IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0638559
(2003-08-12)
|
우선권정보 |
DE-0037381 (2002-08-12) |
발명자
/ 주소 |
- Beyer, Steffen
- Bichler, Peter
- Keinath, Wolfgang
- Kindermann, Roland
- Kunzmann, Dieter
|
출원인 / 주소 |
- EADS Space Transportation GmbH
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
3 |
초록
▼
A combustion chamber structure for a rocket engine or the like, has a combustion chamber liner with cooling channels and at least one manifold for feeding and removing a coolant, particularly a cryogenic fuel. The at least one manifold is brazed together with the combustion chamber liner and the are
A combustion chamber structure for a rocket engine or the like, has a combustion chamber liner with cooling channels and at least one manifold for feeding and removing a coolant, particularly a cryogenic fuel. The at least one manifold is brazed together with the combustion chamber liner and the area of the combustion chamber liner that is not covered by the at least one manifold is coated with an electroplated structural jacket. The invention also includes a method for manufacturing the combustion chamber structure.
대표청구항
▼
1. Combustion chamber structure for a rocket engine, comprising a combustion chamber liner with cooling channels and at least one manifold for feeding and removing a coolant,wherein the at least one manifold is brazed together with the combustion chamber liner, and wherein the area of the combustion
1. Combustion chamber structure for a rocket engine, comprising a combustion chamber liner with cooling channels and at least one manifold for feeding and removing a coolant,wherein the at least one manifold is brazed together with the combustion chamber liner, and wherein the area of the combustion chamber liner that is not covered by the at least one manifold is coated with an electroplated structural jacket. 2. Combustion chamber structure pursuant to claim 1, wherein the structural jacket additionally supports the at least one manifold.3. Combustion chamber structure pursuant to claim 2, wherein the structural jacket covers an area of the at least one manifold.4. Combustion chamber structure pursuant to claim 1, wherein the combustion chamber liner consists of a high-performance, good thermoconducting material, in particular copper or a copper alloy,wherein the structural jacket consists of a high-performance material, in particular nickel or a nickel alloy, and wherein the at least one manifold consists of a high-temperature material, in particular a nickel-based alloy. 5. Combustion chamber structure pursuant to claim 1, wherein said at least one manifold includes a manifold for feeding a coolant and a manifold for removing a coolant.6. Combustion chamber structure pursuant to claim 1, wherein the at least one manifold includes respective inlet and outlet manifolds for coolant in the form of cryogenic fuel for the rocket engine.7. Method for manufacturing a combustion chamber structure for a rocket engine, comprising a combustion chamber liner with cooling channels and at least one manifold for feeding and removing a coolant, particularly a cryogenic fuel, said method comprising:brazing the at least one manifold together with the combustion chamber liner, and coating an area of the combustion chamber liner that is not covered by the at least one manifold with an electroplated structural jacket. 8. Method for manufacturing a combustion chamber structure pursuant to claim 7, wherein the structural jacket is applied such that the structural jacket supports the at least one manifold.9. Method for manufacturing a combustion chamber structure pursuant to claim 7, wherein the solder is introduced between the at least one manifold and the combustion chamber liner in the form of a brazed film prior to the brazing process.10. Method for manufacturing a combustion chamber structure pursuant to claim 8, wherein the solder is introduced between the at least one manifold and the combustion chamber liner in the form of a brazed film prior to the brazing process.11. Method for manufacturing a combustion chamber structure pursuant to claim 7, wherein the at least one manifold includes respective inlet and outlet manifolds for coolant in the form of cryogenic fuel for the rocket engine.12. Method for manufacturing a combustion chamber structure pursuant to claim 7, wherein the solder is applied to the at least one manifold or the combustion chamber liner prior to the brazing process through a kinetic cold gas compacting operation or through a chemical coating operation.13. Method for manufacturing a combustion chamber structure pursuant to claim 7, wherein the structural jacket is applied at a layer thickness of 10-20 mm.14. Method for manufacturing a combustion chamber structure pursuant to claim 8, wherein the structural jacket is applied at a layer thickness of 10-20 mm.15. Method for