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

IPC: F17D3/01 ,  F16L53/00

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。

公开(公告)号：US10371098B2

公开(公告)日：2019-08-06

申请号：US14909945

申请日：2014-07-25

Applicant: SNECMA

Inventor： Gérard Roz ,  David Hayoun ,  Didier Vuillamy ,  François Lassoudiere

IPC: F02K9/50 ,  F02K9/44 ,  F02K9/42 ,  F02K9/60

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.

公开(公告)号：US10072610B2

公开(公告)日：2018-09-11

申请号：US14440835

申请日：2013-11-04

Applicant: SNECMA

Inventor： Jean Michel Sannino ,  François Lassoudiere ,  David Hayoun

IPC: F02K9/48 ,  F02K9/50 ,  F02K9/97 ,  F02K9/64

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

Abstract: The invention relates to a feed device for feeding a thrust chamber (10) of a rocket engine (100) with first and second propellants. According to the invention, a first feed circuit (16) of the thrust chamber (10) comprises a turbopump (22) having at least one pump (22a) for pumping the first propellant from a first tank (12), and a turbine (22b) mechanically coupled to said pump (22a). The first feed circuit connects an outlet of the pump to an inlet of the turbine via a heat exchanger (24) configured to heat the first propellant with heat generated by the thrust chamber, in order to actuate the turbine. According to the invention, a second feed circuit (18) is configured to feed the thrust chamber with second propellant from a second tank (14) that is configured to be pressurized. The invention also provides a method of feeding a rocket engine thrust chamber with first and second propellants.

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

IPC: F17D1/16 ,  F17D3/01 ,  F02K9/50 ,  F17C5/00 ,  F16L53/00 ,  F02K9/48

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。

公开(公告)号：US20150285187A1

公开(公告)日：2015-10-08

申请号：US14440835

申请日：2013-11-04

Applicant: SNECMA

Inventor： Jean Michel Sannino ,  François Lassoudiere ,  David Hayoun

IPC: F02K9/48 ,  F02K9/50

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

Abstract: The invention relates to a feed device for feeding a thrust chamber (10) of a rocket engine (100) with first and second propellants. According to the invention, a first feed circuit (16) of the thrust chamber (10) comprises a turbopump (22) having at least one pump (22a) for pumping the first propellant from a first tank (12), and a turbine (22b) mechanically coupled to said pump (22a). The first feed circuit connects an outlet of the pump to an inlet of the turbine via a heat exchanger (24) configured to heat the first propellant with heat generated by the thrust chamber, in order to actuate the turbine. According to the invention, a second feed circuit (18) is configured to feed the thrust chamber with second propellant from a second tank (14) that is configured to be pressurized. The invention also provides a method of feeding a rocket engine thrust chamber with first and second propellants.

Abstract translation: 本发明涉及一种用于向第一和第二推进剂供给火箭发动机（100）的推力室（10）的进料装置。 根据本发明，推力室（10）的第一供给回路（16）包括涡轮泵（22），其具有用于从第一罐（12）泵送第一推进剂的至少一个泵（22a）和涡轮（ 22b），其机械地联接到所述泵（22a）。 第一进料回路经由热交换器（24）将泵的出口连接到涡轮机的入口，热交换器（24）构造成通过由推力室产生的热量来加热第一推进剂，以便致动涡轮机。 根据本发明，第二进料回路（18）构造成从第二罐（14）向推进室供给第二推进剂，第二罐被构造成被加压。 本发明还提供了一种向第一和第二推进剂供给火箭发动机推力室的方法。

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。