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公开(公告)号：US10018360B2
公开(公告)日：2018-07-10
申请号：US14728991
申请日：2015-06-02
Applicant: United Technologies Corporation
Inventor： Gabriel L Suciu , Brian D Merry , James D Hill
CPC classification number: F23R3/10 , F01D5/082 , F01D9/06 , F01D25/125 , F02C3/04 , F02C6/08 , F02C7/185 , F05D2220/323 , F05D2260/213 , F05D2270/303 , F05D2270/3062 , Y02T50/676
Abstract: A turbine injection system for a gas turbine engine includes a first end operable to receive air from a heat exchanger, a second end operable to distribute mixed cooling air to a turbine stage, an opening downstream of said first end and a mixing plenum downstream of said first end and said opening. The opening provides a direct fluid pathway into said turbine injection system.
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公开(公告)号：US09752704B2
公开(公告)日：2017-09-05
申请号：US13938925
申请日：2013-07-10
Applicant: SNECMA
Inventor： Huguette de Wergifosse
CPC classification number: F16K49/00 , F02C7/06 , F02C7/224 , F05D2260/606 , F05D2260/98 , F05D2270/303 , F05D2270/3062 , F05D2270/56 , G05D23/1393 , G05D23/1925 , Y02T50/671 , Y10T137/6579
Abstract: A valve for regulating the temperature of an oil flow, includes a first inlet channel, a second inlet channel and an outlet channel, the second inlet channel and the outlet channel being capable of cooperating with a temperature regulator. One of the inlet channels includes an oil flow regulator controlled by a computer by generation of an electrical set value respecting a control law configured within the computer, the control law being slaved by an oil flow temperature sensor, the electrical set value controlling opening and closing of the regulator, the regulation law generating an alternation of open and closed states of the flow regulator so as to achieve a required average temperature of the oil flow over a given period.
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公开(公告)号：US20170204786A1
公开(公告)日：2017-07-20
申请号：US14997319
申请日：2016-01-15
Applicant: General Electric Company
Inventor： Hua Zhang , Parag Prakash Kulkarni , Bradly Aaron Kippel
CPC classification number: F02C7/18 , F01D25/305 , F02C7/052 , F02C9/16 , F05D2270/082 , F05D2270/3062
Abstract: A gas turbine system includes a gas turbine engine, an exhaust processing system disposed downstream of and fluidly coupled to the gas turbine engine, and an air delivery system that may supply treated air to the gas turbine engine and the exhaust processing system. The air delivery system includes a main air duct fluidly coupled to the gas turbine engine and that may supply a first portion of the treated air to the gas turbine engine, an auxiliary air duct fluidly coupled to the main air duct and the exhaust processing system and that may supply a second portion of the treated air to the exhaust processing system, and an air treatment unit fluidly coupled to the main air duct and that may generate the treated air.
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公开(公告)号：US09657585B2
公开(公告)日：2017-05-23
申请号：US14071922
申请日：2013-11-05
Applicant: Mitsubishi Hitachi Power Systems, Ltd.
Inventor： Yasuo Takahashi , Tetsuro Morisaki , Chihiro Myoren , Kohta Kawamura
CPC classification number: F01D11/24 , F01D11/18 , F01D25/26 , F02C3/305 , F02C7/1435 , F05D2270/3062 , F05D2300/50212 , Y02T50/675
Abstract: An axial compressor comprising liquid drop feed means for feeding liquid drops to an operating fluid of the compressor, a casing for forming a flow path through which the operating fluid flows down and a plurality of stages, each of which is composed of one continuous rotor blade row and one continuous stator vane row, the axial compressor being structured so that the liquid drops evaporate inside the compressor, characterized in that: the casing is provided with a cavity therein, and the cavity is formed by an outer casing and an inner casing which is enclosing a periphery of the rotor blade rows at the plurality of stages and forming internally a flow path of the operating fluid, and a flow path is provided for feeding the operating fluid to the cavity on a downstream side of a region forming the cavity of the inner casing.
