Combined thermal protection and surface temperature control system
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B60H-001/00
F28F-007/00
출원번호
US-0182844
(2008-07-30)
등록번호
US-8191616
(2012-06-05)
발명자
/ 주소
Behrens, William W.
Tucker, Andrew R.
출원인 / 주소
The Boeing Company
인용정보
피인용 횟수 :
1인용 특허 :
4
초록▼
The invention relates to a combined thermal protection and surface temperature control apparatus. In one embodiment, a combined thermal protection and surface temperature control apparatus comprises a porous member having an entrance side, a separate exit side, and a plurality of thermally conductiv
The invention relates to a combined thermal protection and surface temperature control apparatus. In one embodiment, a combined thermal protection and surface temperature control apparatus comprises a porous member having an entrance side, a separate exit side, and a plurality of thermally conductive plugs disposed in the porous member. One or more coolant entrance channels extend through the entrance side, extend part-way through the porous member, and end within the porous member before reaching the exit side. Conversely, one or more coolant exit channels begin within the porous member, extend through a portion of the porous member, and extend through the exit side. The coolant entrance and exit channels may be parallel and may alternate. The channels may only extend across a portion of the thickness of the porous member.
대표청구항▼
1. A combined thermal protection and surface temperature control apparatus comprising: a porous member comprising an entrance side, and a separate exit side, wherein said porous member has a plurality of thermally conductive plugs disposed in said porous member;one or more coolant entrance channels
1. A combined thermal protection and surface temperature control apparatus comprising: a porous member comprising an entrance side, and a separate exit side, wherein said porous member has a plurality of thermally conductive plugs disposed in said porous member;one or more coolant entrance channels extending through said and further entrance side, extending through said porous member, towards said exit side and ending within said porous member before reaching said exit side; andone or more coolant exit channels beginning within said porous member, and extending through said porous member, towards said exit side and extending through said exit side,wherein said thermally conductive plugs extend part-way through said porous member from a top side of said porous member to a portion of a thickness of said porous member, said thermally conductive plugs having bottom surfaces ending at a depth equal to bottom ends of said coolant entrance channels and said coolant exit channels. 2. The apparatus of claim 1, wherein said porous member comprises a porous foam. 3. The apparatus of claim 2, wherein said porous foam comprises a high porosity foam with microchannel pore sizes. 4. The apparatus of claim 3, wherein said foam is a hyperporous, microchannel, alumina silica foam. 5. The apparatus of claim 1, wherein said foam is an alumina silica foam. 6. The apparatus of claim 1, wherein said conductive plugs are formed from a material selected from the group consisting of boron nitride, aluminum nitride, and alumina. 7. The apparatus of claim 1, wherein said conductive plugs have top ends that are in thermal communication with a top erosion coating. 8. The apparatus of claim 1, wherein there are a plurality of coolant entrance channels and a plurality of coolant exit channels. 9. The apparatus of claim 8, wherein said plurality of coolant entrance and exit channels are parallel and alternate. 10. The apparatus of claim 1, wherein said apparatus is adapted to be attached to a thermally protected member. 11. The apparatus of claim 10, wherein said thermally protected member comprises a portion of at least one of an engine, a vehicle, an aircraft, and a spacecraft. 12. The apparatus of claim 1, wherein the top side of said porous member is coated with an erosion coating. 13. The apparatus of claim 1, wherein a coolant flows through said coolant entrance and exit channels, said coolant comprising at least one of a gas and a fluid. 14. The apparatus of claim 1, wherein at least one of a height dimension of said entrance and exit channels, a spacing distance between said entrance and exit channels, and another spacing distance between said entrance and exit channels and a surface of said porous member, is pre-determined based on the amount of thermal protection and surface temperature control required. 15. The apparatus of claim 1, wherein a plurality of combined thermal protection and surface temperature control apparatus are attached together. 16. The apparatus of claim 15, wherein said plurality of combined thermal protection and surface temperature control apparatus are bonded together. 