抄録
Compressors used in aircraft gas turbines must require fewer stages than those used in industrial gas turbines while maintaining high efficiency and a wide operating range. In such a case, the compressor's diffused cascades are subject to three-dimensional separation, or corner separation, which occurs fatally at the corner between the suction surface and the endwall, resulting in compressor efficiency drop. Furthermore, when the compressor is operated at slottled condition, the incidence angle of the blade near the endwall increases, causing corner stall where flow separates from the leading edge of the blade, resulting in unstable compressor operation. In this study, a means was devised to further suppress the corner stall by utilizing an ejector effect of the slot jet flow. A detailed three-dimensional flow analysis was conducted using the Detached-eddy simulation (DES). As a result, the effectiveness of this means to suppress the corner stall was confirmed.
