公开(公告)号：US20160003144A1

公开(公告)日：2016-01-07

申请号：US14737633

申请日：2015-06-12

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis

IPC: F02C6/02 ,  F02C7/36 ,  F02C7/10 ,  F02K1/06 ,  F02C7/32 ,  F02C6/18 ,  F02C3/14

CPC classification number: F02C6/02 ,  B64C27/14 ,  B64D35/08 ,  F01D13/003 ,  F01D15/12 ,  F02C3/145 ,  F02C6/18 ,  F02C7/10 ,  F02C7/32 ,  F02C7/36 ,  F05D2220/329 ,  F05D2260/40311 ,  F05D2260/532

Abstract: A drive architecture comprises a rotor and a gearbox for driving the rotor. A pair of input gears provides rotational drive to the gearbox. A first recuperative cycle engine drives one of the pair of gears and a second engine drives the other of the pair of gears. The first recuperative cycle engine and the second engine are both gas turbine engines. A power takeoff from a drive shaft of the second engine supplies rotational drive to drive at least one component in the first recuperative cycle drive.

Abstract translation: 驱动架构包括用于驱动转子的转子和齿轮箱。 一对输入齿轮为齿轮箱提供旋转驱动。 第一恢复循环发动机驱动该对齿轮中的一个，第二发动机驱动该对齿轮中的另一个。 第一台换热循环发动机和第二台发动机都是燃气涡轮发动机。 来自第二发动机的驱动轴的动力输出提供旋转驱动以在第一换热循环驱动器中驱动至少一个部件。

公开(公告)号：US20150354455A1

公开(公告)日：2015-12-10

申请号：US14729473

申请日：2015-06-03

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  James D. Hill

IPC: F02C7/18 ,  F02C3/14 ,  F02C7/28 ,  F02C3/04

CPC classification number: F01D5/088 ,  F01D5/08 ,  F01D5/081 ,  F01D5/082 ,  F01D5/084 ,  F01D5/085 ,  F01D5/087 ,  F01D11/00 ,  F01D11/001 ,  F01D11/02 ,  F01D25/12 ,  F02C3/04 ,  F02C3/14 ,  F02C7/12 ,  F02C7/18 ,  F02C7/28 ,  F05D2220/32 ,  F05D2260/231 ,  Y02T50/676

Abstract: A gas turbine engine includes a turbine section fluidly connected to a combustor by a primary flow path. The turbine section includes a first portion at a high pressure relative to a second portion. A thermally isolated cooling plenum is positioned radially inward of the primary flow path. The cooling plenum is defined by a forward wall, a shaft structure, an aft wall, and an inner diameter wall of the primary flow path. Air in the thermally isolated cooling plenum is thermally isolated from air in the primary flow path. At least one cooling air system is operable to provide cooling air to the thermally isolated cooling plenum.

Abstract translation: 燃气涡轮发动机包括通过主流路流体连接到燃烧器的涡轮部分。 涡轮部分包括相对于第二部分处于高压的第一部分。 热隔离的冷却增压室位于主流路径的径向内侧。 冷却气室由主流路的前壁，轴结构，后壁和内径壁限定。 热隔离冷却通风室中的空气与主流路中的空气热隔离。 至少一个冷却空气系统可操作以向热隔离的冷却通风室提供冷却空气。

公开(公告)号：US09163521B2

公开(公告)日：2015-10-20

申请号：US13542669

申请日：2012-07-06

Applicant: William Byron Roberts, II ,  Shawn P. Lawlor

Inventor： William Byron Roberts, II ,  Shawn P. Lawlor

IPC: F02C9/16 ,  F02C9/18 ,  F02C3/04 ,  F01D1/02 ,  F01D1/10 ,  F01D1/16 ,  F01D9/04 ,  F01D9/00 ,  F04D21/00 ,  F02C7/00 ,  F02C3/00 ,  F02C3/06 ,  F02C3/14

