CFD 기법에 의해 예측된 흡입구 및 배기구 손실을 고려한 터보 축 엔진의 장착성능에 관한 연구

Abstract

This paper describes an advanced simulation strategy in which a couple of steady state high-fidelity three dimension analysis of an engine component, the inlet and exhaust duct aimed at developing a reliable smart UAV capable of high speed cruise, takeoff , and all flight modes that applies to a UAV. Since the object of study involves advance flight dynamics it is essential that the intake and exhaust system including the plenum chamber be designed with maximum accuracy that facilitate good performance characteristics. hence the purpose of this study being the analysis of inlet and exhaust duct losses experienced in the ducts in question. The losses is then used to analyze installed engine loss. 3-D CFD analysis is employed to calculate the pressure loss and show the flow characteristics through the inlet and exhaust system at different flight attitudes. inlet and exhaust boundary conditions used are the same as those used in the design point performance analysis done at sea level static condition and at cruise altitude of 10000ft. Design point simulation was performed by a commercial program (GasTurb 9) to calculate design and off design performance of the candidate gas turbine engine. Simulation methods are not only costly but also time consuming. Superior simulation and analysis method is hence vital and as shown in this research that alternative method can be used to describe the engine performance with specific detail on the performance of the intake and exhaust so that cost-effective and time management simulation is present for future designs.