TRANSPIRATION-COOLED SYSTEMS HAVING PERMEABLE AND NON-PERMEABLE PORTIONS

Abstract: 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.

Inventor(s): Weidong Song, Kutter Kupke, Alexander Twaites

CPC Classification: F02K9/972 (JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants , ))

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