スクラムジェットエンジンにおけるモジュール間干渉の2次元数値解析

抄録

As one of hypersonic propulsion systems, airframe-integrated scramjet engines of NASA Langley type are promising. These engines are consist of several modules, each of which composed of a compressor, a combustion chamber and a nozzle. When some disturbances occur in one module of the airframe-integrated scramjet engine, its influences are thought to propagate to other modules. In this study, it is investigated numerically how shock waves caused by thermal choke in one module propagate upstream and how they influence adjacent modules. The calculations are carried out in the two-dimensional compressible inviscid flow model using explicit symmetric TVD schemes. It is shown that shock wave generated in front of one module extends and that it blocks the flow coming into the adjacent modules quickly, which makes the modules unstarted.