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公开(公告)号：US20150000755A1
公开(公告)日：2015-01-01
申请号：US14365204
申请日：2012-12-07
Applicant: SNECMA
Inventor： David Hayoun , Francois Danguy , Jean Michel Sannino , Pascal Marcel, Jean Noir
CPC classification number: F17D3/01 , F02K9/48 , F02K9/50 , F16L53/30 , F17C5/00 , F17C2201/054 , F17C2205/0326 , F17C2221/011 , F17C2221/012 , F17C2221/017 , F17C2221/08 , F17C2223/0161 , F17C2223/033 , F17C2225/0123 , F17C2225/036 , F17C2227/0107 , F17C2227/0135 , F17C2227/0142 , F17C2227/0157 , F17C2227/0164 , F17C2227/0309 , F17C2227/0388 , F17C2270/0197 , Y02E60/321 , Y10T137/0396 , Y10T137/6579
Abstract: A pressurizing device and method, for pressurizing a first tank, the device including at least a second tank configured to contain a cryogenic fluid, a first pressurizing circuit for putting the second tank into communication with the first tank, the first pressurizing circuit including at least a first heat exchanger for heating a flow of the cryogenic fluid extracted from the second tank through the first pressurizing circuit, and a second pressurizing circuit with a compressor, branched off from the first pressurizing circuit and leading to the second tank. A feed system for feeding a reaction engine with at least a first liquid propellant includes at least a first tank configured to contain the first liquid propellant, and a device for pressurizing the first tank.
Abstract translation: 一种用于对第一罐加压的加压装置和方法，所述装置至少包括构造成容纳低温流体的第二罐，用于使第二罐与第一罐连通的第一加压回路，第一加压回路至少包括 第一热交换器，用于加热通过第一加压回路从第二罐提取的低温流体的流动;以及第二加压回路，其具有从第一加压回路分支并通向第二罐的压缩机。 用于向至少第一液体推进剂供给反应引擎的进料系统包括至少第一罐，其构造成容纳第一液体推进剂，以及用于对第一罐加压的装置。
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公开(公告)号：US09951694B2
公开(公告)日：2018-04-24
申请号：US15022101
申请日：2014-09-12
Inventor： Romain Thiriet , Patrick Marconi , Camel Serghine , Antoine Marie Georges Caratge , Francois Danguy , Laurent Fabbri , Pierre Yvart , Laurent Soulie , Philippe Barrat
CPC classification number: F02C7/277 , B64D27/10 , F01D19/00 , F02C6/206 , F02C7/272 , F05D2260/85 , Y02T50/672
Abstract: An emergency start system for a turbine engine of an aircraft including at least one solid propellant gas generator, an electrically controlled ignition device, a computer connected to the ignition device, and at least one starter motor comprising a turbine for driving a shaft which is for coupling to a shaft of the turbine engine The outlet of the gases from the generator are connected to the inlet of the turbine of the starter motor.
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公开(公告)号：US09341315B2
公开(公告)日：2016-05-17
申请号：US14365204
申请日：2012-12-07
Applicant: SNECMA
Inventor： David Hayoun , Francois Danguy , Jean Michel Sannino , Pascal Marcel Jean Noir
CPC classification number: F17D3/01 , F02K9/48 , F02K9/50 , F16L53/30 , F17C5/00 , F17C2201/054 , F17C2205/0326 , F17C2221/011 , F17C2221/012 , F17C2221/017 , F17C2221/08 , F17C2223/0161 , F17C2223/033 , F17C2225/0123 , F17C2225/036 , F17C2227/0107 , F17C2227/0135 , F17C2227/0142 , F17C2227/0157 , F17C2227/0164 , F17C2227/0309 , F17C2227/0388 , F17C2270/0197 , Y02E60/321 , Y10T137/0396 , Y10T137/6579
Abstract: A pressurizing device and method, for pressurizing a first tank, the device including at least a second tank configured to contain a cryogenic fluid, a first pressurizing circuit for putting the second tank into communication with the first tank, the first pressurizing circuit including at least a first heat exchanger for heating a flow of the cryogenic fluid extracted from the second tank through the first pressurizing circuit, and a second pressurizing circuit with a compressor, branched off from the first pressurizing circuit and leading to the second tank. A feed system for feeding a reaction engine with at least a first liquid propellant includes at least a first tank configured to contain the first liquid propellant, and a device for pressurizing the first tank.
Abstract translation: 一种用于对第一罐加压的加压装置和方法，所述装置至少包括构造成容纳低温流体的第二罐，用于使第二罐与第一罐连通的第一加压回路，第一加压回路至少包括 第一热交换器，用于加热通过第一加压回路从第二罐提取的低温流体的流动;以及第二加压回路，其具有从第一加压回路分支并通向第二罐的压缩机。 用于向至少第一液体推进剂供给反应引擎的进料系统包括至少第一罐，其构造成容纳第一液体推进剂，以及用于对第一罐加压的装置。
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公开(公告)号：US20160230672A1
公开(公告)日：2016-08-11
申请号：US15022101
申请日：2014-09-12
Inventor： Romain Thiriet , Patrick Marconi , Camel Serghine , Antoine Marie Georges Caratge , Francois Danguy , Laurent Fabbri , Pierre Yvart , Laurent Soulie , Philippe Barrat
CPC classification number: F02C7/277 , B64D27/10 , F01D19/00 , F02C6/206 , F02C7/272 , F05D2260/85 , Y02T50/672
Abstract: The invention relates to an emergency start system (20) for a turbine engine of an aircraft, characterised in that it comprises at least one solid-propellant gas generator (22), an electrically controlled ignition device (24), a computer (28) connected to the ignition device, and at least one starter motor (18) comprising a turbine (38) for driving a shaft (34) intended for being coupled to a shaft (54) of the turbine engine, the outlet of the gases from the generator being connected to the inlet (44) of the turbine of the starter motor.
Abstract translation: 本发明涉及一种用于飞行器的涡轮发动机的紧急启动系统（20），其特征在于其包括至少一个固体推进剂气体发生器（22），电控点火装置（24），计算机（28） 连接到点火装置的至少一个启动马达（18），以及包括用于驱动用于联接到涡轮发动机的轴（54）的轴（34）的涡轮机（38）的至少一个起动马达（18），来自 发电机连接到起动电动机的涡轮机的入口（44）。
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