Propulsion chamber with reinforcing fiber belts and a method of fabricating the propulsion chamber

Patent metadata

Field	Value
Publication number	US-10451006-B2
Application number	US-201615296537-A
Country	US
Kind code	B2
Filing date	Oct 18, 2016
Priority date	Oct 20, 2015
Publication date	Oct 22, 2019
Grant date	Oct 22, 2019

Abstract

A propulsion chamber for a liquid propellant rocket engine is provided. The propulsion chamber includes an inside wall made of metal, an outside covering made of organic matrix composite material, and a cooling circuit arranged between the outside covering and the inside wall. The propulsion chamber further includes at least a first axial endpiece secured to the metal inside wall and presenting at least one radial protrusion received in a concave recess in an inside face of the outside covering. The concave recess is situated axially between first and second belts of reinforcing fibers oriented substantially circumferentially in the outside covering in such a manner as to take up forces associated with inside pressure and thrust.

First claim

The invention claimed is:

1. A propulsion chamber for a liquid propellant rocket engine, the propulsion chamber having an axial centerline and comprising:
an inside wall made of metal;
an outside covering made of organic matrix composite material;
a cooling circuit; and
a first axial endpiece secured to a first end of the inside wall made of metal and comprising a first radial protrusion received in a first concave recess in an inside face of the outside covering, the concave recess being situated axially between a first belt of reinforcing fibers and a second belt of reinforcing fibers, the first belt of reinforcing fibers and the second belt of reinforcing fibers being oriented substantially circumferentially in said outside covering.

2. The propulsion chamber according to claim 1 , wherein said organic matrix composite material includes other reinforcing fibers made of carbon.

3. The propulsion chamber according to claim 1 , wherein said first belt of reinforcing fibers and second belt of reinforcing fibers surround at least one inner layer of the outside covering.

4. The propulsion chamber according to claim 1 , wherein said first belt of reinforcing fibers and second belt of reinforcing fibers are prestressed in tension.

5. The propulsion chamber according to claim 1 , wherein the first radial protrusion extends around a perimeter of the first axial endpiece.

6. The propulsion chamber according to claim 1 , wherein the inside wall defines a throat of a convergent-divergent nozzle.

7. The propulsion chamber according to claim 6 , further including an annular part interposed between the inside wall and a cylindrical segment of the outside covering around said nozzle throat.

8. The propulsion chamber according to claim 7 , further comprising a connection device for transmitting an axial force between the annular part and the outside covering without the axial force being transmitted through the inside wall.

9. The propulsion chamber according to claim 1 , further comprising a sealing barrier between the cooling circuit and the outside covering.

10. The propulsion chamber according to claim 1 , including a second axial endpiece secured to a second end of said inside wall and presenting a second radial protrusion received in a second concave recess of the inside face of the outside covering, the second concave recess being situated axially between a third belt of reinforcing fibers and a fourth belt of reinforcing fibers, the third belt of reinforcing fibers and the fourth belt of reinforcing fibers being oriented substantially circumferentially in said outside covering.

11. A fabrication method for fabricating the propulsion chamber according to claim 1 , the method comprising:
forming an inner layer of the outside covering by placing fibers around a core incorporating said first axial endpiece, the fibers fitting closely over an outline of the first radial protrusion of the first axial endpiece in order to form the first concave recess in which the first radial protrusion is received;
winding additional reinforcing fibers in a substantially circumferential direction in order to form at least said first belt of reinforcing fibers and said second belt of reinforcing fibers;
impregnating the fibers with a liquid resin; and
hardening the resin in order to form the organic matrix of the composite material of the outside covering.

12. The fabrication method according to claim 11 , wherein, after the resin has been hardened, a main body of the core is extracted from inside of the outside covering and the inside wall and the cooling circuit of the propulsion chamber are inserted inside the outside covering and fastened to the first axial endpiece.

13. The fabrication method according to claim 11 , wherein said core also incorporates at least the inside wall and the cooling circuit.

14. The fabrication method according to claim 11 , wherein the forming the inner layer of the outside covering includes placing said fibers by at least one of two- or three-dimensionally braiding around the core.

15. The fabrication method according to claim 11 , wherein the forming the inner layer of the outside covering includes placing the fibers around the core by draping, around the core, pre-impregnated sheets incorporating said fibers.

16. The fabrication method according to claim 11 , wherein said first radial protrusion is fabricated by an additive fabrication method.

Assignees

• Airbus Safran Launchers Sas
• Arianegroup Sas

Inventors

• Du Tertre Alban
• Guichard Didier
• Thomas Cedric Pierre Michel

Classifications

• B29K2307/04

  Carbon · CPC title

• F02K9/972

  Fluid cooling arrangements for nozzles (F02K9/64 takes precedence) · CPC title

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title

• B29C70/345

  using matched moulds · CPC title

• F02K9/64 Primary

  having cooling arrangements · CPC title