Numerical Investigation on Influence on the Regression Rate of the Inlet Parameters in Solid Fuel Scramjet Combustor

Abstract

The influence on the regression rate of the inlet parameters of a solid fuel (PMMA) under supersonic cross flow has been investigated theoretically and numerically. Based on two-dimensional compressible N-S equations and species transport equations, the regression rate values were obtained by adding to the source term in the quality、 momentum and energy of the fuel. With different inlet parameters , i.e., stagnation temperature and pressure , the combustion conditions were analyzed at the flame-holding zone and the constant diameter cylindrical section. Comparison between numerical results with test data showed fair agreement, indicating the correctness of the calculation model. The results show that increasing the amount of oxygen or the mixture of the fuel and oxidant can improve the combustion efficiency; the inlet mass flow of air、stagnation temperature and depth of cavity has a great impact on the regression rate, then the impact of the length of cavity was slightly smaller, the impact of the stagnation pressure was minimum. NomenclatureP =pressure T =temperature u, v =axial, radial velocity h =enthalpy value  =density M =Mach number r  =regression rate D =diameter L =length w q  =heat flux subscripts fh =flameholding zone cyl =cylindrical section