航空機エンジン用低圧タービン翼のベース領域に関する研究

抄録

In this research, a low pressure turbine blade (LPT) of high bypass ratio turbofan engine is studied. Since the LPT drives the fan, the improvement in LPT aerodynamic performance contributes surely to the fuel burn reduction of the engine. A focus is on the effects of the freestream turbulence intensities (FSTI), the Reynolds numbers and the Strouhal numbers on the base pressure in a LPT blade, which is because few studies have been made on base pressure despite the fact that it has some impact on the efficiency of the blade. Base pressure and PIV measurements around the base region were performed in the LPT linear cascade at six conditions covering Low FSTI and High FSTI, St =0.00 and 1.25 with Re = 130,000 and 170,000. In order to investigate the relationship between base pressure and flow field, PIV measurement was conducted. At low FSTI and St =0.00, the flow of suction side turn to the center of the trailing edge, so the separation point is moved. The phenomenon seems to affect base pressure.