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Numerical analysis of the hot-gas-side and coolant-side heat transfer in liquid rocket engine combustorsThe objective of this paper are to develop a multidisciplinary computational methodology to predict the hot-gas-side and coolant-side heat transfer and to use it in parametric studies to recommend optimized design of the coolant channels for a regeneratively cooled liquid rocket engine combustor. An integrated numerical model which incorporates CFD for the hot-gas thermal environment, and thermal analysis for the liner and coolant channels, was developed. This integrated CFD/thermal model was validated by comparing predicted heat fluxes with those of hot-firing test and industrial design methods for a 40 k calorimeter thrust chamber and the Space Shuttle Main Engine Main Combustion Chamber. Parametric studies were performed for the Advanced Main Combustion Chamber to find a strategy for a proposed combustion chamber coolant channel design.
Document ID
19920066154
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wang, Ten-See
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Van, Luong
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1992
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 92-3151
Accession Number
92A48778
Distribution Limits
Public
Copyright
Other

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