叶顶喷气对凹槽叶尖气动性能的影响

A low⁃speed blade profile of a certain aero⁃engine high⁃pressure turbine rotor blade obtained by similarity transformation was studied,and the effect of tip injection on the aerodynamic performance of the squealer tip under the condition of relative casing motion was discussed.The results showed that tip injection had limited effect on the aerodynamic performance of the flat tip,but it could reduce the efficiency of the squealer tip.Under the same injection condition,the squealer tip can reduce the tip leakage loss by 20% compared with the flat tip.The energy dissipation of the leakage flow in the cavity mainly came from the interaction of the leakage flow with cavity vortex and scraping vortex.Under the injection condition,scraping vortex was still the dominant flow structure of the leakage flow.The injection position had a significant effect on the performance of the squealer tip; the jet holes near the suction side and leading edge were conducive to the improvement of the aerodynamic performance.Based on the above research,a leakage flow loss model for the squealer tip was established,and the error of new model was reduced by 31.6% compared with the Denton model.