Device for pressurizing a propellant tank of a rocket engine

Patent metadata

Field	Value
Publication number	US-2016169159-A1
Application number	US-201414909945-A
Country	US
Kind code	A1
Filing date	Jul 25, 2014
Priority date	Aug 6, 2013
Publication date	Jun 16, 2016
Grant date	—

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.

First claim

1 . A pressurization device for pressurizing a propellant tank of a rocket engine, the device comprising a pressurization loop having a primary heater suitable for heating the propellant coming from the tank prior to it being reintroduced into the tank, the primary heater using the heat of combustion from the engine, the device further including a secondary heater having its source of heat independent from the operation of the engine, the secondary heater being arranged downstream from the primary heater to heat the propellant between the propellant leaving the primary heater and being reintroduced into the tank, the propellant being put under pressure in the pressurization loop.

2 . A device as claimed in claim 1 , wherein the secondary heater is an electric heater.

3 . A device as claimed in claim 1 , wherein the outlet from the secondary heater is suitable for being connected to an ejection pipe.

4 . A device as claimed in claim 1 , including a motor-driven pump arranged upstream from the primary heater.

5 . A propulsion assembly including a device as claimed in claim 1 for pressurizing a first tank containing a first propellant, a rocket engine fed by said first propellant and by a second propellant coming from a second tank, and a regenerator circuit for said second propellant, this circuit including a regenerative heat exchanger that co-operates with the engine to heat the second propellant prior to being reintroduced into the second tank, the primary heater co-operating with an outlet pipe of the regenerative heat exchanger.

6 . An assembly as claimed in claim 5 , wherein the primary heater comprises at least one tube immersed in the outlet pipe.

7 . An assembly as claimed in claim 5 , including an auxiliary circuit for pressurizing the second tank without using the heat of combustion from the engine.

Assignees

• Snecma

Inventors

• Roz Gérard
• Hayoun David
• Vuillamy Didier
• Lassoudiere François

Classifications

• B64G1/401

  Liquid propellant rocket engines (Ion or plasma engines B64G1/413; Arcjets and other resistojets B64G1/415) · CPC title

• B64G1/402

  Propellant tanks; Feeding propellants · CPC title

• F02K9/44 Primary

  Feeding propellants · CPC title

• F05D2220/80

  in supersonic vehicles excluding hypersonic vehicles or ram, scram or rocket propulsion · CPC title

• F02K9/425 Primary

  Propellants · CPC title