Study on the Influence of Geometry Configuration of Combustion Chamber on the Performance of Hydrogen-Fueled Scramjet Engine

This paper takes the hydrogen-fueled scramjet as the research object, fully considering the mixing degree and combustion efficiency of the hydrogen fuel and airflow and other issues, a one-dimensional lumped parameter calculation model based on integral form is established. On the basis of this calculation model, in the flight range of Ma5-10, the two-stage, three-stage and four-stage geometry configuration of the combustion chamber are respectively calculated, the influence of the geometry configuration of the combustion chamber on the performance of the hydrogen-fueled scramjet engine is studied, and the calculation results are analyzed and summarized. The final calculation results show that the calculation model based on integral form established in this paper can complete the performance simulation and calculation of hydrogen-fueled scramjet engine, which can effectively compensate the deficiency of the differential form calculation model and improve the calculation accuracy. At the same time, the change of the two-stage, three-stage and four-stage geometry configuration of the combustion chamber does have a certain impact on the performance of the maximum fuel supply state of the hydrogen-fueled scramjet.