Empirical Verification of Effusion Cooled CMC Rocket Thrust Chambers

Thrust chambers are one of the most sensitive components in rocket propulsion systems due to safety and efficiency related to reasonable costs. Competitive space transportation systems ask for such low cost and high sophisticated solutions. A very promising approach in this field is the development of an effusion cooled CMC combustion chamber design, which offers a new perspective on the way to reliable future cryogenic rocket engines. The undoubted advantages of transpiration cooling under the critical view of efficiency, damage tolerance and low cost aspects can be accomplished with a relatively simple and low weight concept using carbon fiber composite materials. In the recent years DLR works on the application of effusion technology. The paper illustrates the empirical development steps accompanied by numerical simulations until a break through in form of the latest high performance tests early in 2005.

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