Injector Head Transpiration Cooling Coupled with Combustion in H2/O2 Subscale Thrust Chamber
Author:
Affiliation:
1. Department of Thermal Engineering, Tsinghua University, 100084 Beijing, People’s Republic of China
2. Beijing Aerospace Propulsion Institute, Beijing Aerospace Propulsion Institute, 10006 Beijing, People’s Republic of China
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Condensed Matter Physics,Aerospace Engineering,Space and Planetary Science,Fluid Flow and Transfer Processes,Mechanical Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.T3872
Reference31 articles.
1. Experimental investigation of transpiration cooled hydrogen-oxygen subscale chambers
2. MueggenburgH. H.HidahlJ. W.KesslerE. L.RousarD. C. “Plate Actively Cooled Thermal Management Devices,” AIAA Paper 1992-3127, 1992.
3. Design and fabrication of a hydrogen/oxygen thrust chamber assembly
4. The prediction of nozzle performance and heat transfer in hydrogen/oxygen rocket engines with transpiration cooling, film cooling, and high area ratios
5. Development of advanced technologies for future cryogenic thrust chamber applications
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