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Aerothermal environment induced by mismatch at the SSME main combustion chamber-nozzle jointThe computational study reported here is motivated by a Space Shuttle main engine hardware problem detected in post-flight and post-test inspections. Of interest are the potential for hot gas ingestion into the joint (G15) at the main combustion chamber-to-nozzle interface and the effect of particular goemetric nonuniformities on that gas ingestion. The flowfield in the G15 region involves supersonic flow past a rounded forward facing step preceded by a deep narrow cavity. This paper describes the physical problem associated with joint G15 and computational investigations of the G15 aerothermal environment. The associated flowfield was simulated in two and three space dimensions using the United Solutions Algorithm (USA) computational fluid dynamics code series. A benchmark calculation of experimentally measured supersonic flow over of a square cavity was performed to demonstrate the accuracy of the USA code in analyzing flows similar to the G15 computational flowfield. The G15 results demonstrate the mechanism for hot gas ingestion into the joint and reveal the sensitivity to salient geometric nonuniformities.
Document ID
19900055084
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mcconnaughey, H. V.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
O'Farrell, J. M.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Olive, T. A.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Brown, G. B.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Holt, J. B.
(Rockwell International Corp. Space Transportation Systems Div., Huntsville, AL, United States)
Date Acquired
August 14, 2013
Publication Date
July 1, 1990
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 90-2359
Accession Number
90A42139
Distribution Limits
Public
Copyright
Other

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