초록 ▼

An apparatus and method for surface temperature control is provided. Surface temperature control is achieved by flowing coolant in and then out of a low strength porous layer attached to a structural plenum. A semi-permeable layer may be attached to the outer surface of the porous layer to prevent e

An apparatus and method for surface temperature control is provided. Surface temperature control is achieved by flowing coolant in and then out of a low strength porous layer attached to a structural plenum. A semi-permeable layer may be attached to the outer surface of the porous layer to prevent erosion of the porous layer and to facilitate surface film cooling.

대표청구항 ▼

What is claimed is: 1. An apparatus comprising: an inner structural member and an outer structural wall defining a plenum there between, said plenum adapted to contain a pressurized cooling fluid; a porous layer attached to said outer structural wall and including a ceramic foam insulation layer; a

What is claimed is: 1. An apparatus comprising: an inner structural member and an outer structural wall defining a plenum there between, said plenum adapted to contain a pressurized cooling fluid; a porous layer attached to said outer structural wall and including a ceramic foam insulation layer; and a hardened perforated layer disposed on an exterior surface of the porous layer; said outer structural wall including openings therein, said openings adapted to provide a flow of cooling fluid from said plenum to said porous layer. 2. The apparatus of claim 1 wherein said hardened perforated layer is made from a semi-permeable material. 3. The apparatus of claim 2, wherein said semi-permeable material is a hardened ceramic matrix composite. 4. The apparatus of claim 1, wherein said outer structural wall is formed from a metallic material. 5. An aircraft comprising: a structural member including an inner structural member and an outer structural wall defining a plenum there between, said plenum adapted to contain a pressurized cooling fluid; a porous layer bonded to said outer structural wall and including a ceramic foam insulation layer; and a hardened perforated layer disposed on an exterior surface of the porous layer; said outer structural wall including openings therein, said openings adapted to provide a flow of cooling fluid from said plenum to said porous layer. 6. The apparatus of claim 5, wherein said hardened perforated layer is made from a semi-permeable material. 7. The apparatus of claim 6, wherein said semi-permeable material is a hardened ceramic matrix composite. 8. The aircraft of claim 5, wherein said outer structural wall is formed from a metallic material. 9. A space vehicle comprising: a structural member including an inner structural member and an outer structural wall defining a plenum there between, said plenum adapted to contain a pressurized cooling fluid; a porous layer bonded to said outer structural wall and including a ceramic foam insulation layer; and a hardened perforated layer disposed on an exterior surface of the porous layer; said outer structural wall including openings therein, said openings adapted to provide a flow of cooling fluid from said plenum to said porous layer. 10. The space vehicle of claim 9, wherein said hardened perforated layer is made from a semi-permeable material. 11. The space vehicle of claim 10, wherein said semi-permeable material is a hardened ceramic matrix composite. 12. The space vehicle of claim 9, wherein said outer structural wall is formed from a metallic material. 13. An apparatus comprising: an inner structural member and an outer structural wall defining a plenum there between for a coolant fluid; a porous layer attached to the outer structural wall and including a ceramic foam insulation layer; the outer structural wall including openings therein; the porous layer having a number of openings, which at least partially penetrate the porous layer for providing flow of the coolant fluid; wherein the porous layer has a number of exit openings, which at least partially penetrate an exterior surface of the porous layer; and wherein the exit openings of the porous layer are laid out in staggered rows and form a uniform grid. 14. An apparatus comprising: an inner structural member and an outer structural wall defining a plenum there between for a coolant fluid; a porous layer attached to the outer structural wall and including a ceramic foam insulation layer; the outer structural wall including openings therein; the porous layer having a number of openings, which at least partially penetrate the porous layer for providing flow of the coolant fluid; wherein the porous layer has a number of entrance openings, which at least partially penetrate an interior surface of the porous layer, and a number of exit openings, which at least partially penetrate an exterior surface of the porous layer; and wherein the ratio of exit openings to entrance openings is about 10 exit openings per entrance opening. 