Volume 4, 2013Progress in Propulsion Physics
|Page(s)||167 - 184|
|Section||Chapter Two. Liquid and gelled propulsion|
|Published online||05 March 2013|
Determination of thermal load in film cooled bipropellant thrust chambers by an inverse method
INPE Sao José ‚ dos Campos, SP, Brasil
A method to obtain the heat load on the internal wall of a rocket thrust chamber using an inverse problem approach is described. According to the “classical” approach, the heat load on the internal wall of the chamber is assumed as the product of a heat transfer coefficient and the temperature difference of adiabatic wall temperature and local wall surface temperature. The time-dependent temperature distribution of the external wall of the thruster chamber is used to obtain empirical curve fittings to the temperature profile of the near wall flow field (adiabatic wall temperature) and the heat transfer coefficient profile. The applicability of the method is verified by applying it to three different problems; a model problem, an analytical solution, and a set of experimental data.
© Owned by the authors, published by EDP Sciences, 2013