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The Prediction of Nozzle Performance and Heat Transfer in Hydrogen/Oxygen Rocket Engines with Transpiration Cooling, Film Cooling, and High Area RatiosAn advanced engineering computational model has been developed to aid in the analysis of chemical rocket engines. The complete multispecies, chemically reacting and diffusing Navier-Stokes equations are modelled, including the Soret thermal diffusion and Dufour energy transfer terms. Demonstration cases are presented for a 1030:1 area ratio nozzle, a 25 lbf film-cooled nozzle, and a transpiration-cooled plug-and-spool rocket engine. The results indicate that the thrust coefficient predictions of the 1030:1 nozzle and the film-cooled nozzle are within 0.2 to 0.5 percent, respectively, of experimental measurements. Further, the model's predictions agree very well with the heat transfer measurements made in all of the nozzle test cases. It is demonstrated that thermal diffusion has a significant effect on the predicted mass fraction of hydrogen along the wall of the nozzle and was shown to represent a significant fraction of the diffusion fluxes occurring in the transpiration-cooled rocket engine.
Document ID
19940030418
Acquisition Source
Headquarters
Document Type
Conference Paper
Authors
Kacynski, Kenneth J. (NASA Lewis Research Center Cleveland, OH, United States)
Hoffman, Joe D. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
May 1, 1994
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NAS 1.15:106617
E-8902
AIAA PAPER 94-2757
NASA-TM-106617
Meeting Information
Meeting: Joint Propulsion Conference
Location: Indianapolis, IN
Country: United States
Start Date: June 27, 1994
End Date: June 29, 1994
Sponsors: AIAA, ASME, SAE, and ASEE
Accession Number
94N34924
Funding Number(s)
PROJECT: RTOP 232-01-0A
Distribution Limits
Public
Copyright
Public Use Permitted.

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