Attitude Liquid Rocket Engine Combustor Heat Transfer Integrated Computation Method Research

In order to get the attitude liquid rocket engine wall temperature distribution more quickly and precisely, an integral counting film cooling heat transfer analysis model is presented. This model, which focuses on the engineering application, determines the different heat convection in liquid film and gas film under working condition by using stratified layers theory. It takes the stratified radiation model into account, and employs the empirical formula to analyze the heat transfer process. The gas property parameters are obtained from the minimum Gibbs free energy method, the flow parameters from one dimensional is entropic flow method, and the radiation parameters from the Leckner function. In the end, an example is given to verify the accuracy of this model and the calculated results conform with quoted experiment data. The maximum temperature of the combustor wall is near the throat, and the radiation heat transfer in the engine plays an important role of heat transfer which cannot be ignored.