Experimental and Numerical Study on Flow Resistance of Turbine Blade Tilted Trailing Edge Slots

Reducing the internal flow resistance of turbine blades can improve the overall efficiency of aero engines. To address the issue of the large internal flow losses in traditional horizontal exhaust slots for trailing edge cooling, structure of radially tilted trailing edge slots was proposed in previous work, and the flow resistance reduction ability of the novel scheme was investigated through numerical simulations under typical engine working conditions. Building on this, this research aimed to investigate the flow resistance of both novel and traditional schemes under ordinary pressure conditions through a combination of experimental and numerical methods. The results indicated that the tilted scheme exhibited a reduction in total pressure loss of approximately 5.7–9.1% compared to the horizontal one at the same Reynolds number. The analysis and comparison of the internal flow field details of the two schemes was conducted, which indicated that the tilted slots effectively suppressed vortex generation by reducing the coolant turning angle, resulting in lower flow losses. These research works have demonstrated the clear advantages of utilizing tilted trailing edge slots in reducing internal flow resistance, which would provide a reference for the high-performance aero engines in the future.