Combustion chamber comprising a condensation-proof barrier on a regenerative circuit

Patent metadata

Field	Value
Publication number	US-9429106-B2
Application number	US-201013381431-A
Country	US
Kind code	B2
Filing date	Jul 8, 2010
Priority date	Jul 9, 2009
Publication date	Aug 30, 2016
Grant date	Aug 30, 2016

Abstract

The invention concerns a combustion chamber ( 10 ) comprising a neck ( 15 ) downstream of the injection ( 11 ) of gases, and downstream of this neck a divergent section ( 20 ) whereof the outer face of the wall ( 30 ), when in operation, is cooled by a cooling system using a cryogenic product and surrounding this outer face. This divergent section ( 20 ), on the inner face ( 32 ) of its wall ( 30 ), comprises a coating ( 40 ) acting as temperature compensator so that the temperature of the inner face ( 42 ) of the coating ( 40 ) is higher than the condensation temperature of the combustion gases on this inner face ( 42 ) under operating conditions, such that no condensation is formed on this inner face ( 42 ).

First claim

What is claimed is:

1. A combustion chamber comprising a neck downstream of the injection of gases, and downstream of the neck a divergent section whereof a radially outer face of an outer wall of the divergent section, when in operation, is cooled by a cooling system using a cryogenic product and surrounding the outer face,
wherein the divergent section being such that on an inner face of the outer wall comprises a coating acting as a temperature compensator so that the temperature of the inner face of said coating is higher than the condensation temperature of the combustion gases on the inner face under operating conditions, such that no condensation is formed on the inner face,
wherein the coating is located entirely downstream of the neck, and wherein the thickness of said coating increases gradually over a first, upstream portion of the divergent section and then decreases over a second, downstream pardon of the divergent section.

2. The combustion chamber according to claim 1 , wherein said coating comprises a ceramic.

3. The combustion chamber according to claim 2 , wherein said ceramic is yttria-stabilized zirconia.

4. The combustion chamber according to claim 2 wherein said coating further comprises a sub-layer deposited directly on the said inner face of said wall of the divergent section, and said ceramic being deposited on this sub-layer.

5. The combustion chamber according to claim 4 , wherein said sub-layer is of MCrAlY type, where M is a metal.

6. The combustion chamber according to claim 5 , wherein the metal comprises at least one of: nickel, iron and cobalt.

7. The combustion chamber according to claim 1 , wherein the thickness of said coating is of the order of 150 microns.

8. The combustion chamber according to claim 1 , wherein said coating covers the entire said inner face of said wall of the divergent section.

9. The combustion chamber according to claim 1 , wherein said cooling system is a regenerative circuit in which a cryogenic liquid circulates.

10. The combustion chamber according to claim 1 , wherein the coating has a thickness between 50 μm and 100 μm.

11. The combustion chamber according to claim 1 , wherein the coating has a thermal conductivity between 1 W/m·K and 2 W/m·K.

12. The combustion chamber according to claim 1 , wherein the combustion chamber is embodied in a rocket engine.

13. The combustion chamber according to claim 1 , wherein the combustion chamber is rotationally symmetrical.

Assignees

• Cornu Daniel
• Snecma

Inventors

• Cornu Daniel

Classifications

• F02K9/974

  Nozzle- linings; Ablative coatings · CPC title

• F02K9/97 Primary

  Rocket nozzles (thrust or thrust vector control F02K9/80) · CPC title

• F02K9/64

  having cooling arrangements · CPC title

• F05D2260/231

  Preventing heat transfer · CPC title

• F05D2300/2118

  Zirconium oxides · CPC title