Development of a Throughflow-Based Simulation Tool for Preliminary Compressor Design Considering Blade Geometry in Gas Turbine Engine

Gas turbine engines are highly intricate machines, and every component of them is closely associated with one another. In the traditional engine developing process, vast experiment tests needed. To reduce unnecessary trials, a whole gas simulation extremely For this purpose, compressor tool now developed. Considering inherent drawbacks 0D analysis 3D CFD (Computational Fluid Dynamics) calculation, 2D throughflow method an indispensable tool. Based on circumferential average (CAM), Navier–Stokes transformed into method. One phenomenon arising that lack description about motion leads to need for blade force modeling in simulation. Previous models based assumption flow passes through stream surface without entropy increasing, which not applicable CAM. An improved model proposed result from CAM NUMECA linear cascade. Whereafter, applied loaded low-speed fan, has been tested its performance characteristics. Utilizing new model, error adiabatic efficiency between decreases 4.0% 1.0% accuracy mass flow, pressure ratio remains unchanged. The time involved nearly 70 times faster than