Transpiration-cooled systems having permeable and non-permeable portions
Transpiration-cooled systems having permeable and non-permeable portions are provided. In one aspect, a nozzle for a rocket engine includes a non-permeable outer layer, a plurality of walls, a permeable layer, and a plurality of cooling channels. The non-permeable outer layer forms a predetermined shape of the nozzle and defines an interior space. The plurality of walls extend generally orthogonal to the non-permeable outer layer and into the interior space. The permeable layer is disposed between each set of adjacent walls of the plurality of walls. The permeable layer is spaced a distance from the non-permeable outer layer. The plurality of cooling channels are formed between the permeable layer, the non-permeable outer layer, and a set of adjacent walls of the plurality of walls. The plurality of cooling channels are configured to transport a fluid.
1. A nozzle for a rocket engine comprising:
a non-permeable outer layer forming a predetermined shape of the nozzle, the non-permeable outer layer defining an interior space;
a plurality of walls, each wall comprising a first side and a second side extending generally orthogonal to the non-permeable outer layer and into the interior space;
a plurality of permeable layers, a permeable layer of the plurality of permeable layers disposed between the first side of a first wall of the plurality of walls and the second side of a second, adjacent wall of the plurality of walls, the permeable layer comprising an outermost surface spaced a distance from the non-permeable outer layer and an innermost surface opposite the outermost surface, wherein the first side and the second side of each of the plurality of walls terminate at an innermost surface, and wherein the innermost surface of the first wall, the innermost surface of the permeable layer, and the innermost surface of the second wall define a continuous portion of an inner circumference of the nozzle; and
a plurality of cooling channels extending between an intake end and an exhaust end of the nozzle, a cooling channel of the plurality of cooling channels defined by the outermost surface of the permeable layer, the non-permeable outer layer, the first side of the first wall, and the second side of the second, adjacent wall, the cooling channel configured to transport a fluid.
2. The nozzle of claim 1 , wherein the non-permeable outer layer, the plurality of walls, and the plurality of permeable layers comprise the same material.
3. The nozzle of claim 1 , wherein the outermost surface and the innermost surface of the permeable layer are configured to be permeated by at least a portion of the fluid, and wherein the first side of the first wall and the second side of the second, adjacent wall are configured to contact the at least a portion of the fluid that permeates the outermost surface and the innermost surface of the permeable layer.
4. The nozzle of claim 1 , wherein a density of the permeable layer increases from the outermost surface of the permeable layer to the innermost surface of the permeable layer.
5. The nozzle of claim 4 , wherein a first portion of each permeable layer is permeable to the fluid at a first rate and a second portion of each permeable layer is permeable to the fluid at a second rate.
6. The nozzle of claim 1 , wherein the non-permeable outer layer, the plurality of walls, and the plurality of permeable layers are formed using a single material.
7. The nozzle of claim 1 , wherein the non-permeable outer layer and the plurality of walls are integral.
8. The nozzle of claim 1 , wherein an innermost surface of each of the plurality of permeable layers and the innermost surface of each of the plurality of walls define a circumference of an interior surface of the nozzle.
9. The nozzle of claim 1 , wherein the plurality of permeable layers extend between the intake end and the exhaust end of the nozzle.
10. The nozzle of claim 9 , wherein, when the fluid is transported in the cooling channel, the fluid is in contact with the outermost surface of the permeable layer between the intake end and the exhaust end of the nozzle.
11. The nozzle of claim 1 , wherein the permeable layer is in contact with the first side of the first wall of the plurality of walls and the second side of the second, adjacent wall of the plurality of walls.
12. A rocket engine comprising:
a non-permeable layer defining an interior space;
a plurality of walls, each wall comprising a first side and a second side extending from the non-permeable layer and into the interior space;
a plurality of permeable layers, a permeable layer of the plurality of permeable layers disposed between the first side of a first wall of the plurality of walls and the second side of a second, adjacent wall of the plurality of walls, the first side and the second side of each of the plurality of walls terminating at an innermost surface, an innermost surface of each of the plurality of permeable layers and the innermost surface of each of the plurality of walls defining a circumference of an interior surface of the rocket engine; and
a plurality of cooling channels extending between an intake end and an exhaust end of a nozzle of the rocket engine, a cooling channel of the plurality of cooling channels defined by an outermost surface of the permeable layer, the non-permeable layer, the first side of the first wall, and the second side of the second, adjacent wall, the cooling channel configured to transport a fluid.
13. The rocket engine of claim 12 , wherein the non-permeable layer, the plurality of walls, and the plurality of permeable layers comprise the same material.
14. The rocket engine of claim 12 , wherein the outermost surface and an innermost surface of the permeable layer are configured to be permeated by at least a portion of the fluid, and wherein the first side of the first wall and the second side of the second, adjacent wall are configured to contact the at least a portion of the fluid that permeates the outermost surface and the innermost surface of the permeable layer.
15. The rocket engine of claim 12 , wherein a density of the permeable layer increases from the outermost surface of the permeable layer to the innermost surface of the permeable layer.
16. The rocket engine of claim 12 , wherein a first portion of the permeable layer is permeable to the fluid at a first rate and a second portion of the permeable layer is permeable to the fluid at a second rate.
17. The rocket engine of claim 12 , wherein the non-permeable layer, the plurality of walls, and the plurality of permeable layers are formed using a single material.
18. The rocket engine of claim 12 , wherein the non-permeable layer and the plurality of walls are integral.
19. The rocket engine of claim 12 , wherein the plurality of permeable layers extend between the intake end and the exhaust end of the nozzle of the rocket engine, and wherein, when the fluid is transported in the cooling channel, the fluid is in contact with the outermost surface of the permeable layer between the intake end and the exhaust end of the nozzle.
20. The rocket engine of claim 12 , wherein the permeable layer is in contact with the first side of the first wall of the plurality of walls and the second side of the second, adjacent wall of the plurality of walls.