Marxman モデルに基づくハイブリッドロケット燃焼器内流れ場の準一次元非定常数値解析

摘要

The purpose of this paper is to investigate the acoustic combustion instability of a hybrid rocket motor.Firstly, the quasi-one-dimensional Euler equations for steady flows inside a combustion chamber arenumerically solved with Marxman’s model for the fuel regression due to boundary layer combustion. Inorder to obtain the pressure response of the flowfield, then, not only Euler equations but also a thermalconduction equation inside the solid fuel is solved with a proposed thermal feedback law obtained froma quasi-steady flame model near the burning surface. The present model is applicable for the case thatquick diffusion condition is satisfied in the boundary layer. The regression rate is assumed to follow theArrhenius-type function of the surface temperature with the steady value evaluated by the Marxman’smodel.