摘要
The concept of using blade slotting to suppress the large boundary layer separation of high aerodynamic loading low pressure turbine profile has been developed in Part 1.Calculated results highlight the inability performance accompanied with un-proper blade slotting at high Reynolds number,blade slotting optimization seems like compulsory.Meanwhile,to further dignify the rational for use of blade slotting,slotting position and its geometry needed to be optimized.Comparison of different slotting scheme calculation results promised that blade slotting parameter like outlet angle and outlet position are the most important parameters which must be investigated to satisfy the design purpose.
基金
provided by the Supercomputing Center of Chinese Academy of Sciences and the sponsorship of National Natural Science Foundation of China
