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：US20150354505A1

公开(公告)日：2015-12-10

申请号：US14760175

申请日：2014-01-10

Applicant: SNECMA

Inventor： Didier VUILLAMY ,  Gérard ROZ

IPC: F02K9/60

CPC classification number: F02K9/60 ,  F02K9/40 ,  F02K9/46 ,  F02K9/605 ,  F02K9/64 ,  F02K9/972 ,  F05D2260/20 ,  F05D2260/205

Abstract: The invention relates to the aerospace field, and in particular to the field of vehicles propelled by rocket engines. In particular, the invention relates to a feed circuit (6) for feeding a rocket engine (2) at least with a first liquid propellant, the feed circuit including at least one buffer-tank (20) for said first liquid propellant and a first heat exchanger (18) that is incorporated in said buffer tank (20) and suitable for being connected to a cooling circuit (17) for cooling at least one heat source in order to cool said heat source by transferring heat to the first propellant.

Abstract translation: 本发明涉及航空航天领域，特别涉及由火箭发动机推进的车辆领域。 特别地，本发明涉及用于至少用第一液体推进剂供给火箭发动机（2）的进料回路（6），所述进料回路包括用于所述第一液体推进剂的至少一个缓冲罐（20）和第一液体推进剂 热交换器（18），其结合在所述缓冲罐（20）中并且适于连接到用于冷却至少一个热源的冷却回路（17），以便通过将热传递到第一推进剂来冷却所述热源。

公开(公告)号：US20150354503A1

公开(公告)日：2015-12-10

申请号：US14760186

申请日：2014-01-08

Applicant: SNECMA

Inventor： Didier VUILLAMY ,  Gérard ROZ

IPC: F02K9/46 ,  F02K9/52 ,  F02K9/60

CPC classification number: F02K9/46 ,  F02K9/50 ,  F02K9/52 ,  F02K9/60 ,  F02K9/972

Abstract: The invention relates to the field of rocket engines, and more particularly to a system for feeding a rocket engine (2) with propellant, the system comprising a first tank (3), a second tank (4), a first feed circuit (6) connected to the first tank (3), and a second feed circuit (7) connected to the second tank (4). In order to cool the propellant contained in the second tank (4), the first circuit (6) includes a branch (12) passing through a first heat exchanger (14) incorporated in the second tank (4). The invention also provides a method of feeding the rocket engine (2).

Abstract translation: 本发明涉及火箭发动机领域，更具体地说，涉及一种用于向火箭发动机（2）供给推进剂的系统，所述系统包括第一罐（3），第二罐（4），第一进料回路（6） ）和连接到第二罐（4）的第二供给回路（7）。 为了冷却包含在第二罐（4）中的推进剂，第一回路（6）包括通过结合在第二罐（4）中的第一热交换器（14）的分支（12）。 本发明还提供一种喂食火箭发动机（2）的方法。

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：US20150337763A1

公开(公告)日：2015-11-26

申请号：US14760190

申请日：2014-01-10

Applicant: SNECMA

Inventor： Didier VUILLAMY ,  Gérard ROZ

IPC: F02K9/46

CPC classification number: F02K9/60 ,  F02K9/40 ,  F02K9/46 ,  F02K9/605 ,  F02K9/64 ,  F02K9/972 ,  F05D2260/20 ,  F05D2260/205

Abstract: The invention relates to the aerospace field, and in particular to the field of vehicles propelled by rocket engines. In particular, the invention relates to a feed circuit (6) for feeding a rocket engine (2) at least with a first liquid propellant, the feed circuit including at least one first heat exchanger (18) suitable for being connected to a cooling circuit (17) for cooling at least one heat source in order to cool said heat source by transferring heat to the first propellant, and, in addition, downstream from said first heat exchanger, a branch passing through a second heat exchanger.

Abstract translation: 本发明涉及航空航天领域，特别涉及由火箭发动机推进的车辆领域。 特别地，本发明涉及用于至少用第一液体推进剂进给火箭发动机（2）的进料回路（6），所述进料回路包括至少一个第一热交换器（18），该第一热交换器适于连接到冷却回路 （17），用于冷却至少一个热源，以便通过将热量传递到第一推进剂来冷却所述热源，并且另外在所述第一热交换器的下游，通过第二热交换器的分支。