CPC classification number: F01D9/00 ,  F01D1/026 ,  F01D1/10 ,  F01D1/16 ,  F01D5/02 ,  F01D9/047 ,  F02C3/00 ,  F02C3/04 ,  F02C3/06 ,  F02C3/14 ,  F02C7/00 ,  F02C7/22 ,  F02C9/16 ,  F02C9/18 ,  F04D21/00 ,  F05D2220/3216 ,  F05D2220/3218 ,  F05D2220/3219 ,  F05D2240/128 ,  F05D2240/30 ,  F05D2240/301 ,  F05D2240/302 ,  F05D2240/35 ,  Y02E20/14

Abstract: A gas turbine engine having a compressor section using blades on a rotor to deliver a gas at supersonic conditions to a stator. The stator includes one or more of aerodynamic ducts that have converging and diverging portions for deceleration of the gas to subsonic conditions and to deliver a high pressure gas to combustors. The aerodynamic ducts include structures for changing the effective contraction ratio to enable starting even when designed for high pressure ratios, and structures for boundary layer control. In an embodiment, aerodynamic ducts are provided having an aspect ratio of two to one (2:1) or more, when viewed in cross-section orthogonal to flow direction at an entrance to the aerodynamic duct.

Abstract translation: 一种具有压缩机部分的燃气涡轮发动机，该压缩机部分使用转子上的叶片将超声条件下的气体输送到定子。 定子包括一个或多个空气动力学管道，其具有用于将气体减速到亚音速条件并且将高压气体输送到燃烧器的会聚和发散部分。 空气动力学管道包括用于改变有效收缩比以便即使设计用于高压比也能起动的结构，以及用于边界层控制的结构。 在一个实施例中，当在与空气动力学管道的入口处垂直于流动方向的横截面中观察时，提供具有两比一（2:1）或更大的纵横比的空气动力学管道。

公开(公告)号：US20150292402A1

公开(公告)日：2015-10-15

申请号：US14658606

申请日：2015-03-16

Applicant: ROLLS-ROYCE PLC

Inventor： Ahmad RAZAK

IPC: F02C3/14 ,  F02C7/12 ,  F02C3/06

CPC classification number: F02C3/14 ,  F02C3/064 ,  F02C6/003 ,  F02C7/12 ,  F02C9/28 ,  F02K3/06 ,  F02K3/08 ,  F05D2220/323 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2270/082 ,  F23R2900/03341 ,  Y02T50/671 ,  Y02T50/677

Abstract: A gas turbine engine. The engine includes a first compressor coupled to a first turbine by a first shaft, the first turbine having first and second turbine stages. A first combustor is provided downstream of the first compressor and upstream of the first stage of the first turbine. A second combustor is provided downstream of the first stage of the first turbine, and upstream of the second stage of the first turbine. A further turbine is provided downstream of the first turbine, and is coupled to a further compressor by a further shaft.

Abstract translation: 燃气涡轮发动机。 发动机包括通过第一轴联接到第一涡轮机的第一压缩机，第一涡轮机具有第一和第二涡轮级。 第一燃烧器设置在第一压缩机的下游和第一涡轮机的第一级的上游。 第二燃烧器设置在第一涡轮机的第一级的下游，以及第一涡轮机的第二级的上游。 另外的涡轮设置在第一涡轮机的下游，并且通过另一个轴联接到另一个压缩机。

公开(公告)号：US09151223B2

公开(公告)日：2015-10-06

申请号：US13704972

申请日：2011-06-15

Applicant: Dimitrie Negulescu

Inventor： Dimitrie Negulescu

IPC: F02C3/06 ,  F02C3/14 ,  F23R3/16 ,  F23R3/50 ,  F23R3/58 ,  F01D9/04

CPC classification number: F02C3/06 ,  F01D9/041 ,  F02C3/14 ,  F05D2240/129 ,  F05D2250/314 ,  F23R3/04 ,  F23R3/16 ,  F23R3/50 ,  F23R3/58 ,  Y02T50/671 ,  Y02T50/675

Abstract: A gas-turbine combustion chamber arrangement includes a flame tube, a diffuser element arranged upstream of the flame tube in the flow direction, the diffuser element including an annular duct, and an axial compressor arranged upstream of the diffuser element. The diffuser element features an annular guide vane area in which guide vanes are arranged, which for redirecting an incoming flow are provided at an angle (α) in a range between 28° and 32° relative to a central axis of the gas turbine. Downstream of the guide vane area, a diffuser area is arranged, the diffuser area not being provided with flow-guiding elements affecting the flow, where burners arranged in the annular combustion chamber are provided with their burner axes at an angle (β) between 40° and 50° relative to the central axis.

