Abstract
The problem of prediction of heat flux at throat of liquid rocket engines still constitutes a challenge, because of the little experimental information. Such a problem is of obvious importance in general, and becomes even more important when considering reusable engines. Unfortunately, only few indirect experimental data are available for the validation of throat heat flux prediction. On the numerical side, a detailed solution would require a huge resolution and codes able to solve at the same time combustion, boundary layer with possible finite-rate reactions, expansion up to at least sonic speed, and in some cases radiative heat flux. Therefore, it is important to validate, with the few experimental data available in the literature, simplified CFD approaches whose aim is to predict heat flux in the nozzle in affordable times. Results obtained by different numerical models based on a RANS approach show the correctness and quality of the approximations made, indicating the main phenomena to be included in modeling for the correct prediction of throat heat flux.
Highlights
Heat flux prediction at throat of liquid rocket engines still constitutes a challenge, because of the limited experimental information
On the other hand, being capable of predicting numerically the heat flux at the throat of a rocket thrust chamber is of paramount importance
Throat region is the most critical one in terms of heat loading and requires a suitable cooling system design, which is a tradeoff between overall engine efficiency and safe structural life
Summary
Heat flux prediction at throat of liquid rocket engines still constitutes a challenge, because of the limited experimental information. Many experimental studies have been focused on the measure of wall temperature and heat flux in the combustion region, that is the thrust chamber part from the injector faceplate up to the beginning of the converging section. It is important to validate CFD solvers for the specific objective and especially to understand the uncertainties introduced by each approximation made to get reasonable predictions in affordable times In this framework, a wealth of experimental information has been recently obtained and made available to scientific community by a campaign of tests conceived and carried out at Technical University of Munich (TUM) [3,4,5,6]. The study of wall heat transfer at the throat of LRE thrust chambers is carried out including in principle both convection and thermal radiation models. Numerical Approach for the Estimation of Throat Heat Flux in Liquid Rocket Engines
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