公开(公告)号：US20170074171A1

公开(公告)日：2017-03-16

申请号：US15264941

申请日：2016-09-14

Applicant: MITSUBISHI HITACHI POWER SYSTEMS, LTD.

Inventor： Kodai TAKENAKA ,  Shinichi YAMAZAKI

IPC: F02C9/18 ,  F02C3/30 ,  F02C7/18 ,  F02C7/224 ,  F02C3/04 ,  F02C7/141

CPC classification number: F02C9/18 ,  F02C3/04 ,  F02C3/30 ,  F02C7/141 ,  F02C7/18 ,  F02C7/224 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2230/80 ,  F05D2240/35 ,  F05D2260/213 ,  Y02E20/16

Abstract: A gas turbine plant comprises: a gas turbine having a compressor configured to compress air, a combustor configured to mix compressed air compressed by the compressor with fuel to generate combustion gas, a turbine connected to the compressor and configured to acquire rotary power by the combustion gas, and an air bleeding piping configured to supply the compressed air bled off from the compressor to the turbine as cooling air; and an auxiliary compressed air supply apparatus having a separately placed compressor different from the compressor, a motor configured to rotate the separately placed compressor, and an auxiliary compressed air piping configured to connect the separately placed compressor to the air bleeding piping to supply auxiliary compressed air compressed by the separately placed compressor to the air bleeding piping. The gas turbine further includes a cooling apparatus connected to the air bleeding piping and configured to cool down the cooling air.

Abstract translation: 一种燃气轮机设备包括：燃气轮机，其具有压缩机构造成压缩空气;燃烧器，被配置为将由压缩机压缩的压缩空气与燃料混合以产生燃烧气体;涡轮机，连接到压缩机并构造成通过燃烧获得旋转动力 气体和排气管道，其构造成将从压缩机排出的压缩空气供给到涡轮机作为冷却空气; 以及辅助压缩空气供给装置，其具有与压缩机不同的单独放置的压缩机，构造成旋转分开放置的压缩机的电动机和辅助压缩空气配管，其配置成将分开放置的压缩机连接到排气管道，以供应辅助压缩空气 通过分开放置的压缩机压缩到排气管道。 燃气轮机还包括连接到排气管道并构造成冷却冷却空气的冷却装置。

公开(公告)号：US09587561B2

公开(公告)日：2017-03-07

申请号：US14107412

申请日：2013-12-16

Applicant: Rolls-Royce North American Technologies, Inc.

Inventor： Douglas J. Snyder ,  Kenneth M. Pesyna ,  Anthony F. Pierluissi

IPC: F01D25/12 ,  F02C7/12 ,  F02C7/141 ,  F02K3/06 ,  F02C7/14 ,  F02C7/18

CPC classification number: F02C7/12 ,  F01D25/12 ,  F02C7/14 ,  F02C7/141 ,  F02C7/18 ,  F02K3/06 ,  F05D2260/20 ,  Y02T50/675

Abstract: One embodiment of an engine may include an enclosure surrounding an engine having an engine centerline, and the enclosure defining a passage for a cold-side airflow. The engine may also include one or more contiguous heat exchangers having a cold side inlet surface receiving a cold-side airflow. The heat exchanger may be disposed within the passage, such that a surface normal relative to the cold side inlet surface is offset by at least 30 degrees from the engine centerline.

Abstract translation: 发动机的一个实施例可以包括围绕具有发动机中心线的发动机的外壳，并且外壳限定用于冷侧气流的通道。 发动机还可以包括一个或多个连续的热交换器，其具有接收冷侧气流的冷侧入口表面。 热交换器可以设置在通道内，使得相对于冷侧入口表面法线的表面与发动机中心线相抵离至少30度。

公开(公告)号：US20170030265A1

公开(公告)日：2017-02-02

申请号：US14814656

申请日：2015-07-31

Applicant: GE Aviation Systems LLC

Inventor： Michael Timothy O'TOOLE ,  Kevin Harold COATES ,  Michael Robert WACKETT

IPC: F02C7/047 ,  F02C9/18 ,  F02C3/04

CPC classification number: F02C7/047 ,  B64D13/08 ,  B64D15/04 ,  B64D2033/0233 ,  F01D17/145 ,  F01D25/02 ,  F01D25/12 ,  F02C3/04 ,  F02C6/04 ,  F02C6/08 ,  F02C7/14 ,  F02C7/141 ,  F02C7/18 ,  F02C7/32 ,  F02C9/18 ,  F05D2220/32 ,  F05D2260/213 ,  F05D2260/57 ,  Y02T50/671 ,  Y02T50/675

Abstract: An anti-ice valve, a turbine engine including an anti-ice valve assembly and a method of operating an anti-ice valve where an anti-ice valve has a housing and a valve element configured to control a flow of hot bleed air through the housing, and a muscle air passage extending through the housing, a cooling air passage extending through the housing, and a heat exchanger located within the housing and having heat transfer surfaces in thermal communication with the muscle air passage and the cooling air passage.

