The Counter Rotationg Axial Fan Turbojet Engine is considered as the propulsion engine for the subscale supersonic unmanned plane, because of its aerodynamic and structural advantages. In the present study, the numerical design and analysis of counter rotating fan are conducted by Streamline Curvature Method (SCM). At same time, the two staged counter rotating turbine is also numerically designed and its aerodynamic performances are evaluated by CFD. We discussed the system integration of this type of engine based on the results of the analyses of the engine elements.
反転ファンターボジェットエンジンの研究
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