Effects of squealer tips on blade aerodynamic performances and tip heat transfer in a gas turbine were investigated.
应用数值方法研究了燃气透平动叶顶部凹槽对动叶气动性能及叶顶传热的影响。
The calculation method for radial clearance of turbine blade tip considering the effect of temperature and rotational speed is developed in this paper.
给出了考虑温度和转速影响的涡轮叶尖径向间隙的分析计算方法。
The blade tip crack of the high pressure turbine is repaired by using the laser welding, which can reduce effectively the repair cost and increase the economic effectiveness of the engine repair.
采用激光熔焊方法，修复了高压涡轮工作叶片叶尖裂纹，有效降低了发动机修理成本，提高了发动机修理的经济效益。
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