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Experimental evaluation of an advanced Space Shuttle main engine hot-gas manifold design conceptThis study, using an extensively modified, full-scale space shuttle main engine (SSME) hot-gas manifold (HGM), established a detailed aerodynamic data base to support development of an advanced, three-dimensional, fluid-dynamic analysis computer model. In addition, the advanced SSME hot-gas manifold design used in this study demonstrated improved flow environment (uniformity) in the fuel side turbine exit and transfer duct exit regions. Major modifications were incorporated in the full-scale HGM flow test article model using two large transfer ducts on the fuel turbine side of the HGM in place of the three small transfer ducts in the present design. Other model features included an increases in the flow areas downstream of the 180-degree turn and in the fishbowl regions.
Document ID
19850018587
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Pelaccio, D. G. (Rockwell International Corp. Canoga Park, CA, United States)
Lepore, F. F. (Rockwell International Corp. Canoga Park, CA, United States)
Oconnor, G. M. (Rockwell International Corp. Canoga Park, CA, United States)
Rao, G. V. R. (Rockwell International Corp. Canoga Park, CA, United States)
Ratekin, G. H. (Rockwell International Corp. Canoga Park, CA, United States)
Vogt, S. T. (Rockwell International Corp. Canoga Park, CA, United States)
Date Acquired
August 12, 2013
Publication Date
April 1, 1985
Publication Information
Publication: NASA. Marshall Space Flight Center Advan. High Pressure O2(H2 Technol.
Subject Category
Spacecraft Propulsion And Power
Accession Number
85N26898
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19850018551Collected WorksAdvanced High Pressure O2/H2 Technology
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