Abstract translation: 防冰阀，包括防冰阀组件的涡轮发动机和防冰阀的操作方法，其中防冰阀具有外壳和阀元件，该阀元件被配置成控制通过 壳体和延伸穿过壳体的肌肉空气通道，延伸穿过壳体的冷却空气通道和位于壳体内的热交换器，并具有与肌肉空气通道和冷却空气通道热连通的传热表面。

公开(公告)号：US09534537B2

公开(公告)日：2017-01-03

申请号：US13432590

申请日：2012-03-28

Applicant: Steven Gagne ,  Rigoberto J. Rodriguez ,  William L. Siegel ,  John R. Arvin

Inventor： Steven Gagne ,  Rigoberto J. Rodriguez ,  William L. Siegel ,  John R. Arvin

IPC: F02C6/08 ,  F02C7/12 ,  F02C7/32 ,  F02C6/20 ,  F41H13/00 ,  F01D15/10

CPC classification number: F02C7/141 ,  F01D15/08 ,  F01D15/10 ,  F02C3/04 ,  F02C6/08 ,  F02C6/20 ,  F02C7/12 ,  F02C7/16 ,  F02C7/32 ,  F05D2220/323 ,  F05D2220/50 ,  F05D2220/76 ,  F05D2240/35 ,  F05D2260/207 ,  F25B23/00 ,  F25B2400/24 ,  F41H13/005 ,  F41H13/0068 ,  H02K7/1823 ,  Y02T50/675

Abstract: A system is disclosed one form of which is an aircraft that includes a pod capable of housing a work providing device. The pod can also include a thermal conditioning system and a power generation device that can be powered from the work providing device. The pod can provide thermal conditioning services and power services to a payload aboard the aircraft. In one non-limiting form the payload is a directed energy member that can be cooled using the thermal conditioning system and powered using the power generation device.

Abstract translation: 公开了一种系统，其一种形式是包括能够容纳工作提供装置的荚的飞机。 吊舱还可以包括热调节系统和可以从工作提供装置供电的发电装置。 荚可以为飞机上的有效载荷提供热调节服务和电力服务。 在一个非限制性形式中，有效载荷是能够使用热调节系统进行冷却并使用发电装置供电的定向能量构件。

公开(公告)号：US20160376954A1

公开(公告)日：2016-12-29

申请号：US14753064

申请日：2015-06-29

Applicant: General Electric Company

Inventor： Lewis Berkley Davis, JR. ,  Gilbert Otto Kraemer ,  Parag Prakash Kulkarni ,  Hua Zhang

IPC: F01N3/04 ,  F01N3/20 ,  F01D15/10 ,  F02C7/141 ,  F02C7/16 ,  F01N3/10 ,  F02C3/04

CPC classification number: F01N3/04 ,  F01D15/10 ,  F01D25/305 ,  F01N3/103 ,  F01N3/2066 ,  F01N2590/10 ,  F01N2610/02 ,  F01N2610/08 ,  F02C3/04 ,  F02C3/30 ,  F02C7/141 ,  F02C7/16 ,  F05D2220/32 ,  F05D2220/76 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2240/60 ,  F05D2260/212 ,  F05D2270/082 ,  Y02T10/24

Abstract: A turbomachine system according to an embodiment includes: a gas turbine system including a compressor component, a combustor component, and a turbine component; a mixing area for receiving an exhaust gas stream produced by the gas turbine system; a fluid injection system for injecting a fluid into the mixing area to reduce a temperature of the exhaust gas stream; and an exhaust processing system for processing the reduced temperature exhaust gas stream.

