second flow of compressed air bypasses the combustor and arrives at the turbine section to form a cooling flow. A first portion of the cooling flow is routed to a front face of the rotor disc and a second portion of the cooling flow is routed to a rear face of the rotor disc.

Abstract translation: 提供一种燃气涡轮发动机，其包括涡轮部分冷却系统和冷却燃气涡轮发动机的涡轮部分的方法。 燃气涡轮发动机包括流动系列，压缩机部分，燃烧器和涡轮部分，发动机还包括涡轮部分冷却系统。 涡轮部分冷却系统包括第一压缩空气排放装置和第二压缩空气排放装置。 第一压缩排气装置从压缩机部分的高压级排出第一流的压缩空气。 压缩空气的第一流动绕过燃烧器并到达涡轮部分，以在相邻转子盘的上游的一排定子叶片上形成密封和/或冷却流。 第二压缩空气排出装置从压缩机部分的一个或多个较低压力级渗出第二压缩空气流。 压缩空气的第二流动绕过燃烧器并到达涡轮部分以形成冷却流。 冷却流的第一部分被引导到转子盘的前表面，并且冷却流的第二部分被引导到转子盘的后表面。

公开(公告)号：US07234917B2

公开(公告)日：2007-06-26

申请号：US11041269

申请日：2005-01-25

Applicant: Geoffrey M Dailey ,  Martin G Rose

Inventor： Geoffrey M Dailey ,  Martin G Rose

IPC: F01D17/16

CPC classification number: F01D17/167 ,  F01D5/146 ,  F01D9/041 ,  F02C9/22 ,  Y02T50/673

Abstract: Rotary apparatus for a gas turbine engine comprises a rotor assembly and first and second stator assemblies mounted coaxially with respect to each other. The first stator assembly is upstream of the second stator assembly, and the second stator assembly is upstream of the rotor assembly. The rotor assembly comprises an annular array of rotor blades, and each stator assembly comprises an annular array of stator vanes. Each vane has a leading edge and a trailing edge. The stator assemblies are circumferentially translatable relative to each other between a first condition and a second condition. In the first condition, at least a part of each vane of the second stator assembly extends beyond the trailing edge of the respective vane of the first stator assembly.

Abstract translation: 用于燃气涡轮发动机的旋转装置包括转子组件和相对于彼此同轴安装的第一和第二定子组件。 第一定子组件在第二定子组件的上游，并且第二定子组件位于转子组件的上游。 转子组件包括转子叶片的环形阵列，并且每个定子组件包括定子叶片的环形阵列。 每个叶片具有前缘和后缘。 定子组件在第一状态和第二状态之间相对于彼此可周向地平移。 在第一条件下，第二定子组件的每个叶片的至少一部分延伸超过第一定子组件的相应叶片的后缘。

公开(公告)号：US06544001B2

公开(公告)日：2003-04-08

申请号：US09944366

申请日：2001-09-04

Applicant: Geoffrey M Dailey

Inventor： Geoffrey M Dailey

IPC: F01D518

CPC classification number: F01D5/186 ,  B22C9/10 ,  F01D5/187

Abstract: A turbine blade for a gas turbine engine comprises an aerofoil having a suction and pressure side. The pressure side is provided with a reflex curvature at the aerofoil trailing edge region so as to reduce the thickness of the aerofoil in that region.

公开(公告)号：US06874992B2

公开(公告)日：2005-04-05

申请号：US10294666

申请日：2002-11-15

Applicant: Geoffrey M Dailey

Inventor： Geoffrey M Dailey

IPC: F01D5/18 ,  F01D5/08

CPC classification number: F01D5/187

Abstract: An aerofoil blade or vane for a gas turbine engine comprises a body member having an inner end for mounting the blade on a shaft and an outer or tip end. A plurality of cooling passages are formed within the blade, the cooling passages comprising a plurality of inlet passages along which cooling air flows from the base towards the tip region of the blade and a plurality of return passages along which cooling air flows from the tip towards the base region of the blade. At least some of the passages are connected by a common chamber located within the tip region of the blade.

Abstract translation: 用于燃气涡轮发动机的机翼叶片或叶片包括主体构件，其具有用于将叶片安装在轴上的内端和外端或尖端。 多个冷却通道形成在叶片内，冷却通道包括多个入口通道，冷却空气从基座朝向叶片的顶端区域流过冷却空气，多个返回通道沿着冷却空气从顶端流向 叶片的基部区域。 至少一些通道通过位于叶片的尖端区域内的公共室连接​​。

公开(公告)号：US06564557B1

公开(公告)日：2003-05-20

申请号：US09910060

申请日：2001-07-23

Applicant: Geoffrey M Dailey

Inventor： Geoffrey M Dailey

IPC: F02C712

CPC classification number: F01D25/12 ,  F02C7/18

Abstract: Cooling air enters a cooling path 56 from a supply at 58. The path follows a serpentine path consecutively through a number of components to be cooled, including guide vanes 38, 40, blades 30, a shroud 54 and a shaft 18. A valve 68 is provided at the downstream end of the path 56. The setting of the valve 56 modulates the flow and pressure of air along the path 56, without wholly preventing it.

Abstract translation: 冷却空气从58处的供应部分进入冷却路径56.路径沿着蛇形路径连续地穿过要冷却的多个部件，包括导向叶片38,40，叶片30，护罩54和轴18.阀68 设置在路径56的下游端。阀56的设定调节沿着路径56的空气的流量和压力，而不完全阻止它。