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公开(公告)号：US20160376890A1
公开(公告)日：2016-12-29
申请号：US15259218
申请日：2016-09-08
Applicant: Kabushiki Kaisha Toshiba
Inventor： Asako INOMATA , Iwataro SATO , Hideyuki MAEDA , Satoru SEKINE , Kazutaka TSURUTA , Takeo SUGA
CPC classification number: F01D5/08 , F01D5/06 , F01D5/063 , F01D5/081 , F01D5/085 , F05D2220/32 , F05D2240/24 , F05D2240/61 , F05D2260/20 , F05D2270/3062
Abstract: A turbine 10 includes: a turbine rotor having a rotor main body including a hollow part into which a cooling fluid flows, and a plurality of rotor wheels arranged in an axial direction of the rotor main body and protruding from the rotor main body. A cooling-fluid introducing passage extending from the hollow part in a direction intersecting with the axial direction of the rotor main body is formed in the rotor main body so as to allow the cooling fluid in the hollow part to flow through the cooling-fluid introducing passage and then to flow around the rotor wheel to be conducted to the working-fluid flow passage. A flow-rate control plug regulating a flow rate of the cooling fluid flowing through the cooling-fluid introducing passage is disposed in the cooling-fluid introducing passage.
Abstract translation: 涡轮10包括：涡轮转子，具有转子主体，该转子主体包括冷却流体流过的中空部分，以及沿转子主体的轴向布置并从转子主体突出的多个转子轮。 在与转子主体的轴向交叉的方向上从中空部延伸的冷却流体导入通道形成在转子主体中，以使中空部分中的冷却流体流过冷却流体导入 通过，然后围绕转子轮流动以被传导到工作流体流动通道。 调节冷却流体导入通道的冷却流体的流量的流量控制插头配置在冷却流体导入通路内。
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Patent Agency Ranking
6.发明申请TURBINE COMPONENT HAVING SURFACE COOLING CHANNELS AND METHOD OF FORMING SAME 有权具有表面冷却通道的涡轮机部件及其形成方法公开(公告)号：US20160348512A1
公开(公告)日：2016-12-01
申请号：US14725695
申请日：2015-05-29
Applicant: General Electric Company
Inventor： Carlos Miguel Miranda , Andrew Lee Trimmer , Srikanth Chandrudu Kottilingam , Benjamin Paul Lacy
CPC classification number: F01D5/18 , F01D5/186 , F01D5/187 , F01D5/288 , F01D9/041 , F01D25/12 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2230/10 , F05D2240/128 , F05D2240/30 , F05D2240/35 , F05D2260/204 , F05D2270/3062 , F23R3/002 , Y02T50/676
Abstract: A component for a turbine engine includes a substrate that includes a first surface, and an insert coupled to the substrate proximate the substrate first surface. The component also includes a channel. The channel is defined by a first channel wall formed in the substrate and a second channel wall formed by at least one coating disposed on the substrate first surface. The component further includes an inlet opening defined in flow communication with the channel. The inlet opening is defined by a first inlet wall formed in the substrate and a second inlet wall defined by the insert.
Abstract translation: 涡轮发动机的部件包括：基板，其包括第一表面;以及插入件，其接近所述基板第一表面。 该组件还包括一个通道。 通道由形成在基板中的第一通道壁和由设置在基板第一表面上的至少一个涂层形成的第二通道壁限定。 该部件还包括与通道流动连通地限定的入口开口。 入口开口由形成在衬底中的第一入口壁和由插入件限定的第二入口壁限定。
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公开(公告)号：US20130312425A1
公开(公告)日：2013-11-28
申请号：US13477671
申请日：2012-05-22
Applicant: Lane Thornton , Thomas N. Slavens
Inventor： Lane Thornton , Thomas N. Slavens
CPC classification number: F01D5/187 , F01D5/18 , F01D5/188 , F01D11/18 , F01D17/00 , F01D17/085 , F02C6/08 , F02C7/185 , F05D2270/303 , F05D2270/3062 , F05D2270/42 , G05D23/1921
Abstract: An airfoil includes an airfoil body having an internal cavity. A thermostatic valve is located at least partially within the internal cavity. The thermostatic valve is configured to passively control fluid flow into the internal cavity in response to a temperature within the internal cavity.