Abstract translation: 根据实施例的涡轮机系统包括：包括压缩机部件，燃烧器部件和涡轮机部件的燃气轮机系统; 用于接收由所述燃气轮机系统产生的废气流的混合区域; 用于将流体注入混合区域以降低排气流的温度的流体注入系统; 以及用于处理降温废气流的废气处理系统。

公开(公告)号：US09422063B2

公开(公告)日：2016-08-23

申请号：US13907187

申请日：2013-05-31

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Carlos Enrique Diaz

IPC: B64D33/10 ,  F02K3/115 ,  F02C7/141 ,  B64D33/02

CPC classification number: B64D33/10 ,  B64D29/00 ,  B64D2033/024 ,  F01D25/24 ,  F02C3/04 ,  F02C7/141 ,  F02C7/18 ,  F02K3/115 ,  F05D2220/32 ,  F05D2260/213 ,  Y02T50/672 ,  Y02T50/675

Abstract: In an aircraft including a gas turbine engine having a compressor including a compressor booster, a turbine, and a nacelle, a system for cooling compressor discharge air provided to the turbine to cool the turbine includes a heat exchanger provided in a nacelle compartment of the gas turbine engine configured to cool the compressor discharge air by exchanging heat from the compressor discharge air to a cooling fluid; and a cooling fluid circuit configured to circulate cooling fluid through the heat exchanger and a heat sink, wherein the heat sink is at least one of an inlet of the nacelle compartment, an inlet of the compressor booster, or outlet guide vanes of the gas turbine engine.

Abstract translation: 在具有包括压缩机助力器，涡轮机和机舱的压缩机的燃气涡轮发动机的飞机中，用于冷却设置到涡轮以冷却涡轮机的压缩机排出空气的系统包括设置在气体的机舱隔室中的热交换器 涡轮发动机，被配置为通过将来自压缩机排放空气的热量传递给冷却流体来冷却压缩机排放空气; 以及冷却流体回路，其被配置为使冷却流体循环通过所述热交换器和散热器，其中所述散热器是所述机舱隔室的入口，所述压缩机助力器的入口或所述燃气轮机的出口导向叶片中的至少一个 发动机。

公开(公告)号：US09341113B2

公开(公告)日：2016-05-17

申请号：US13658394

申请日：2012-10-23

Applicant: General Electric Company

Inventor： Joseph John ,  Raub Warfield Smith ,  Bhaskar Pemmi ,  Veerappan Muthaiah

IPC: F02C7/141 ,  F02C3/30 ,  F01K23/10 ,  F02C7/14 ,  F02C7/18 ,  F02C7/236

CPC classification number: F02C3/30 ,  F01K23/10 ,  F02C7/14 ,  F02C7/141 ,  F02C7/185 ,  F02C7/2365 ,  F05D2260/20 ,  F05D2260/205 ,  F05D2260/2322 ,  Y02E20/16

Abstract: An attemperation system and an atomizing air system are integrated for a combined cycle turbine including a gas turbine and a steam turbine. The atomizing air system receives compressor discharge air for fuel atomization. The atomizing air system includes an atomizing air cooler that serves to cool the compressor discharge air. A heat recovery steam generator receives exhaust from the gas turbine and generates steam for input to the steam turbine via an attemperation system. A feed water circuit draws feed water from the heat recovery steam generator and communicates in a heat exchange relationship with the atomizing air cooler to heat the feed water. The feed water circuit communicates the heated feed water to the attemperation system of the heat recovery steam generator.

Abstract translation: 包括燃气轮机和汽轮机的联合循环涡轮机整合了调温系统和雾化空气系统。 雾化空气系统接收用于燃料雾化的压缩机排放空气。 雾化空气系统包括用于冷却压缩机排出空气的雾化空气冷却器。 热回收蒸汽发生器接收来自燃气轮机的废气，并且通过调温系统产生用于输入到蒸汽轮机的蒸汽。 给水回路从热回收蒸汽发生器抽取供水，并与雾化空气冷却器以热交换关系连通以加热给水。 给水回路将加热的供水与热回收蒸汽发生器的调温系统连通。

公开(公告)号：US09297310B2

公开(公告)日：2016-03-29

申请号：US13654818

申请日：2012-10-18

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Sheo Narain Giri ,  Sanjeev Kumar Jha ,  Bhaskar Pemmi ,  Harish Bommanakatte ,  Santhosh Donkada ,  Krishna Kishore Gumpina ,  Indrajit Mazumder ,  Rajarshi Saha

