The proposed regeneratively cooled ceramic matrix composite combustion chamber and nozzle technology would be immediately applicable to upper-stage rocket engines and small in-space and powered descent engines. With additional development, the same technology could be applied to large nozzles, which would yield an even greater system benefit than small nozzles due to their greater fraction of the total system mass for a large rocket.
Cooled ceramic matrix composites are applicable to combustors and hot structure for flight vehicles. For hypersonic airplanes, the technology is applicable to leading edges, combustor liners, and jet impingement surfaces. It can be used with fuel as coolant as in the rocket engine case, or with separate cooling loops including cryogenic, phase-change, or refrigerated. The temperature capabilities of existing CMC parts can be increased, or lower-cost CMCs could be substituted, enabled by cooling.
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