Abstract translation: 燃气轮机燃烧室装置包括火焰管，在流动方向上布置在火焰管的上游的扩散器元件，扩散器元件包括环形管道，以及布置在扩散器元件上游的轴向压缩机。 扩散器元件具有环形引导叶片区域，在该环形引导叶片区域中布置导向叶片，用于重定向流入流体的角度（α）相对于燃气轮机的中心轴线在28°和32°之间的范围内提供。 在引导叶片区域的下游，布置有扩散器区域，扩散区域没有设置有影响流动的流动引导元件，其中布置在环形燃烧室中的燃烧器设置有它们的燃烧器轴线在 相对于中心轴40°和50°。

公开(公告)号：US20150260053A1

公开(公告)日：2015-09-17

申请号：US14418066

申请日：2013-07-29

Applicant: FINNO ENERGY OY

Inventor： Timo Erämaa

IPC: F01D15/10 ,  F02C3/14 ,  F02C6/16 ,  F02C3/13

CPC classification number: F01D15/10 ,  F01K21/04 ,  F02C3/13 ,  F02C3/14 ,  F02C5/12 ,  F02C6/16 ,  F05D2260/601 ,  Y02E20/16 ,  Y02E60/15

Abstract: An object of the present invention is to provide a method and a system for implementing the method so as to alleviate the disadvantages of a reciprocating combustion engine and gas turbine in electric energy production. The invention is based on the idea of arranging a combustion chamber (10) outside a gas turbine (22) and providing compressed air to the combustion chamber (10) in order to carry out a combustion process in controlled and optimal conditions.

Abstract translation: 本发明的目的是提供一种实现该方法的方法和系统，以减轻往复式内燃发动机和燃气轮机在电能生产中的缺点。 本发明基于将燃烧室（10）布置在燃气涡轮机（22）的外面并且向燃烧室（10）提供压缩空气以在受控和最佳条件下执行燃烧过程的想法。

公开(公告)号：US09127554B2

公开(公告)日：2015-09-08

申请号：US13602422

申请日：2012-09-04

Applicant: Richard C. Charron ,  Matthew D. Montgomery

Inventor： Richard C. Charron ,  Matthew D. Montgomery

IPC: F01D9/02 ,  F01D9/04 ,  F02C3/14 ,  F23R3/46

CPC classification number: F01D9/023 ,  F01D9/02 ,  F01D9/04 ,  F02C3/14 ,  F23R3/46 ,  Y02T50/671

Abstract: An industrial gas turbine engine (10), including: a can annular combustion assembly (80), having a plurality of discrete flow ducts configured to receive combustion gas from respective combustors (82) and deliver the combustion gas along a straight flow path at a speed and orientation appropriate for delivery directly onto the first row (56) of turbine blades (62); and a compressor diffuser (32) having a redirecting surface (130, 140) configured to receive an axial flow of compressed air and redirect the axial flow of compressed air radially outward.

Abstract translation: 一种工业燃气涡轮发动机（10），包括：罐式环形燃烧组件（80），其具有多个离散的流动管道，其构造成从相应燃烧器（82）接收燃烧气体，并沿着直线流动路径 适于直接输送到涡轮叶片（62）的第一排（56）上的速度和方位; 和压缩机扩散器（32），其具有被配置为接收压缩空气的轴向流动并将径向向外的压缩空气的轴向流动重定向的重定向表面（130,140）。

公开(公告)号：US20150219336A1

公开(公告)日：2015-08-06

申请号：US14170729

申请日：2014-02-03

Applicant: General Electric Company

Inventor： Sarah Lori Crothers ,  Willy Steve Ziminsky ,  Christian Xavier Stevenson

