Aerodynamic performance test results of single stage oxidizer turbine with volute manifolds
Author:
Affiliation:
1. NASA, Marshall Space Flight Center, Huntsville, AL
2. Pratt & Whitney, West Palm Beach, FL
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1997-3099
Reference19 articles.
1. 'Griffin, L.W. and Huber, F.W. "Turbine Technology Team: An Overview of Current and Planned Activities relevant to the National Launch System,"AIAA92-3220,1992.
2. 2Huber, F.W.,Johnson, P.D., Montesdeoca, X.A., Rowey, R.J., and Griffin, L.W. "Design of Advanced Turbopump Drive Turbines for National LaunchSystemsApplication,"AIAA92-3221, 1992.
3. 4Hudson, S.T., Johnson, P.O., and Branick, R.E. "Performance Testingof aHighly Loaded Single Stage Oxidizer Turbine with Inlet and Exit Volute Manifolds,"AIAA95-2405, 1995.
4. 5Smith, A.W.and Ramachandran, N. 'Two-Dimensional LDV Measurements in the Inlet and Exit Manifolds of a Single Stage Oxidizer Turbine," AIAA 97-0883,1997.
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