Design and Characteristic Calculation of Combustion Chamber of Hydrogen-Fueled Scramjet Based on “Constant Static Temperature” Heating Method

Abstract

This article takes the hydrogen-fueled scramjet as the research object, considering the mixing and combustion of the hydrogen fuel with the airflow, to propose a variable specific heat calculation method which considering the chemical equilibrium of the hydrogen-fueled combustion products. And then, propose a one-dimensional lumped parameter calculation model based on integral form for the geometry configuration design and performance simulation of hydrogen-fueled scramjet. On the basis of this calculation model, the constant static temperature heating method is used to simulate the combustion heating process of the combustion chamber, and the geometry configuration of the combustion chamber is designed. Using this profile as the final geometry configuration of the combustion chamber, conduct engine characteristics research and the results were analyzed. At the same time, the specific thrust Fs and specific impulse ISP are selected as the overall performance parameters, in the flight range of Ma7̴10, the constant static temperature design of the combustion chamber is respectively performed to obtain the engine performance parameters, and the performance comparison with the corresponding engine reference configuration is completed. The comparison results show that the constant static temperature heating method can obtain better performance, and the Fs and ISP are about 35% higher than the engine reference configuration.