Propulsion assembly and method

Patent metadata

Field	Value
Publication number	US-9249758-B2
Application number	US-201313771562-A
Country	US
Kind code	B2
Filing date	Feb 20, 2013
Priority date	Feb 21, 2012
Publication date	Feb 2, 2016
Grant date	Feb 2, 2016

Abstract

The invention relates to the field of aerospace propulsion, and more particularly to a propulsion assembly having at least one channel defined by an inner wall and an outer wall, the channel presenting an inlet opening and an outlet opening, the assembly including a plurality of rocket engines oriented axially in the channel and forming ejectors for accelerating a flow of air in the channel to supersonic speed. Downstream from the outlet opening from the channel, the inner wall forms a single expansion ramp nozzle. The invention also provides an aerospace craft and a method of propulsion using such a propulsion assembly.

First claim

What is claimed is:

1. A propulsion assembly comprising at least:
a channel defined by an inner wall and an outer wall and presenting an inlet opening and an outlet opening, said inner wall forming, downstream from said outlet opening of the channel, a single expansion ramp nozzle;
a plurality of rocket engines oriented in an axial direction in the channel and forming ejectors for accelerating a flow of air in the channel to a supersonic speed;
turbopumps for feeding oxidizer and fuel, said turbopumps being situated axially downstream from said outlet opening of the channel on the inside of said inner wall; and
a gas generator for actuating said turbopumps.

2. A propulsion assembly according to claim 1 , wherein at least portions of said inner and outer walls form pervious screens for passing the pressurized fuel-rich gas.

3. A propulsion assembly according to claim 2 , wherein said gas generator is configured to generate a fuel-rich gas mixture for feeding said rocket engines and/or said pervious screen after actuating said turbopumps.

4. A propulsion assembly according to claim 1 , wherein said channel is annular.

5. A propulsion assembly according to claim 1 , further including a plurality of masts, each connecting together said inner and outer walls, and having said rocket engines incorporated therein.

6. A propulsion assembly according to claim 1 , wherein said propellants are cryogenic.

7. A propulsion assembly according to claim 1 , including a ground-to-vehicle interface in a downstream end of the propulsion assembly that is suitable for receiving a delivery of external energy for starting said turbopumps.

8. A propulsion assembly according to claim 7 , wherein said ground-to-vehicle interface is suitable for receiving a flow of pressurized fuel for actuating said turbopumps on starting.

9. A propulsion assembly according to claim 1 , wherein each of said rocket engines comprises:
a tubular body provided internally with a coaxial wall forming a pervious screen defining an annular fuel-injection zone that extends over the major fraction of the length of said tubular wall; and
an oxidizer injector opening out axially to the inside of said pervious screen close to its front end.

10. A propulsion assembly according to claim 1 , further including at least one flap for closing the inlet opening of the channel.

11. An aerospace craft including a propulsion assembly according to claim 1 .

Assignees

• Snecma

Inventors

• Conrardy Jean Marie

Classifications

• F02K9/52

  Injectors · CPC title

• F02K7/18 Primary

  Composite ram-jet/rocket engines · 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