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Nonadiabatic Flamelet Formulation for Predicting Wall Heat Transfer in Rocket Engines

Journal Article · · AIAA Journal
DOI:https://doi.org/10.2514/1.J056539· OSTI ID:1544273
 [1];  [1];  [1];  [2]
  1. Stanford Univ., CA (United States)
  2. Univ. of Waterloo, ON (Canada)
+ Show Author Affiliations
A flamelet-based combustion model is introduced for the prediction of wall heat transfer in rocket engines and confined combustion systems. To account for convective heat loss due to the interaction of the flame with the wall, a permeable thermal boundary condition is introduced in the counterflow diffusion flame configuration. The solution of the resulting nonadiabatic flame structure forms a three-dimensional manifold, which is parameterized in terms of mixture fraction, progress variable, and temperature. The performance of the model is first assessed through a direct numerical simulation analysis of an H2/O2 diffusion flame that is stabilized at an inert isothermal wall. The developed nonadiabatic flamelet model is shown to accurately predict the temperature, chemical composition, and wall heat transfer. Combined with a presumed probability density function closure, the model is then applied to large-eddy simulation of a single-injector rocket combustor to examine effects of heat transfer on the turbulent flame structure in rocket engines.
Research Organization:
Lawrence Berkeley National Laboratory (LBNL), Berkeley, CA (United States). National Energy Research Scientific Computing Center (NERSC)
Sponsoring Organization:
NASA; USDOE Office of Science (SC)
Grant/Contract Number:
AC02-05CH11231
OSTI ID:
1544273
Journal Information:
AIAA Journal, Journal Name: AIAA Journal Journal Issue: 6 Vol. 56; ISSN 0001-1452
Publisher:
AIAACopyright Statement
Country of Publication:
United States
Language:
English

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Cited By (1)

Analysis of Wall–flame Interaction in Laminar Non-premixed Combustion journal October 2019

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