Conjugate conductive, convective, and radiative heat transfer in rocket engines
- Manhattan Coll., Riverdale, NY (United States). Dept. of Mechanical Engineering
A comprehensive conductive, convective and radiative model for thermal analysis of rocket thrust chambers and nozzles is presented. In this model, the rocket thrust chamber and nozzle are subdivided into a number of stations along the longitudinal direction. At each station a finite element scheme is used to evaluate wall temperature distribution. The hot-gas-side convective heat transport is evaluated by numerically solving the compressible boundary layer equations and the radiative fluxes are evaluated by implementing an exchange factor scheme. The convective heat flux in the cooling channel is modeled based on the existing closed form correlations for rocket cooling channels. The conductive, convective and radiative processes are conjugated through an iterative procedure. The hot-gas-side heat transfer coefficients evaluated based on this model are compared to the experimental results reported in the literature. The computed convective heat transfer coefficients agree very well with experimental data for most of the engine except the throat where a discrepancy of approximately 20% exists. The model is applied to a typical regeneratively cooled rocket engine and the resulting wall temperature and heat flux distribution are presented.
- OSTI ID:
- 449509
- Report Number(s):
- CONF-950828-; ISBN 0-7918-1706-7; TRN: IM9714%%66
- Resource Relation:
- Conference: 1995 National heat transfer conference, Portland, OR (United States), 5-9 Aug 1995; Other Information: PBD: 1995; Related Information: Is Part Of 1995 national heat transfer conference: Proceedings. Volume 5: Heat transfer in aerospace devices or systems; Heat pipes and thermosyphons; Gas turbine heat transfer; HTD-Volume 307; Downing, S.; Haas, L.; Chang, W.S.; McEligot, D.M. [eds.]; PB: 152 p.
- Country of Publication:
- United States
- Language:
- English
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