公开(公告)号：US20160281641A1

公开(公告)日：2016-09-29

申请号：US15034215

申请日：2014-11-05

Applicant: SNECMA

Inventor： François DANGUY ,  David HAYOUN ,  Jean Michel SANNINO

IPC: F02K9/42 ,  F02K9/48

CPC classification number: F02K9/425 ,  F02K9/48 ,  F02K9/50 ,  F02K9/64 ,  F02K9/972

Abstract: The invention relates to the field of rocket engines, and more particularly to a propulsion assembly (10) comprising a first tank (11) for a first liquid propellant, a second tank (12) for a second liquid propellant, a pressurizer device (60) configured to maintain a substantially higher pressure in the second tank (12) than in the first tank (11), and a single-shaft turbopump (30) comprising a turbine (33), a first pump (31), and a second pump (32). The turbine (33) is actuated by expansion of the first propellant after it has passed through a regenerative heat exchanger (44), and in turn it acts via the single rotary shaft (34) of the turbopump (30) to drive said first and second pumps (31, 32) respectively pumping said first and second propellants in order to feed a propulsion chamber (40).

Abstract translation: 本发明涉及火箭发动机领域，更具体地涉及一种推进组件（10），其包括用于第一液体推进剂的第一罐（11），用于第二液体推进剂的第二罐（12），加压装置（60） ）构造成在第二箱（12）中保持比在第一箱（11）中显着更高的压力，以及单轴涡轮泵（30），其包括涡轮机（33），第一泵（31）和第二泵 泵（32）。 第一推进剂在其通过再生热交换器（44）之后的膨胀致动涡轮（33），并且再次通过涡轮泵（30）的单个旋转轴（34）作用以驱动所述第一推进剂和 分别泵送所述第一和第二推进剂以便馈送推进室（40）的第二泵（31,32）。

公开(公告)号：US20160237951A1

公开(公告)日：2016-08-18

申请号：US15141431

申请日：2016-04-28

Applicant: SNECMA

Inventor： Jean Michel SANNINO ,  Emmanuel EDELINE ,  David HAYOUN

IPC: F02K9/46 ,  F02K9/60

Abstract: The invention relates to a device and a method for feeding a propulsion chamber of a rocket engine with at least with a first propellant. The device comprises at least a first tank for containing the first propellant, a first feed circuit connected to the first tank, and a first electric pump within the first tank in order to pump the first propellant through the first feed circuit. In the method, the first propellant is pumped through the first feed circuit from the first tank by at least the first electric pump that is immersed in the first propellant within the first tank.

Abstract translation: 本发明涉及一种用于至少与第一推进剂一起供给火箭发动机的推进室的装置和方法。 该装置至少包括用于容纳第一推进剂的第一罐，连接到第一罐的第一进料回路和第一罐内的第一电泵，以便通过第一进料回路泵送第一推进剂。 在该方法中，第一推进剂通过至少浸没在第一罐内的第一推进剂中的第一电动泵从第一罐泵送通过第一进料回路。

公开(公告)号：US20160169159A1

公开(公告)日：2016-06-16

申请号：US14909945

申请日：2014-07-25

Applicant: SNECMA

Inventor： Gérard ROZ ,  David HAYOUN ,  Didier VUILLAMY ,  François LASSOUDIERE

IPC: F02K9/44 ,  F02K9/42 ,  F02K9/60

CPC classification number: F02K9/44 ,  F02K9/425 ,  F02K9/50 ,  F02K9/605 ,  F05D2220/80 ,  F05D2260/20

Abstract: The device comprises a primary heater (58) suitable for heating the propellant coming from the tank (16) prior to it being reintroduced into its tank. The primary heater uses the heat of combustion from the engine (10) and the device further comprises a secondary heater (66) having its source of heat independent from the operation of the engine, the secondary heater being arranged downstream from the primary heater (58) in order to heat the propellant between its outlet from the primary heater and being reintroduced into the tank. The device also has means (62) between the feed to the primary heater (58) and the return of the propellant to the tank for putting the propellant under pressure.

