Rocket propulsion system and method for operating a rocket propulsion system

Patent metadata

Field	Value
Publication number	US-10968865-B2
Application number	US-201715597922-A
Country	US
Kind code	B2
Filing date	May 17, 2017
Priority date	May 20, 2016
Publication date	Apr 6, 2021
Grant date	Apr 6, 2021

Abstract

A rocket propulsion system comprises a combustion chamber, an oxygen supply system, comprising an oxygen supply duct and being configured to supply oxygen to the combustion chamber, and a hydrogen supply system, comprising a hydrogen supply duct and being configured to supply hydrogen to the combustion chamber. An ignition unit of the propulsion system, to which at least portions of the oxygen and the hydrogen supplied to the combustion chamber can be supplied, is configured to initiate combustion of the oxygen-hydrogen mixture in the combustion chamber. The propulsion system further comprises a cooling duct extending along an inner surface of a combustion chamber wall and through which at least a portion of the oxygen supplied to the combustion chamber, at least a portion of the hydrogen supplied to the combustion chamber or a combustion gas mixture emerging from the ignition unit flows.

First claim

The invention claimed is:

1. A rocket propulsion system comprising: a combustion chamber;
an oxygen supply system, which comprises an oxygen supply duct and is configured to supply oxygen to the combustion chamber;
a hydrogen supply system, which comprises a hydrogen supply duct and is configured to supply hydrogen to the combustion chamber;
an ignition unit, to which at least a portion of the oxygen supplied to the combustion chamber and at least a portion of the hydrogen supplied to the combustion chamber is configured to be supplied and which is configured to initiate combustion of the oxygen-hydrogen mixture in the combustion chamber, wherein the ignition unit comprises a catalyst chamber and a premixing chamber for premixing the portion of oxygen supplied to the ignition unit and the portion of hydrogen supplied to the ignition unit prior to supplying the oxygen-hydrogen mixture to the catalyst chamber, wherein the premixing chamber is arranged upstream of an entrance area to the catalyst chamber, and wherein a flow cross section of the premixing chamber for the gases to be supplied to the catalyst chamber becomes larger in a direction of the entrance area of the catalyst chamber, and
a cooling duct, which extends along an inner surface of a combustion chamber wall wherein the cooling duct comprises a section, which extends between an outer surface of the ignition unit and a section of the inner surface of the combustion chamber wall lying opposite an outer surface of the ignition unit and opens into the combustion section of the combustion chamber arranged downstream of an exit area of the ignition unit, wherein a swirler is arranged in said section of the cooling duct and wherein the cooling duct is configured to be flown through with one of
at least a portion of the oxygen supplied to the combustion chamber from the oxygen supply duct, wherein the oxygen supply duct extends along the inner surface of the combustion chamber wall such that the section of the cooling duct extends from the oxygen supply duct;
at least a portion of the hydrogen supplied to the combustion chamber from the hydrogen supply duct, wherein the hydrogen supply duct extends along the inner surface of the combustion chamber wall such that the section of the cooling duct extends from the hydrogen supply duct; or
a combustion gas mixture emerging from the ignition unit; and

wherein an oxygen supply opening for supplying oxygen to the premixing chamber is formed in a wall of the premixing chamber that at least partially defines the oxygen supply duct; or
a hydrogen supply opening for supplying hydrogen to the premixing chamber is formed in a wall of the premixing chamber that at least partially defines the hydrogen supply duct.

2. The rocket propulsion system according to claim 1 , wherein the cooling duct comprises a further section, which extends in a combustion section of the combustion chamber arranged downstream of the exit area of the ignition unit along the inner surface of the combustion chamber wall.

3. The rocket propulsion system according to claim 1 , wherein at least one of:
the section of the cooling duct is connected to the oxygen supply dud of the oxygen supply system or the hydrogen supply duct of the hydrogen supply system, or
a plurality of individual flow paths, through which a parallel flow is possible, are provided in the cooling duct.