IPC: F02C7/12 ,  F02C9/18 ,  F01D25/08 ,  F02C6/08 ,  F01D25/14 ,  F01D5/08

CPC classification number: F01D17/10 ,  F01D5/08 ,  F01D5/082 ,  F01D17/105 ,  F01D25/08 ,  F01D25/12 ,  F01D25/14 ,  F02C3/04 ,  F02C6/08 ,  F02C7/12 ,  F02C7/141 ,  F02C7/18 ,  F02C9/18 ,  F04D29/522 ,  F04D29/582 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/20 ,  F05D2300/173 ,  F05D2300/502 ,  F05D2300/504 ,  F05D2300/505

Abstract: A cooling arrangement for a gas turbine engine. The cooling arrangement comprises a discharge channel for air flow from a compressor, a first cooling channel and at least one aperture providing communication between the flow of air through the discharge channel and the first cooling channel. A restrictor device in the aperture regulates the flow of air between the discharge channel and the first cooling channel. The restrictor device deforms to vary air flowing through the aperture in response to a physical condition of the engine. This physical condition of the engine may be that of the temperature of air flowing through the discharge channel, the restrictor device responding to regulate the flow of air based on that temperature. The restrictor device may be a two-way shape memory alloy.

Abstract translation: 一种用于燃气涡轮发动机的冷却装置。 冷却装置包括用于来自压缩机的气流的排出通道，第一冷却通道和提供通过排放通道的空气流与第一冷却通道之间的连通的至少一个孔。 孔中的限流装置调节排放通道和第一冷却通道之间的空气流。 限制器装置变形以响应于发动机的物理状况改变流过孔的空气。 发动机的这种物理状态可以是流过排放通道的空气的温度，限制装置响应于基于该温度调节空气的流量。 限流装置可以是双向形状记忆合金。

公开(公告)号：US09273607B2

公开(公告)日：2016-03-01

申请号：US13907528

申请日：2013-05-31

Applicant: Rodney J. Allam

Inventor： Rodney J. Allam

IPC: F02C1/00 ,  F02C3/20 ,  F01K23/10 ,  F02C6/18

CPC classification number: F02C3/20 ,  F01K23/10 ,  F02C3/28 ,  F02C3/30 ,  F02C6/06 ,  F02C6/18 ,  F02C7/141 ,  F02C7/22 ,  F05D2220/32 ,  F05D2220/722 ,  F05D2220/75 ,  F05D2240/24 ,  F05D2240/35 ,  Y02E20/16 ,  Y02E20/18 ,  Y02E50/11 ,  Y02E50/12

Abstract: A system may include a compressor, a heat exchanger and an ITM. The compressor is configured to receive an air stream and compress the air stream to generate a pressurized stream. The heat exchanger is configured to receive the pressured stream and indirectly heat the pressurized stream using heat from an oxygen stream from an Ion Transport Membrane (ITM). The ITM is configured to receive the heated pressurized stream and generate an oxygen stream and the non-permeate stream, wherein the non-permeate stream is passed to a gas turbine burner and the oxygen stream is passed to the heat exchanger.

公开(公告)号：US20150308339A1

公开(公告)日：2015-10-29

申请号：US14647844

申请日：2013-01-29

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Matthew J. Forcier

IPC: F02C7/141

CPC classification number: F02C7/141 ,  F01D25/24 ,  F02C7/14 ,  F02C7/32 ,  F02K3/115 ,  F05D2230/72 ,  F05D2260/213 ,  Y02T50/675

Abstract: A gas turbine engine includes a nacelle, a lower bifurcation structure, and a heat exchanger. The nacelle extends circumferentially around an engine core and defines a fan bypass duct that is substantially annular between an inner wall and an outer wall. The lower bifurcation structure extends between the inner wall and the outer wall, bifurcating the fan bypass duct. The lower bifurcation structure defines a bifurcation duct extending along a central axis of the lower bifurcation structure. A heat exchanger is positioned in the bifurcation duct.

Abstract translation: 燃气涡轮发动机包括机舱，下分叉结构和热交换器。 机舱围绕发动机核心周向延伸并且限定了在内壁和外壁之间基本上环形的风扇旁路管道。 下分叉结构在内壁和外壁之间延伸，将风扇旁路管道分叉。 下分叉结构定义了沿着下分叉结构的中心轴延伸的分叉管。 热交换器位于分叉管中。