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Patent Agency Ranking
公开(公告)号：US20140373507A1
公开(公告)日：2014-12-25
申请号：US14372883
申请日：2013-01-16
Applicant: SNECMA
Inventor： Nicolas Soulier , David Hayoun , Jean Michel Sannino
IPC: F02K9/46
CPC classification number: F02K9/46 , F02K9/48 , F05D2260/601
Abstract: A rocket engine comprises a prechamber and a combustion chamber, two respective feed pipes of the engine, and two turbopumps. The engine is a staged combustion engine. A jet pump is arranged in at least a first feed pipe. After being pressurized, a portion of the fluid flowing in the first feed pipe is directed to the jet pump in order to enable the jet pump to entrain the fluid flowing in said feed pipe to the admission orifice of said first pump, thereby raising the pressure at the feed orifice of the pump.
Abstract translation: 火箭发动机包括预燃室和燃烧室，发动机的两个相应的进料管和两个涡轮泵。 发动机是分级内燃机。 喷射泵布置在至少第一进料管中。 在被加压之后，在第一进料管中流动的一部分流体被引导到喷射泵，以便使喷射泵将流入所述进料管的流体夹带到所述第一泵的进入孔，从而提高压力 在泵的进料口处。
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公开(公告)号：US20140260181A1
公开(公告)日：2014-09-18
申请号：US14350980
申请日：2012-10-08
Applicant: SNECMA
Inventor： Nicolas Soulier , Bruno Brochard , Jean-Michel Sannino
Abstract: A reaction propulsion device in which a first feed circuit for feeding a main thruster with a first propellant includes a branch connection downstream from a pump of a first turbopump, which branch connection passes through a first regenerative heat exchanger and a turbine of a first turbopump, and in which a second feed circuit for feeding the main thruster with a second propellant includes, downstream from a pump of a second turbopump, a branch-off passing through a second regenerative heat exchanger and a turbine of the second turbopump. At least one secondary thruster is connected downstream from the turbines of the first and second turbopumps.
Abstract translation: 一种反应推进装置，其中用于向主推进器供给第一推进剂的第一进料回路包括在第一涡轮泵的泵的下游的分支连接，该分支连接通过第一再生式热交换器和第一涡轮泵的涡轮， 并且其中用于向主推进器供给第二推进剂的第二进料回路包括在第二涡轮泵的泵的下游，通过第二再生热交换器和第二涡轮泵的涡轮的分支。 至少一个次级推进器连接在第一和第二涡轮泵的涡轮机的下游。
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公开(公告)号：US09771897B2
公开(公告)日：2017-09-26
申请号：US14350980
申请日：2012-10-08
Applicant: SNECMA
Inventor： Nicolas Soulier , Bruno Brochard , Jean-Michel Sannino
Abstract: A reaction propulsion device in which a first feed circuit for feeding a main thruster with a first propellant includes a branch connection downstream from a pump of a first turbopump, which branch connection passes through a first regenerative heat exchanger and a turbine of a first turbopump, and in which a second feed circuit for feeding the main thruster with a second propellant includes, downstream from a pump of a second turbopump, a branch-off passing through a second regenerative heat exchanger and a turbine of the second turbopump. At least one secondary thruster is connected downstream from the turbines of the first and second turbopumps.
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4.发明申请公开(公告)号：US20150144738A1
公开(公告)日：2015-05-28
申请号：US14405947
申请日：2013-06-03
Applicant: SNECMA
Inventor： Nicolas Soulier , Maxime Vicentini , Jean-Marie Conrardy
Abstract: A spacecraft including at least one main propellant tank, a main engine fed with propellant by the main tank, and a de-orbiting device. The de-orbiting device includes a detonation engine fed with propellant by the main tank.
Abstract translation: 包括至少一个主推进剂罐，由主油箱供给推进剂的主发动机和离轨装置的航天器。 离轨装置包括由主油箱供给推进剂的爆震发动机。
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5.发明授权公开(公告)号：US09487310B2
公开(公告)日：2016-11-08
申请号：US14405947
申请日：2013-06-03
Applicant: SNECMA
Inventor： Nicolas Soulier , Maxime Vicentini , Jean-Marie Conrardy
Abstract: A spacecraft including at least one main propellant tank, a main engine fed with propellant by the main tank, and a de-orbiting device. The de-orbiting device includes a detonation engine fed with propellant by the main tank.
Abstract translation: 包括至少一个主推进剂罐，由主油箱供给推进剂的主发动机和离轨装置的航天器。 离轨装置包括由主油箱供给推进剂的爆震发动机。
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