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91.发明授权公开(公告)号：US09926809B2
公开(公告)日：2018-03-27
申请号：US14368554
申请日：2013-02-01
申请人： TURBOMECA
发明人： Fabian Ammon , Alexandre Brisson , Guy Crabe , Jacques Demolis , Laurent Houssaye , Julien Munoz
CPC分类号： F01D25/305 , B01F5/049 , B64D33/04 , F01D25/30 , F02C3/32 , F05B2260/601 , Y02T50/672
摘要： A method for discharging exhaust gas from a gas turbine wherein a number of sectors, position, and angle at the center of at least one sector of a peripheral opening capable of forming an area for reingestion of a primary flow into an engine bay are determined by correlation of interactions between secondary cooling flows and the primary flow, from following behavior parameters: air gyration and speed at an inlet of a pipe, geometry of an exhaust stream, routing of the secondary cooling flow for cooling the engine bay, and a geometry and position of inlets of the secondary flows. The peripheral opening is then closed over the identified at least one angular sector. The method prevents backflow of hot primary air into the peripheral opening formed between a pipe and an ejector of the exhaust stream of a gas turbine.
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公开(公告)号：US20180066604A1
公开(公告)日：2018-03-08
申请号：US15673047
申请日：2017-08-09
CPC分类号： F02K1/386 , F01D9/041 , F01D25/30 , F02K1/48 , F05D2240/12 , F05D2250/61
摘要： A turbine exhaust case (TEC) of a turbofan aeroengine includes a mixer in an annular wavy configuration having alternate crests and valleys, and a plurality of radial deswirling struts interconnecting an annular hub positioned within the mixer and selected valleys of the mixer. A plurality of secondary trailing edge struts smaller than the deswirling struts in average chord dimensions interconnect the annular hub and other selected valleys free of connection with the deswirling struts.
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公开(公告)号：US20180051627A1
公开(公告)日：2018-02-22
申请号：US15239086
申请日：2016-08-17
CPC分类号： F02C3/10 , B64D27/10 , B64D33/02 , B64D33/04 , F01D25/30 , F02C7/36 , F02K3/062 , F02K3/12 , F05D2220/32 , F05D2250/314 , F05D2260/40311
摘要： A gas turbine engine for an aircraft includes a core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section. A free turbine is configured to be driven by gas flow from the core engine. A propulsor section aft of the core engine and is driven by the free turbine. An exhaust duct routes exhaust gases from the core engine to the free turbine. The free turbine is disposed aft of the propulsor section and the exhaust duct includes an outlet aft of the propulsor section communicating gas flow to drive the free turbine. An aircraft is also disclosed.
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公开(公告)号：US09890672B2
公开(公告)日：2018-02-13
申请号：US14418756
申请日：2012-09-06
申请人： Hideo Miyanishi , Yasuyuki Kuroda , Rand Drake , Albert Bednarski , Paul Harris , James Paul , Kevin Linfield
发明人： Hideo Miyanishi , Yasuyuki Kuroda , Rand Drake , Albert Bednarski , Paul Harris , James Paul , Kevin Linfield
CPC分类号： F01N3/02 , B01D53/8631 , B01D2251/2062 , B01D2255/20707 , B01D2255/20723 , B01D2255/20776 , B01D2257/404 , F01D25/12 , F01D25/30 , F01N3/05 , F01N3/208 , F01N2470/04 , F02C7/141 , Y02T10/20
摘要： A combustion gas cooling apparatus includes a cooling duct from which a cooling gas at a temperature lower than the temperature of a combustion gas flows out into a mixing duct to form a mixed gas in which the combustion gas and the cooling gas are mixed. The cooling duct has cooling gas flow inlets into which the cooling gas flows, a plurality of cooling gas outflow apertures through which the cooling gas having flowed into the cooling gas flow inlets flows out into the mixing duct, and distribution passages through which the cooling gas having flowed into the cooling gas flow inlets is distributed to the plurality of cooling gas outflow apertures.
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公开(公告)号：US09850782B2
公开(公告)日：2017-12-26
申请号：US13906552
申请日：2013-05-31
申请人： Evapco, Inc.
发明人： Raf de Lausnay
摘要： A double turbine exhaust duct design and an inline V turbine exhaust duct design that both eliminate the need for the standard T-piece in a turbine exhaust duct assembly, substantially reducing the steam-side pressure drop, minimizing the sub-cooling in the steam cycle (the temperature difference between ACC condensate temperature out and turbine steam temperature), thus improving the overall efficiency of the steam cycle plant heat rate.
