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公开(公告)号：US20140245717A1
公开(公告)日：2014-09-04
申请号：US14349820
申请日：2012-10-09
Applicant: SNECMA
Inventor： Didier Vuillamy , Jean-Luc Barthoulot , Jean-Michel Sannino
CPC classification number: F02K9/50 , F02K9/60 , F23C6/04 , F23C2201/40 , F23C2201/401 , F23C2900/06041 , F28D7/00 , F28D7/06 , F28D7/1615 , F28D2021/0026 , F28F1/16 , F28F1/36 , F28F9/22
Abstract: A device heating a fluid and usable in a rocket launcher to pressurize a liquefied propellant. The device includes a first burner performing first combustion between a limiting propellant and an excess propellant; a first heat exchanger in which first burnt gas from the first combustion transfers heat to the fluid; at least one second burner into which both the first burnt gas and some limiting propellant are injected to perform second combustion between the limiting propellant and at least a portion of unburnt excess propellant present in the first burnt gas. The second burnt gas from the second combustion flows through a second heat exchanger to transfer heat to the fluid. Burnt gas from each combustion flows in respective burnt gas tubes within a common overall heat exchanger including the heat exchange units, the gas transferring heat to the fluid, the fluid flowing between the burnt gas tubes.
Abstract translation: 一种加热流体并可用于火箭发射器以对液化推进剂加压的装置。 该装置包括在限制推进剂和过量推进剂之间执行第一燃烧的第一燃烧器; 第一热交换器，其中来自第一燃烧的第一燃烧气体将热量传递到流体; 至少一个第二燃烧器，其中喷射第一燃烧气体和一些限制性推进剂，以在第一燃烧气体中存在的限制推进剂和至少一部分未燃烧的过量推进剂之间进行第二燃烧。 来自第二燃烧的第二燃烧气体流过第二热交换器以将热量传递给流体。 来自每个燃烧的燃烧气体在包括热交换单元，向流体传输热的气体，在燃烧气体管之间流动的流体的气体的公共整体热交换器内的各个燃烧气体管中流动。
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公开(公告)号：US10082106B2
公开(公告)日：2018-09-25
申请号：US14760190
申请日：2014-01-10
Applicant: SNECMA
Inventor： Didier Vuillamy , Gérard Roz
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.
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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
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.
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公开(公告)号：US09803589B2
公开(公告)日：2017-10-31
申请号：US14349820
申请日：2012-10-09
Applicant: SNECMA
Inventor： Didier Vuillamy , Jean-Luc Barthoulot , Jean-Michel Sannino
IPC: F02K9/50 , F23C6/04 , F28F9/22 , F28D7/06 , F28F1/16 , F28F1/36 , F28D7/16 , F02K9/60 , F28D7/00 , F28D21/00
CPC classification number: F02K9/50 , F02K9/60 , F23C6/04 , F23C2201/40 , F23C2201/401 , F23C2900/06041 , F28D7/00 , F28D7/06 , F28D7/1615 , F28D2021/0026 , F28F1/16 , F28F1/36 , F28F9/22
Abstract: A device heating a fluid and usable in a rocket launcher to pressurize a liquefied propellant. The device includes a first burner performing first combustion between a limiting propellant and an excess propellant; a first heat exchanger in which first burnt gas from the first combustion transfers heat to the fluid; at least one second burner into which both the first burnt gas and some limiting propellant are injected to perform second combustion between the limiting propellant and at least a portion of unburnt excess propellant present in the first burnt gas. The second burnt gas from the second combustion flows through a second heat exchanger to transfer heat to the fluid. Burnt gas from each combustion flows in respective burnt gas tubes within a common overall heat exchanger including the heat exchange units, the gas transferring heat to the fluid, the fluid flowing between the burnt gas tubes.
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