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EFFECTS OF GROOVE STRUCTURE ON AERODYNAMIC PERFORMANCE OF A TURBINE BLADE

In the tip gap between a blade and the casing, there are many highly three-dimensional and complex flow structures, which leads to significantly reduce the aerodynamic performance of a turbine. And the interaction between the tip leakage flow and the main passage flow is a substantial source of aerodynamic loss. In order to minimize the flow loss caused by the tip clearance leakage flow to the high-pressure turbine blades, the first-stage rotor of the GE-E3 high-pressure turbine introduced a groove structure and optimized the design parameters. Firstly, the control effect of the groove structure is proved.Then the influence of the design parameter of groove depth on the control effect is studied. Finally, based on the uniform design method, the flow control effect of the groove structure with different design parameter combinations is numerically simulated to obtain the optimal design plan for controlling the tip clearance leakage flow. The results show that there is an optimal groove depth value; the total pressure loss coefficient at the 110% axial chord length is reduced by 9.84%, and the rotor blade efficiency is increased by 0.323%. The obstructive effect of the groove structure causes the airflow to separate after passing through the pressure surface to form a return zone, which hinders the leakage flow and reduces the leakage loss.