Effusion Cooled Rocket Combustion Chamber

Abstract

A new approach followed by DLR since some years is the realization of a revolutionary combustion chamber concept based on effusion cooling and use of high performance composites and porous ceramic matrix composites (CMC). Beside basic principle illustration this paper explains characteristically issues and potential improvements introduced by this new technology, e.g. lower weight, lower costs, increased reliability, higher lifetime by no longer existing thermal cycling sensitivity. DLR’s development road map is sketched and the technology readiness level achieved so far is described. The current phase of technology development is characterized by designing, manufacturing and testing of various functional demonstrators named V01-V03. Tests were carried out at the M3 test facility of DLR Lampoldshausen at typical combustion pressure levels of approximately 1MPa. Tests and measurements include pre-determination of cold flow characteristics of the porous liner material, hot firing experience and data including optical temperature measurements and the demonstration of manufacturing techniques for an entire non-metallic combustion chamber with integrated cooling system. The paper reports on major results and achievements from these various test campaigns. Now, the functional demonstrator V04 for an extended test campaign is under construction while subsuming previous experiences. So, upcoming test campaigns in the near future are likely to prove breakthrough of this new technology approach and an outlook to forthcoming activities is given.