manufacturing a combustion chamber structure pursuant to claim 9, wherein the structural jacket is applied at a layer thickness of 10-20 mm.16. Method for manufacturing a combustion chamber structure pursuant to claim 12, wherein the structural jacket is applied at a layer thickness of 10-20 mm.17. Method for manufacturing a combustion chamber structure pursuant claim 7, wherein the structural jacket is applied in several partial layers.18. Method for manufacturing a combustion chamber structure pursuant to claim 8, wherein the structural jacket is applied in several partial layers.19. Method for manufacturing a combustion chamber structure pursuant claim 9, wherein the structural jacket is applied in several partial layers.20. Method for manufacturing a combustion chamber structure pursuant claim 12, wherein the structural jacket is applied in several partial layers.21. Method for manufacturing a combustion chamber structure pursuant claim 13, wherein the structural jacket is applied in several partial layers.22. Method for manufacturing a combustion chamber structure pursuant claim 7, wherein the structural jacket is applied using a pulse-plating method.23. Method for manufacturing a combustion chamber structure pursuant claim 8, wherein the structural jacket is applied using a pulse-plating method.24. Method for manufacturing a combustion chamber structure pursuant claim 9, wherein the structural jacket is applied using a pulse-plating method.25. Method for manufacturing a combustion chamber structure pursuant claim 13, wherein the structural jacket is applied using a pulse-plating method.26. Method for manufacturing a combustion chamber structure pursuant claim 17, wherein the structural jacket is applied using a pulse-plating method.27. Method for manufacturing a combustion chamber structure pursuant claim 7, wherein said at least one manifold includes an inlet manifold and an outlet manifold.28. A combustion chamber structure comprising:a combustion chamber liner with cooling channels for a coolant, at least one manifold operable to communicate the coolant with the cooling channels, said at least one manifold being connected by brazing to a part of said combustion chamber liner, and a structural jacket electroplated on areas of the combustion chamber liner which are not covered by said brazing. 29. A combustion chamber structure according to claim 28, wherein the structural jacket additionally supports the at least one manifold.30. A combustion chamber structure according to claim 29, wherein the structural jacket covers an area of the at least one manifold.31. A combustion chamber structure according to claim 28, wherein the combustion chamber liner consists of a high-performance, good thermoconducting material, in particular copper or a copper alloy,wherein the structural jacket consists of a high-performance material, in particular nickel or a nickel alloy, and wherein the at least one manifold consists of a high-temperature material, in particular a nickel-based alloy. 32. A combustion chamber structure according to claim 28, wherein the combustion chamber structure is for a rocket engine, andwherein the at least one manifold includes respective inlet and outlet manifolds for coolant in the form of cryogenic fuel for the rocket engine. 33. A method of making a combustion chamber structure having a combustion chamber liner with cooling channels for a coolant, at least one manifold operable to communicate the coolant with the cooling channels, and a structural jacket covering portions of the liner and cooling channels, said method comprising:connecting the at least one manifold to the combustion chamber liner by brazing, and subsequently electroplating the structural jacket onto areas of the combustion chamber liner which are not covered by said brazing and at least one manifold. 34. A method according to claim 33, wherein the combustion chamber structure is for a rocket engine, andwherein the at least one manifold includes respective inlet and outlet manifolds for coolant in the form of cryogenic fuel for the rocket engine. 35. A method according to claim 33, wherein the structural jacket additionally supports the at least one manifold.36. A method according to claim 35, wherein the structural jacket covers an area of the at least one manifold.37. A method according to claim 33, wherein the combustion chamber liner consists of a high-performance, good thermoconducting material, in particular copper or a copper alloy,wherein the structural jacket consists of a high-performance material, in particular nickel or a nickel alloy, and wherein the at least one manifold consists of a high-temperature material, in particular a nickel-based alloy. 38. A method according to claim 33, wherein said structural jacket covers at least parts of the cooling channels.
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