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公开(公告)号：EP2809911B1
公开(公告)日：2018-06-06
申请号：EP13787586.0
申请日：2013-01-16
IPC分类号： F02C6/08
CPC分类号： F02C9/18 , F01D11/04 , F01D25/00 , F01D25/16 , F02C6/08 , F02C7/06 , F02C7/12 , F02C7/18 , F02C7/28 , F05D2260/601 , Y02T50/675 , Y10T29/49229
摘要： A gas turbine engine includes a buffer system that can communicate buffer supply air to a portion of the gas turbine engine. The buffer system can include a first circuit and a second circuit. The first circuit selects between a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to render a first buffer supply air having an intermediate pressure. The second circuit selects between a third bleed air supply and a fourth bleed air supply to communicate a second buffer supply air.
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公开(公告)号：EP3090163B1
公开(公告)日：2018-02-21
申请号：EP14885609.9
申请日：2014-12-18
CPC分类号： F01D5/081 , F01D9/065 , F01D25/24 , F02C3/04 , F02C7/185 , F05D2220/32 , F05D2260/213 , F05D2260/601 , Y02T50/676
摘要： A flow system for use in a gas turbine engine includes a diffuser case strut defining a first opening at a first radial end, a second opening at a second radial end, and a strut passage radially therethrough between the first and second openings. A first chamber wall and a second chamber wall define a first mixing chamber disposed radially inward of the diffuser case strut in fluid communication with the strut passage. A third chamber wall extends between the second flowpath wall and the second chamber wall to define a second mixing chamber disposed between the diffuser case strut and the first mixing chamber. The second flowpath wall and the second chamber wall are shaped to form a venturi in the second mixing chamber.
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公开(公告)号：EP2541020A3
公开(公告)日：2018-01-10
申请号：EP12173461.0
申请日：2012-06-25
摘要： A turbine ventilation system (48) includes at least one fan (32, 54, 56) configured to provide a first air flow (112) into a gas turbine enclosure (18), a fan bypass (12) configured to circumvent the at least one fan (32, 54, 56) to provide a second air flow (114) into the gas turbine enclosure (18), and an eductor (34) configured to draw the first (112) or second (114) air flows through and out of the gas turbine enclosure (18).
摘要翻译： 涡轮机通风系统（48）包括构造成将第一空气流（112）提供到燃气涡轮机外壳（18）中的至少一个风扇（32,54,56），风扇旁路（12），构造成绕过至少一个 一个风扇（32,54,56）将第二气流（114）提供到所述燃气涡轮机外壳（18）中，以及喷射器（34），所述喷射器被配置为将所述第一（112）或第二（114）气流吸入并且 离开燃气涡轮机壳体（18）。
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公开(公告)号：EP3219956A3
公开(公告)日：2017-11-29
申请号：EP17156267.1
申请日：2017-02-15
CPC分类号： F01D25/12 , F01D3/04 , F01D5/06 , F01D25/168 , F02C6/08 , F02C9/18 , F04D29/0516 , F04F5/30 , F05D2260/601 , F05D2270/301 , F16C2360/23
摘要： An apparatus and method for providing a pressurized air supply (88) to a balance piston assembly (94) to balance an axial load on a gas turbine engine compressor (22). The pressurized air supply (88) can be supplied by a mixing valve (144) mixing a primary (140) and secondary pressure bleed air supply (142) relative to feedback received from the balance piston assembly (94) to maintain a predetermined pressure at the balance piston assembly (94).
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公开(公告)号：EP3184747A1
公开(公告)日：2017-06-28
申请号：EP16203123.1
申请日：2016-12-09
发明人： LACY, Benjamin Paul
CPC分类号： F01D25/12 , F01D5/185 , F01D9/023 , F01D9/041 , F01D9/065 , F02C3/04 , F02C3/14 , F02C7/222 , F02C7/224 , F05D2220/32 , F05D2240/123 , F05D2240/124 , F05D2240/35 , F05D2260/202 , F05D2260/232 , F05D2260/601 , F23R3/20 , F23R3/34
摘要： A gas turbine 12 that includes a row of circumferentially spaced stator blades 17 in a turbine. Each of the stator blades may include an airfoil 120 defined between a concave pressure side face 126 and a laterally opposed convex suction side face 127. At least one of the stator blades within the row may include a fuel injector 51 that includes: a transverse nozzle 119 extending through the airfoil between an inlet formed through the pressure side face and an outlet formed through the suction side face of the airfoil; and a fuel channel formed through the airfoil of the stator blade, the fuel channel having an upstream end, at which an inlet port fluidly connects the fuel channel to a fuel supply, and a downstream end, at which an outlet port fluidly connects the fuel channel to the transverse nozzle.