Abstract translation: 该装置包括一个主加热器（58），适用于在其被重新引入其罐内之前加热来自罐（16）的推进剂。 主加热器使用来自发动机（10）的燃烧热，并且该装置还包括二次加热器（66），其二次加热器的热源独立于发动机的操作，二次加热器布置在主加热器（58）的下游 ），以便将推进剂在其来自主加热器的出口之间加热并重新引入罐中。 该装置还具有在进给到第一加热器（58）的进料和将推进剂返回到罐之间以将推进剂置于压力下的装置（62）。

公开(公告)号：US20160341362A1

公开(公告)日：2016-11-24

申请号：US15111989

申请日：2014-12-31

Applicant: SNECMA

Inventor： Didier VUILLAMY ,  Nicolas RAVIER ,  David HAYOUN

IPC: F17C13/00

CPC classification number: F17C13/001 ,  F17C13/088 ,  F17C2201/0104 ,  F17C2201/032 ,  F17C2201/054 ,  F17C2205/0115 ,  F17C2205/0126 ,  F17C2205/0176 ,  F17C2205/018 ,  F17C2221/012 ,  F17C2221/08 ,  F17C2223/0161 ,  F17C2223/033 ,  F17C2227/0341 ,  F17C2227/0386 ,  F17C2260/031 ,  F17C2260/032 ,  F17C2270/0197 ,  Y02E60/321

Abstract: An assembly including a cryogenic fluid tank for a space vehicle and a thermal protection system for a cryogenic fluid tank of the space vehicle, the system including: a shell adapted to surround the cryogenic fluid tank, the shell being dimensioned to define an inside space between the shell and the tank; and an injector for injecting a cooling fluid spray into the inside space; the cooling fluid being injected into the inside space in the liquid state at a temperature that is adapted to ensure that the cooling fluid picks up the heat flux reaching the cryogenic fluid tank, thereby causing the cooling fluid to vaporize, the shell having a plurality of orifices adapted to allow the cooling fluid in gaseous form to leave inside space through the shell.

Abstract translation: 一种组件，包括用于空间飞行器的低温流体箱和用于空间载体的低温流体箱的热保护系统，所述系统包括：适于围绕低温流体箱的壳体，壳体的尺寸被设计成在 壳和油箱; 以及用于将冷却流体喷射注入到所述内部空间中的喷射器; 冷却流体以适于确保冷却流体拾取到达低温流体箱的热通量从而导致冷却流体蒸发的温度而以液态注入到内部空间中，壳体具有多个 适于允许气体形式的冷却流体通过壳体离开内部空间的孔。

公开(公告)号：US20160222918A1

公开(公告)日：2016-08-04

申请号：US15024466

申请日：2014-09-18

Applicant: SNECMA

Inventor： Gérard ROZ ,  David HAYOUN ,  Nicolas RAVIER

IPC: F02K9/42 ,  F02K9/44

CPC classification number: F02K9/425 ,  F02K9/44 ,  F02K9/50 ,  F02K9/94

Abstract: A propulsion assembly (1, 201) for a rocket, comprising a tank (2) configured to contain a propellant, an engine having a combustion chamber (9), a propellant feed pipe (11) extending between the tank (2) and the combustion chamber (9) and having an isolation valve (24) arranged therein, and a heater (15) having an inlet connected to the feed pipe (11) and an outlet connected to the tank (2). The inlet of the heater comprises an inlet pipe (13a) connected firstly to the feed pipe (11) downstream from the isolation valve (24) and secondly to a neutral fluid feed (31).

Abstract translation: 一种用于火箭的推进组件（1,201），包括构造成容纳推进剂的罐（2），具有燃烧室（9）的发动机，在所述罐（2）和所述燃料室 燃烧室（9）并且具有布置在其中的隔离阀（24），以及具有连接到进料管（11）的入口和连接到罐（2）的出口的加热器（15）。 加热器的入口包括入口管（13a），其首先连接到隔离阀（24）下游的进料管（11），其次连接到中性流体进料（31）。

公开(公告)号：US20140283499A1

公开(公告)日：2014-09-25

申请号：US13904584

申请日：2013-05-29

Applicant: SNECMA

Inventor： Jean Michel SANNINO ,  Emmanuel EDELINE ,  David HAYOUN

IPC: F02K9/44

CPC classification number: F02K9/44 ,  F02K9/46 ,  F02K9/605

Abstract: The invention relates to a device and a method for feeding a propulsion chamber 5 of a rocket engine 1 with at least with a first propellant. The device comprises at least a first tank 2 for containing said first propellant, a first feed circuit 4 connected to the first tank 2, and a first electric pump 10 within said first tank 2 in order to pump said first propellant through the first feed circuit 4. In the method, the first propellant is pumped through the first feed circuit 4 from the first tank 2 by at least said first electric pump 10 that is immersed in the first propellant within the first tank 2.

Abstract translation: 本发明涉及一种用于至少与第一推进剂一起供给火箭发动机1的推进室5的装置和方法。 该装置至少包括用于容纳所述第一推进剂的第一罐2，连接到第一罐2的第一进料回路4和在所述第一罐2内的第一电泵10，以便通过第一进料回路泵送第一推进剂 在该方法中，第一推进剂通过至少浸入第一罐2中的第一推进剂的第一电动泵10从第一罐2泵送通过第一进料回路4。