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公开(公告)号：US09845695B2
公开(公告)日：2017-12-19
申请号：US14652715
申请日：2013-12-23
发明人： Matthew Budnick , Conway Chuong
CPC分类号： F01D11/003 , F01D11/005 , F01D25/162 , F01D25/246 , F01D25/30 , F02C7/28 , F05D2220/32
摘要： A gas turbine engine assembly includes a second module interconnected with a first module along a joint such that a surface of a second radial wall faces a surface of a first radial wall, with a cavity defined in part by the first and second radial walls. A seal assembly includes a finger seal, and a seal support ring having a backing ring portion and a flow discourager arm. The backing ring is secured to one of the first radial wall and the second radial wall, and the flow discourager arm extends axially through the cavity into a recess formed in the other of the first and second radial walls. The finger seal includes a free end contacting an inner side of the flow discourager arm.
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公开(公告)号：US20170342863A1
公开(公告)日：2017-11-30
申请号：US15073282
申请日：2016-03-17
CPC分类号： F01D25/305 , F01D9/041 , F01D11/003 , F02K1/386 , F02K1/825 , F05D2220/323 , F05D2260/96
摘要： Systems and methods for suppressing infrared radiation generated by a turbine engine. A system comprises a primary assembly having a center body, a plurality of vanes extending from the center body, an outer radial duct with the plurality of vanes extending therethrough, a structural baffle, and a mixer. The primary assembly is disposed in the exhaust flow path of a turbine engine and encased in ducting and/or an airfoil. An air flow path defined between the center body and outer radial duct is axially spit by an interface rim and flow segregator. The flow segregator segregates engine core flow from ambient air flow.
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公开(公告)号：US20170342862A1
公开(公告)日：2017-11-30
申请号：US15168400
申请日：2016-05-31
摘要： The present application provides an exhaust diffuser for a gas turbine engine. The exhaust diffuser may include a hub, a casing, and a strut extending between the hub and the casing. The hub may include an angled configuration about the strut and a substantially flat configuration downstream of the angled configuration.
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公开(公告)号：US20170335715A1
公开(公告)日：2017-11-23
申请号：US15160366
申请日：2016-05-20
CPC分类号： F01D25/02 , B64D15/04 , F01D25/10 , F01D25/30 , F02C3/04 , F02C6/08 , F02C7/047 , F02C9/18 , F05D2220/323 , F05D2240/35 , F05D2260/213 , Y02T50/675
摘要： A method for providing an anti-icing airflow, including extracting a compressed airflow from a core flow path of an engine, heating the compressed airflow, mixing the heated compressed airflow with air extracted from a bypass flow path to create the anti-icing airflow having a higher temperature and pressure than that of the air extracted from the bypass flow path, and circulating the anti-icing airflow away from the bypass flow path. Also, an assembly located at least in part inside a turbofan engine and including a heat exchanger, a flow mixing device having a first inlet in the bypass flow path, a second inlet and an outlet, a first conduit providing fluid communication between the heat exchanger and a compressed air portion of the core flow path, a second conduit providing fluid communication between the heat exchanger and the second inlet, and a third conduit in fluid communication with the outlet.
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公开(公告)号：US09816461B2
公开(公告)日：2017-11-14
申请号：US14339846
申请日：2014-07-24
申请人： SNECMA
发明人： Guillaume Pouyau , Nicolas Sirvin
IPC分类号： F02K1/04 , F02K1/82 , F01D25/30 , F01D5/14 , B64D33/04 , F01D17/10 , F01D17/14 , F01D25/04 , B21D53/84 , B23P23/00
CPC分类号： F02K1/04 , B21D53/84 , B23P23/00 , B64D33/04 , F01D5/143 , F01D17/10 , F01D17/141 , F01D17/145 , F01D25/04 , F01D25/30 , F02K1/82 , Y02T50/671 , Y02T50/673 , Y10T29/49323
摘要： An exhaust centerbody for a turbine engine is provided. The centerbody includes a truncated downstream part, which is connected to an upstream part by an annular ridge marking a discontinuity between the outer surfaces of the upstream and downstream parts. The outer surface of the downstream part has a substantially conical general shape, of which the tip is oriented downstream and is positioned in the region of the axis A, the axial half-section of this outer surface defining a line of which the upstream end part is substantially tangential to a straight line passing through the ridge and forming a non-zero angle α with a tangent to the outer surface of the upstream part, in the region of the ridge, and of which the downstream end part is substantially tangential to a straight line passing through the tip and forming a non-zero angle β with the axis A.
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