4. The rocket propulsion system according to claim 3 , wherein
the oxygen supply duct or the hydrogen supply duct open into the section of the cooling duct, or
the section of the cooling duct branches off from the oxygen supply duct or the hydrogen supply duct and runs along at least a partial area parallel to the oxygen supply duct or the hydrogen supply duct.

5. The rocket propulsion system according to claim 1 , wherein:
a flashback arrestor is arranged in the region of an entrance area to the catalyst chamber; or
the hydrogen supply duct for supplying hydrogen to the premixing chamber opens into the premixing chamber.

6. The rocket propulsion system according to claim 1 , wherein a core duct passes through the ignition unit, at least in sections, which the core duct is connected to the oxygen supply duct of the oxygen supply system.

7. The rocket propulsion system according to claim 6 , wherein the oxygen supply duct opens into the core duct.

8. The rocket propulsion system according to claim 1 , further comprising:
a control unit configured to control the oxygen supply system and the hydrogen supply system so that the rocket propulsion system is operated alternately in a first operating mode, in which oxygen and hydrogen are supplied to the combustion chamber in a first mass mixing ratio of oxygen to hydrogen, and in a second operating mode, in which oxygen and hydrogen are supplied to the combustion chamber in a second mass mixing ratio of oxygen to hydrogen that is greater than the first mass mixing ratio.

9. A method for operating a rocket propulsion system, comprising:
supplying oxygen to a combustion chamber via an oxygen supply duct;
supplying hydrogen to the combustion chamber via a hydrogen supply duct;
conducting at least a portion of the oxygen supplied to the combustion chamber and at least a portion of the hydrogen supplied to the combustion chamber into an ignition unit, wherein the ignition unit comprises a catalyst chamber and a premixing chamber for premixing the portion of oxygen supplied to the ignition unit and the portion of hydrogen supplied to the ignition unit prior to supplying the oxygen-hydrogen mixture to the catalyst chamber, wherein the premixing chamber is arranged upstream of an entrance area to the catalyst chamber, and wherein a flow cross section of the premixing chamber for the gases to be supplied to the catalyst chamber becomes larger in a direction of the entrance area of the catalyst chamber;
initiation of combustion of the oxygen-hydrogen mixture in the combustion chamber via the ignition unit; and
conducting at least a portion of the oxygen supplied to the combustion chamber, at least a portion of the hydrogen supplied to the combustion chamber, or a combustion gas mixture emerging from the ignition unit through a cooling duct, the cooling duct extending along an inner surface of a combustion chamber wall;
wherein the cooling duct comprises a section, which extends between an outer surface of the ignition unit and a section of the inner surface of the combustion chamber wall lying opposite an outer surface of the ignition unit and opens into the combustion section of the combustion chamber arranged downstream of an exit area of the ignition unit, wherein a swirler is arranged in said section of the cooling duct; and
wherein an oxygen supply opening for supplying oxygen to the premixing chamber is formed in a wall of the premixing chamber at least partly defining, the oxygen supply duct and wherein the oxygen supply duct extends along the inner surface of the combustion chamber such that the section of the cooling duct extends from the oxygen supply duct; or
a hydrogen supply opening for supplying hydrogen to the premixing chamber is formed in a wall of the premixing chamber at least partly defining the hydrogen supply duct and wherein the hydrogen supply duct extends along the inner surface of the combustion chamber such that the section of the cooling duct extends from the hydrogen supply duct.

10. The method according to claim 9 , wherein
the cooling duct comprises a first section, which extends in a combustion section of the combustion chamber arranged downstream of the exit area of the ignition unit along the inner surface of the combustion chamber wall.

11. The method according to claim 9 , wher

Assignees

• Airbus Ds Gmbh
• Arianegroup Gmbh

Inventors

• Gotzig Ulrich
• Wurdak Malte
• Deck Joel
• Frey Manuel

Classifications

• F02K9/68

  Decomposition chambers · CPC title

• F05D2260/202

  by film cooling · CPC title

• F02K9/64 Primary

  having cooling arrangements · CPC title

• F05D2220/80

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

• F02K9/58

  Propellant feed valves · CPC title