Transpiration cooling applied to C/C liners of cryogenic liquid rocket engines

D. Greuel, A. Herbertz, O. J. Haidn, M. Ortelt, H. Hald

Research output: Contribution to conferencePaperpeer-review

46 Scopus citations

Abstract

The state-of-the-art of ceramic matrix composites (CMC) utilization in liquid rock£t engines is briefly reviewed. System analysis studies into the performance of transpiration cooled thrust chamber liners reveal coolant mass flow rates to be feasible only if they do not exceed 0.7% of the engine mass flow rate. Experimental studies clearly show that common models for heat transfer descriptions of blowing boundary layers are not able to predict precisely enough the cooling efficiency along a transpiration cooled liner. Instead a mixed approach, partly experimental and partly numerical, has been employed. A 2-D CFD tool based on the commercial ANSYS program has been adapted to model the compressible flow through the porous structure in order to predict the coolant mass flow distribution along a C/C liner and has been verified with experimental studies. To ensure the thermal protection of the C/C liner a minimum necessary coolant demand of around 0.45% of the total chamber mass flow rate has been calculated with TDK. A mathematical optimisation procedure is presented which should predict the necessary material properties to optimise the design of the liner's micro-structure for the specific transpiration cooling requirements.

Original languageEnglish
StatePublished - 2004
Externally publishedYes
Event40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit - Fort Lauderdale, FL, United States
Duration: 11 Jul 200414 Jul 2004

Conference

Conference40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
Country/TerritoryUnited States
CityFort Lauderdale, FL
Period11/07/0414/07/04

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