IPC: F23R3/34 ,  F02C3/14

CPC classification number: F23R3/34 ,  F23R3/14 ,  F23R3/286 ,  F23R3/46 ,  F23R2900/00014

Abstract: A gas turbine includes one or more combustors, and each combustor may include one or more fuel nozzles for mixing fuel with a compressed working fluid prior to combustion. The gas turbine further includes various structures for reducing the modal coupling of the combustion dynamics by producing a different convective time, fuel flow, and/or compressed working fluid flow through at least one fuel nozzle.

Abstract translation: 燃气轮机包括一个或多个燃烧器，并且每个燃烧器可以包括用于在燃烧之前将燃料与压缩的工作流体混合的一个或多个燃料喷嘴。 燃气轮机还包括各种结构，用于通过产生不同的对流时间，燃料流量和/或压缩的工作流体流过至少一个燃料喷嘴来减少燃烧动力学的模态耦合。

公开(公告)号：US09097183B2

公开(公告)日：2015-08-04

申请号：US12879552

申请日：2010-09-10

Applicant: Werner J. A. Dahm

Inventor： Werner J. A. Dahm

IPC: F02C7/22 ,  F02K7/10 ,  F02C1/00 ,  F02K9/66 ,  F23R3/40 ,  F02C3/14 ,  F02C3/16 ,  F02C5/04

CPC classification number: F02C7/22 ,  F02C3/14 ,  F02C3/165 ,  F02C5/04 ,  F02K7/10 ,  F02K9/66 ,  F23R3/40

Abstract: A method for improving interpenetration, mixing, and combustion between a fuel and oxidizer reactant mixture and combustion product gases in engines having a combustor includes the step of providing an engine having a combustor in which the reaction mixture and product gases are subjected to acceleration directed transverse to a direction along which the reactant mixture flows through the combustor during combustion. One or more catalyst elements are positioned within the combustor to generate Rayleigh-Taylor instability and thereby enhance interpenetration of the reactant mixture and product gases within the combustor chamber during combustion.

Abstract translation: 一种用于改善在具有燃烧器的发动机中的燃料和氧化剂反应物混合物和燃烧产物气体之间的相互渗透，混合和燃烧的方法包括提供具有燃烧器的发动机的步骤，其中反应混合物和产物气体经受加速度横向 在燃烧期间反应物混合物沿着该方向流过燃烧器。 一个或多个催化剂元件定位在燃烧器内以产生瑞利 - 泰勒不稳定性，从而增强燃烧期间燃烧室内的反应物混合物和产物气体的相互渗透。

公开(公告)号：US09046058B2

公开(公告)日：2015-06-02

申请号：US13392149

申请日：2009-12-18

Applicant: Scott Claflin

Inventor： Scott Claflin

IPC: F02C5/00 ,  F02K9/66 ,  F02C3/14 ,  F02K7/04 ,  F23R7/00 ,  H05H1/52

CPC classification number: F02K9/66 ,  F02C3/14 ,  F02K7/04 ,  F05D2250/25 ,  F05D2270/172 ,  F23R7/00 ,  H05H1/52

Abstract: An annular combustion (22) chamber and a transient plasma system (42) in communication with the annular combustion chamber (22) to sustain a spinning detonation wave. This system (42) is also called as “nanosecond pulsed plasma” system and a pulse generator (48) operates to generate by energy but intense high voltage pulses to provide tansient plasma (p); increasing the reactivity of the chemical species of the popelllants. The propulsion relies on constant pressure combustion (CDWE).

Abstract translation: 与环形燃烧室（22）连通的环形燃烧室（22）和瞬态等离子体系统（42），以维持旋转爆震波。 该系统（42）也称为“纳秒脉冲等离子体”系统，脉冲发生器（48）通过能量而产生强烈的高电压脉冲以提供令人感觉的等离子体（p）; 增加了大众化学品种的反应性。 推进力依赖于恒压燃烧（CDWE）。