15. An apparatus comprising: an inner structural member and an outer structural wall defining a plenum there between for a coolant fluid; a porous layer attached to the outer structural wall and including a ceramic foam insulation layer; the outer structural wall including openings therein; the porous layer having a number of openings, which at least partially penetrate the porous layer for providing flow of the coolant fluid; further including a perforated layer disposed on an exterior surface of the porous layer. 16. The apparatus of claim 15, wherein the perforated layer is made from a semi-permeable material. 17. The apparatus of claim 16, wherein the semi-permeable material is a hardened ceramic matrix composite. 18. An aircraft comprising: a structural member including an inner structural member and an outer structural wall defining a plenum there between for a coolant fluid; a porous layer bonded to the outer structural wall and including a ceramic foam insulation layer; the outer structural wall including openings therein; the porous layer having a number of openings, which at least partially penetrate the porous layer for providing flow of the coolant fluid; wherein the porous layer has a number of exit openings, which at least partially penetrate an exterior surface of the porous layer; and wherein the exit openings of the porous layer are laid out in staggered rows and form a uniform grid. 19. An aircraft comprising: a structural member including an inner structural member and an outer structural wall defining a plenum there between for a coolant fluid; a porous layer bonded to the outer structural wall and including a ceramic foam insulation layer; the outer structural wall including openings therein; the porous layer having a number of openings, which at least partially penetrate the porous layer for providing flow of the coolant fluid; wherein the porous layer has a number of entrance openings, which at least partially penetrate an interior surface of the porous layer, and a number of exit openings, which at least partially penetrate an exterior surface of the porous layer; and wherein the ratio of exit openings to entrance openings is about 10 exit openings per entrance opening. 20. An aircraft comprising: a structural member including an inner structural member and an outer structural wall defining a plenum there between for a coolant fluid; a porous layer bonded to the outer structural wall and including a ceramic foam insulation layer; the outer structural wall including openings therein; the porous layer having a number of openings, which at least partially penetrate the porous layer for providing flow of the coolant fluid; and further including a perforated layer disposed on an exterior surface of the porous layer. 21. The aircraft of claim 20, wherein the perforated layer is made from a semi-permeable material. 22. The aircraft of claim 21, wherein the semi-permeable material is a hardened ceramic matrix composite. 23. A space vehicle comprising: a structural member including an inner structural member and an outer structural wall defining a plenum there between for a coolant fluid; a porous layer bonded to the outer structural wall and including a ceramic foam insulation layer; the outer structural wall including openings therein; the porous layer having a number of openings, which at least partially penetrate the porous layer for providing flow of the coolant fluid; wherein the porous layer has a number of exit openings, which at least partially penetrate an exterior surface of the porous layer; and wherein the exit openings of the porous layer are laid out in staggered rows and form a uniform grid. 24. A space vehicle comprising: a structural member including an inner structural member and an outer structural wall defining a plenum there between for a coolant fluid; a porous layer bonded to the outer structural wall and including a ceramic foam insulation layer; the outer structural wall including openings therein; the porous layer having a number of openings, which at least partially penetrate the porous layer for providing flow of the coolant fluid; wherein the porous layer has a number of entrance openings, which at least partially penetrate an interior surface of the porous layer, and a number of exit openings, which at least partially penetrate an exterior surface of the porous layer; and wherein the ratio of exit openings to entrance openings is about 10 exit openings per entrance opening. 25. A space vehicle comprising: a structural member including an inner structural member and an outer structural wall defining a plenum there between for a coolant fluid; a porous layer bonded to the outer structural wall and including a ceramic foam insulation layer; the outer structural wall including openings therein; the porous layer having a number of openings, which at least partially penetrate the porous layer for providing flow of the coolant fluid; further including a perforated layer disposed on an exterior surface of the porous layer. 26. The space vehicle of claim 25, wherein the perforated layer is made from a semi-permeable material. 27. The space vehicle of claim 26, wherein the semi-permeable material is a hardened ceramic matrix composite.