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：US20160290284A1

公开(公告)日：2016-10-06

申请号：US15037780

申请日：2014-11-14

Applicant: SNECMA

Inventor： Antoine CARATGE ,  Gérard ROZ

IPC: F02K9/50 ,  F02K9/58

CPC classification number: F02K9/50 ,  F02C9/263 ,  F02K9/56 ,  F02K9/58 ,  F05B2240/40

Abstract: A feed device (20) for feeding propellant to at least one rocket engine propulsion chamber (19) of a propulsion assembly (21) comprises a main propellant tank (1, 2), and a main feed pipe (3, 4) extending between the main tank (1, 2) and the propulsion chamber (19) and having a main feed valve (VAH, VAO) placed thereon. The feed device further comprises an auxiliary tank (11, 12) for said propellant and an auxiliary feed pipe (13, 14) provided with an auxiliary feed valve (VH1, VO1) connecting the auxiliary tank (11, 12) to the main feed pipe (3, 4) downstream from the main feed valve (VAH, VAO).

Abstract translation: 一种用于将推进剂输送到推进组件（21）的至少一个火箭发动机推进室（19）的进料装置（20）包括主推进剂罐（1,2）和主进料管（3,4） 主舱（1,2）和推进室（19），并具有主进给阀（VAH，VAO）。 进料装置还包括用于所述推进剂的辅助罐（11,12）和设有辅助进料阀（VH1，VO1）的辅助进料管（13,14），其将辅助罐（11,12）连接到主进料 主管（VAH，VAO）下游的管道（3,4）。

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：US20160177874A1

公开(公告)日：2016-06-23

申请号：US14909894

申请日：2014-07-25

Applicant: SNECMA

Inventor： Gérard ROZ ,  Lauren NGUYEN DUC ,  Stéphanie DREYER ,  Nicolas RAVIER

IPC: F02K9/50 ,  F02K9/94

Abstract: The device comprises two heat exchangers (74, 90) suitable respectively for vaporizing first and second propellants before they are reintroduced in gaseous form into their tanks (16, 18). The heat exchangers co-operate respectively with first and second gas generators (60, 84) suitable for being fed with a mixture of propellants in order to produce combustion, the second gas generator (84) being suitable for being fed at least in part by the exhaust from the first gas generator (60).

Abstract translation: 该装置包括两个热交换器（74,90），它们分别适于在将第一和第二推进剂以气态重新引入其储罐（16,18）之前蒸发。 所述热交换器分别与适于供给燃料混合物的第一和第二气体发生器（60,84）配合以产生燃烧，所述第二气体发生器（84）适于至少部分地由 来自第一气体发生器（60）的排气。

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。