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

IPC: F02K9/50 ,  F02K9/60 ,  F28D7/00

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.

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。

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.