摘要翻译： 燃气涡轮机12包括涡轮机中的一排周向隔开的定子叶片17。 每个定子叶片可以包括限定在凹形压力侧面126和横向相对的凸形吸力侧面127之间的翼型件120.该排内的定子叶片中的至少一个可以包括燃料喷射器51，该燃料喷射器51包括：横向喷嘴 119在穿过压力侧面形成的入口和穿过翼型的吸力侧面形成的出口之间穿过翼型件延伸; 以及通过定子叶片的翼型形成的燃料通道，燃料通道具有上游端和下游端，在该上游端处，入口端口将燃料通道流体连接至燃料供应源，在该下游端处，出口端口流体连接燃料 通道到横向喷嘴。
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公开(公告)号：EP2971748A4
公开(公告)日：2016-11-30
申请号：EP13878215
申请日：2013-12-16
CPC分类号： F02C7/222 , F02C7/22 , F02C7/236 , F04F5/02 , F05D2260/601 , F23K5/142 , F23K2301/201
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7.发明公开COOLING SYSTEM WITH COMPRESSOR BLEED AND AMBIENT AIR FOR GAS TURBINE ENGINE 审中-公开冷却系统，燃气涡轮发动机的压气机出口和环境的空气
公开(公告)号：EP3066317A1
公开(公告)日：2016-09-14
申请号：EP14793405.3
申请日：2014-10-23
申请人： Siemens Energy, Inc.
发明人： MARSH, Jan H. , MARRA, John J.
CPC分类号： F01D25/12 , F02C6/08 , F02C7/12 , F02C7/185 , F05D2220/3215 , F05D2260/601
摘要： A cooling system for a turbine engine for directing cooling fluids from a compressor to a turbine blade cooling fluid supply and from an ambient air source to the turbine blade cooling fluid supply to supply cooling fluids to one or more airfoils of a rotor assembly is disclosed. The cooling system may include a compressor bleed conduit extending from a compressor to the turbine blade cooling fluid supply that provides cooling fluid to at least one turbine blade. The compressor bleed conduit may include an upstream section and a downstream section whereby the upstream section exhausts compressed bleed air through an outlet into the downstream section through which ambient air passes. The outlet of the upstream section may be generally aligned with a flow of ambient air flowing in the downstream section. As such, the compressed air increases the flow of ambient air to the turbine blade cooling fluid supply.
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8.发明公开INSTALLATION A TURBINE A GAZ ET PROCEDE DE REGULATION DE LADITE INSTALLATION. 审中-公开用于控制该系统燃气轮机和方法的设备
公开(公告)号：EP2951420A1
公开(公告)日：2015-12-09
申请号：EP14703056.3
申请日：2014-02-04
申请人： DALKIA
CPC分类号： F02C7/143 , F05D2260/60 , F05D2260/601 , F25B7/00 , Y02E20/14 , Y02P80/15
摘要： The invention concerns a facility with a gas turbine, comprising: - a refrigerating machine (100) comprising: ° a high-pressure circuit (110) with a generator (114) supplied by a pump (112) and subjected to a heat source, ° a low-pressure circuit (120) with an evaporator (108) supplied by an expansion member (106) and forming a first cold source, ° an intermediate-pressure circuit (130) with an ejector (102) and a condenser (104) positioned downstream from said ejector (102), - a gas turbine (200) with a compressor (202), in which the air supply conduit (210) of the compressor is subjected to a cold source and the exhaust gas conduit (212) belongs to said heat source. Application to the production of electricity by stationary co-generation.
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公开(公告)号：EP2805039B1
公开(公告)日：2015-11-04
申请号：EP13704160.4
申请日：2013-01-16
申请人： Snecma
IPC分类号： F02K9/48
CPC分类号： F02K9/46 , F02K9/48 , F05D2260/601
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公开(公告)号：EP2809901A4
公开(公告)日：2015-10-21
申请号：EP13775885
申请日：2013-01-16
CPC分类号： F02C6/08 , F01D25/18 , F01D25/183 , F02C7/12 , F02C7/14 , F05D2260/601 , Y02T50/675
摘要： A gas turbine engine includes a buffer system that includes a first circuit and a second circuit. The first circuit can communicate a first buffer supply air to a first portion of the gas turbine engine and the second circuit can communicate a second buffer supply air to a second portion of the gas turbine engine.
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