17. A thermally protected, controlled surface temperature apparatus comprising: a member requiring thermal protection;a porous member comprising an attachment side, a separate entrance side, and a separate exit side, wherein said attachment side of said porous member is attached to said member, and further wherein said porous member has a plurality of thermally conductive plugs disposed in said porous member;one or more coolant entrance channels extending through said entrance side, and further extending through said porous member, towards said exit side and ending within said porous member before reaching said exit side; andone or more coolant exit channels beginning within said porous member, and extending through of said porous member, towards said exit side and extending through said exit side,wherein said thermally conductive plugs extend part-way through said porous member from a top side of said porous member to a portion of a thickness of said porous member, said thermally conductive plugs having bottom ends ending at a depth equal to bottom surfaces of said coolant entrance channels and said coolant exit channels. 18. The apparatus of claim 17, wherein said conductive plugs are formed from a material selected from the group consisting of boron nitride, aluminum nitride, and alumina. 19. The apparatus of claim 17, wherein the top side of said porous member is coated with an erosion coating, and said conductive plugs have top ends that are in thermal communication with said erosion coating. 20. The apparatus of claim 17, wherein said member is a portion of at least one of an engine, a vehicle, an aircraft, and a spacecraft. 21. The apparatus of claim 17, wherein said porous member comprises a porous foam. 22. The apparatus of claim 21, wherein said foam is of high porosity with microchannel pore sizes. 23. The apparatus of claim 17, wherein said foam is an alumina silica foam. 24. The apparatus of claim 17, wherein said attachment side of said porous member is attached to said member using an adhesive. 25. The apparatus of claim 17, wherein said coolant entrance and exit channels are parallel and alternate with respect to one another. 26. The apparatus of claim 17, wherein at least one of a height dimension of said entrance and exit channels, a spacing distance between said entrance and exit channels, and another spacing distance between said entrance and exit channels and a surface of said porous member, is predetermined based on the amount of thermal protection and surface temperature control required. 27. The apparatus of claim 17, wherein a plurality of porous members are attached together. 28. The apparatus of claim 27, wherein said plurality of porous members are bonded together. 29. A method of manufacturing a thermal protection, controlled surface temperature apparatus comprising: providing a porous member wherein said porous member has a plurality of thermally conductive plugs disposed in said porous member an entrance side, and an exit side; andmanufacturing coolant entrance and exit channels within said porous member, wherein said coolant entrance channels extend through side entrance side of said porous member towards said exit side and ending within the porous member and said coolant exit channels begin within the porous member and extend through said exit side of said porous member,wherein said thermally conductive plugs extend part-way through said porous member from a top side of said porous member to a portion of a thickness of said porous member, said thermally conductive plugs having bottom ends ending at a depth equal to bottom ends of said coolant entrance channels and said coolant exit channels. 30. The method of claim 29, wherein said porous member comprises a porous foam. 31. The method of claim 30, wherein said foam is of high porosity with microchannel pore sizes. 32. The method of claim 29, wherein said foam is an alumina silica foam. 33. The method of claim 29, wherein said coolant entrance and exit channels are manufactured to be parallel and alternate with respect to one another. 34. The method of claim 29, further comprising the step of determining a member which requires thermal protection. 35. The method of claim 34, further comprising the step of determining at least one of a height dimension of said entrance and exit channels, a spacing distance between said entrance and exit channels, and another spacing distance between said entrance and exit channels and a surface of said porous member, to provide the amount of thermal protection and surface temperature control required. 36. The method of claim 34, wherein the member comprises a portion of at least one of an engine, a vehicle, an aircraft, and a spacecraft. 37. The method of claim 34, further comprising the step of attaching said porous member to said member. 38. The method of claim 29, wherein said conductive plugs are formed from a material selected from the group consisting of boron nitride, aluminum nitride, and alumina. 39. The method of claim 29, wherein the top side of said porous member is coated with an erosion coating, and said conductive plugs have top ends that are in thermal communication with said erosion coating.
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