Jet propulsion device and fuel supply method

Patent metadata

Field	Value
Publication number	US-9771897-B2
Application number	US-201214350980-A
Country	US
Kind code	B2
Filing date	Oct 8, 2012
Priority date	Oct 11, 2011
Publication date	Sep 26, 2017
Grant date	Sep 26, 2017

Abstract

A reaction propulsion device in which a first feed circuit for feeding a main thruster with a first propellant includes a branch connection downstream from a pump of a first turbopump, which branch connection passes through a first regenerative heat exchanger and a turbine of a first turbopump, and in which a second feed circuit for feeding the main thruster with a second propellant includes, downstream from a pump of a second turbopump, a branch-off passing through a second regenerative heat exchanger and a turbine of the second turbopump. At least one secondary thruster is connected downstream from the turbines of the first and second turbopumps.

First claim

The invention claimed is:

1. A reaction propulsion device comprising: a main thruster including a propulsion chamber; a first feed circuit including a first turbopump including at least a first turbine coupled to a first pump, a first main line connected to the first pump downstream of the first pump that delivers a first propellant to the propulsion chamber of the main thruster, and a first branch-off from the first main line; and a second feed circuit including a second turbopump including at least a second turbine coupled to a second pump, a second main line connected to the second pump downstream of the second pump that delivers a second propellant to the propulsion chamber of the main thruster and a second branch-off from the second main line, wherein the propulsion chamber of the main thruster is a regenerative propulsion chamber, including a first heat exchanger and a second heat exchanger, wherein the first branch-off passes through the first heat exchanger and the first turbine of the first turbopump, and the second branch-off passes through the second heat exchanger and the second turbine of the second turbopump, and further comprising at least one secondary thruster connected to the first and second branch-offs downstream from the first and second turbines of the first and second turbopumps.

2. The reaction propulsion device according to claim 1 , further comprising valves interposed between each of the first and second turbines and the at least one secondary thruster.

3. The reaction propulsion device according to claim 1 , comprising a plurality of secondary thrusters connected downstream from each of the first and second turbines of the first and second turbopumps.

4. The reaction propulsion device according to claim 1 , wherein the first heat exchanger and/or the second heat exchanger is/are incorporated in an outer wall of the propulsion chamber.

5. The reaction propulsion device according to claim 4 , wherein the first and/or second heat exchanger incorporated in the outer wall of the propulsion chamber includes at least one propellant duct adjacent to an outer side of the wall.

6. A space launcher comprising at least one reaction propulsion device according to claim 1 .

7. A propellant feed method for feeding propellants to a reaction propulsion device, the method comprising: delivering a first main flow of a first propellant to a propulsion chamber of a main thruster via a first main line of a first feed circuit in which the first propellant is pumped by a first pump of a first turbopump wherein the first main line is connected to the first pump downstream of the first pump; delivering a second main flow of a second propellant to the propulsion chamber of the main thruster via a second main line of a second feed circuit in which the second propellant is pumped by a second pump of a second turbopump wherein the second main line is connected to the second pump downstream of the second pump; diverting a first secondary flow of the first propellant via a first branch-off from the first main line carrying the main flow of the first propellant, heating the first secondary flow by the propulsion chamber of the main thruster in a first heat exchanger, and expanding the first secondary flow in a first turbine driving the first turbopump; diverting a second secondary flow of the second propellant via a second branch-off from the second main line carrying the main flow of the second propellant, heating the second secondary flow by the propulsion chamber of the main thruster in a second heat exchanger, and expanding the second secondary flow in a second turbine driving the second turbopump; and delivering the first and second secondary flows of the first and second propellants, after the secondary flows have expanded in the first and second turbines of the first and second turbopumps, to at least one secondary thruster.

8. The propellant feed method according to claim 7 , wherein thrust from the at least one secondary thruster is used for steering.

9. The propellant feed method according to claim 7 , wherein the propellant flows delivered to the at least one secondary thruster are regulated by valves interposed between each of the first and second turbines and the at least one secondary thruster.

10. The propellant feed method according to claim 7 , wherein the first and/or second propellant is/are liquid upstream from the first and/or second heat exchanger, and gaseous downstream.

Assignees

• Snecma

Inventors

• Soulier Nicolas
• Brochard Bruno
• Sannino Jean-Michel

Classifications

• F02K9/64

  having cooling arrangements · CPC title

• F02K9/88

  using auxiliary rocket nozzles · CPC title

• F02K9/48 Primary

  driven by a gas turbine fed by propellant combustion gases {or fed by vaporized propellants or other gases} · CPC title

• B64G1/002

  Launch systems · CPC title

• B64G1/402

  Propellant tanks; Feeding propellants · CPC title