Abstract translation: 翼型件包括具有内部空腔的翼型件本体。 恒温阀至少部分位于内腔内。 恒温阀被配置为响应于内部空腔内的温度而被动地控制流入内腔的流体。
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公开(公告)号：US20130174564A1
公开(公告)日：2013-07-11
申请号：US13345278
申请日：2012-01-06
Applicant: Rex Allen Morgan
Inventor： Rex Allen Morgan
IPC: F02C7/12
CPC classification number: F02C7/18 , F02C9/16 , F05D2270/3062 , F05D2270/708
Abstract: A method for determining a cooling flow parameter of a cooling medium supplied through a gas turbine is disclosed. The method may generally include receiving a signal associated with a first value of a combustion product parameter at a location within a combustion zone of the gas turbine, receiving a signal associated with a second value of a combustion product parameter at a location downstream of the combustion zone, comparing the first and second values of the combustion product parameter and determining a cooling flow parameter of the cooling medium based on the comparison of the first and second values.
Abstract translation: 公开了一种用于确定通过燃气轮机供应的冷却介质的冷却流量参数的方法。 该方法通常可以包括在燃气轮机的燃烧区域内的位置处接收与燃烧产物参数的第一值相关联的信号，在燃烧的下游位置接收与燃烧产物参数的第二值相关联的信号 区域，比较燃烧产物参数的第一和第二值，并且基于第一和第二值的比较来确定冷却介质的冷却流动参数。
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公开(公告)号：US10036329B2
公开(公告)日：2018-07-31
申请号：US14430315
申请日：2013-03-12
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu
IPC: F02C9/18 , F02C7/14 , F02K3/115 , F02C6/08 , F02C3/107 , F02C7/18 , F01D17/10 , F02K3/04 , F02K3/075
CPC classification number: F02C9/18 , F01D17/105 , F02C3/107 , F02C6/08 , F02C7/14 , F02C7/18 , F02K3/04 , F02K3/075 , F02K3/115 , F05D2260/213 , F05D2270/3062 , Y02T50/676
Abstract: A gas turbine engine has a fan nacelle and a core nacelle arranged to provide a bypass flow path. A compressor section is provided within the core nacelle. A heat exchanger is arranged within a duct. The heat exchanger is configured to receive bypass flow from the bypass flow path. The duct is in fluid communication with the compressor section and is configured to pass bleed air through the heat exchanger.
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公开(公告)号：US20170314473A1
公开(公告)日：2017-11-02
申请号：US15498850
申请日：2017-04-27
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Serge Rene MORREALE
IPC: F02C7/16 , F02C3/14 , F02C7/36 , F01D25/20 , F04D29/056 , F04D29/053 , F02C7/06 , F02C3/04
CPC classification number: F02C7/16 , F01D25/125 , F01D25/20 , F02C3/04 , F02C3/14 , F02C7/06 , F02C7/36 , F04D29/053 , F04D29/056 , F05D2220/32 , F05D2240/35 , F05D2240/60 , F05D2260/40311 , F05D2260/98 , F05D2270/3062
Abstract: A turbomachine including a turbine shaft supported by at least one bearing, at least one enclosure, housing the bearing of the turbine shaft, an oil cooling circuit of the enclosure including at least one jet configured to inject oil from the cooling circuit into the enclosure, and a regulator configured to regulate the flow of oil in the cooling circuit as a function of an oil temperature at output of the enclosure and a pressure difference at the level of the jet.
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