초록 ▼

An apparatus and method for thermal protection is provided. A thermal protection apparatus includes a porous layer attached to an inner structural member requiring thermal protection. The porous layer serves as both a cooling air plenum and a transpiring medium. The porous layer may include a low s

An apparatus and method for thermal protection is provided. A thermal protection apparatus includes a porous layer attached to an inner structural member requiring thermal protection. The porous layer serves as both a cooling air plenum and a transpiring medium. The porous layer may include a low strength ceramic foam layer. Thermal protection may be achieved by flowing cooling air the length of the porous layer. The voids in the porous layer may be sized to less than 50 μm, producing uniquely efficient thermal protection due to micro-fluidic effects in the air flowing through the layer. A semi-permeable layer may be attached to the outer surface of the porous layer. The semi-permeable layer may prevent erosion of the porous layer and may transform the porous layer into a plenum by making the majority of the cooling air flow the length of the porous layer before exiting through small holes drilled or punched through the semi-permeable layer.

대표청구항 ▼

What is claimed is: 1. A thermal protection apparatus comprising: a porous layer, having a void size of less than about 50 microns, and having an outer surface and an inner surface, directly attached to an inner structural member requiring thermal protection at said inner surface of said porous lay

What is claimed is: 1. A thermal protection apparatus comprising: a porous layer, having a void size of less than about 50 microns, and having an outer surface and an inner surface, directly attached to an inner structural member requiring thermal protection at said inner surface of said porous layer, and having a semi-permeable layer attached to said outer surface of said porous layer, said porous layer adapted to carry a flow of cooling fluid that is actively introduced into said porous layer, said porous layer including an inlet end and an outlet end, said inlet end being adapted to receive said flow of cooling fluid into said porous layer, and said outlet end being adapted so that most of said cooling fluid exits out of said outlet end after flowing along a substantial length of said porous layer, wherein said length is substantially parallel to a bond-line between said porous layer and said inner structural member. 2. The thermal protection apparatus of claim 1, wherein said outlet end includes one or more openings in said semi-permeable layer, each of said openings being adapted to provide an exit path for most of said cooling fluid as it exits out of said outlet end after flowing along said substantial length of said porous layer. 3. The apparatus of claim 1, wherein said porous layer includes a ceramic foam layer. 4. The apparatus of claim 3, wherein said semi-permeable layer includes a hardened ceramic matrix composite. 5. An aircraft comprising: an inner structural member requiring thermal protection; and a porous layer, having a void size of less than about 50 microns, and having an outer surface and an inner surface, directly attached to said inner structural member at said inner surface of said porous layer, and having a semi-permeable layer attached to said outer surface of said porous layer, said porous layer adapted to carry a flow of cooling fluid that is actively introduced into said porous layer, said porous layer including an inlet end and an outlet end, said inlet end being adapted to receive said flow of cooling fluid into said porous layer, and said outlet end being adapted so that most of said cooling fluid exits out of said outlet end after flowing along a substantial length of said porous layer, wherein said length is substantially parallel to a bond-line between said porous layer and said inner structural member. 6. The aircraft of claim 5, wherein said outlet end includes one or more openings in said semi-permeable layer, each of said openings being adapted to provide an exit path for most of said cooling fluid as it exits out of said outlet end after flowing along said substantial length of said porous layer. 7. The aircraft of claim 5, wherein said porous layer includes a ceramic foam layer. 8. The aircraft of claim 7, wherein said semi-permeable layer includes a hardened ceramic matrix composite. 9. A space vehicle comprising: an inner structural member requiring thermal protection; and a porous layer, having a void size of less than about 50 microns, and having an outer surface and an inner surface, directly attached to said inner structural member at said inner surface of said porous layer, and having a semi-permeable layer attached to said outer surface of said porous layer, said porous layer adapted to carry a flow of cooling fluid that is actively introduced into said porous layer, said porous layer including an inlet end and an outlet end, said inlet end being adapted to receive said flow of cooling fluid into said porous layer, and said outlet end being adapted so that most of said cooling fluid exits out of said outlet end after flowing along a substantial length of said porous layer, wherein said length is substantially parallel to a bond-line between said porous layer and said inner structural member. 10. The space vehicle of claim 9, wherein said outlet end includes one or more openings in said semi-permeable layer, each of said openings being adapted to provide an exit path for most of said cooling fluid as it exits out of said outlet end after flowing along said substantial length of said porous layer. 11. The space vehicle of claim 9, wherein said porous layer includes a ceramic foam layer. 12. The space vehicle of claim 11, wherein said semi-permeable layer includes a hardened ceramic matrix composite.