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开展了叶顶结构及间隙变化对高压涡轮冷却叶片气动与传热性能影响的研究,建立了四种不同叶顶结构的涡轮冷却叶片几何与数值分析模型,进行了高精度流热固耦合分析,得到了不同叶顶结构及间隙对涡轮冷却叶片气动与传热性能影响的数值分析结果。结果表明:不带射流孔叶片随着叶顶间隙的增大,总压损失增加;由于近壁面处存在的涡流,凹槽叶顶结构能够减少叶顶燃气泄漏,阻碍叶顶平面高温燃气的流动与热交换;叶顶射流孔冷却效果明显,能够大幅度降低叶顶平面温度。在相同叶顶间隙下,凹槽射流叶片具有最高的气动性能。
The influence of blade tip structure and gap on the aerodynamic and heat transfer performance of high pressure turbine cooling blades was studied. The geometric and numerical analysis models of four different blade tip turbine cooling vanes were established. High precision fluid thermomechanical coupling analysis was carried out. The numerical analysis results of the influence of different tip structures and gaps on the aerodynamic and heat transfer performance of turbine cooling blades were obtained. The results show that with the increase of the tip clearance, the total pressure loss increases. Due to the eddy current near the wall, the grooved roof structure can reduce the leakage of the top gas and hinder the flow of hot gas at the tip plane And heat exchange; the effect of cooling the tip jet hole is obvious, which can greatly reduce the blade top plane temperature. Grooved jet blades have the highest aerodynamic performance at the same tip clearance.