突肩叶尖吸力侧开槽对叶尖间隙流动换热特性的影响

推进技术 ›› 2016, Vol. 37 ›› Issue (8): 1543-1550.

突肩叶尖吸力侧开槽对叶尖间隙流动换热特性的影响

成锋娜¹,常海萍¹,张镜洋²,田兴江¹,杜治能³

南京航空航天大学能源与动力学院，江苏南京 210016,南京航空航天大学能源与动力学院，江苏南京 210016,南京航空航天大学航天学院，江苏南京 210016,南京航空航天大学能源与动力学院，江苏南京 210016,中国航空工业集团公司沈阳发动机设计研究所，辽宁沈阳 110015

发布日期:2021-08-15
作者简介:成锋娜，女，博士生，研究领域为航空发动机高温部件冷却技术。
基金资助:
国家自然科学基金(51406085)；江苏省研究生培养创新工程(KYLX_0306)；

Effects of Squealer Tip Suction Side Cutback on Tip Leakage

College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,College of Astronautics，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China and Shenyang Aeroengine Design and Research Institute，China Aviation Industry Corporation，Shenyang 110015，China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究突肩叶尖吸力侧开槽对叶尖间隙泄漏流动换热特性的影响，采用标准k-omega两方程模型对不同突肩叶尖形式下的间隙泄漏流动进行了研究，研究的叶顶形状包括全突肩和3种部分突肩叶尖。详细分析了不同叶尖结构在3种间隙高度下的间隙泄漏流场，机匣压比，泄漏流量，总压损失和叶尖表面换热系数。结果表明:吸力侧前缘开槽可以改变前缘附近的间隙泄漏流路径，使得泄漏涡的形成位置后移，从而减小泄漏损失，但是效果微弱；吸力侧尾缘开槽可以改变开槽附近泄漏流体的流动路径，抑制其与主流的掺混，有效减小间隙泄漏损失，研究范围内最多减小8%。吸力侧前缘和尾缘开槽叶尖均会增加间隙泄漏流量，开槽长度越大泄漏流量越大，研究范围内最多增加32%。吸力侧前缘开槽会减小具有高换热系数的突肩表面积，增加凹槽表面换热系数；尾缘开槽会减小突肩表面积，增加凹槽底面的低换热系数区域的面积。

关键词: 高压涡轮；叶尖间隙高度；叶尖泄漏流量；叶尖泄漏损失；换热系数

Abstract: In order to investigate the effects of squealer tip suction side cutback on the tip leakage flow and heat transfer characteristics，the standard k-omega two equation model was used to simulate the tip leakage flow heat transfer characteristics of different squealer tips. The researching tip configurations include a full squealer tip and three partial squealer tips. The leakage flow field，casing pressure ratio distribution，leakage flow rate，total pressure loss and tip heat transfer coefficient of different squealer tips were analyzed under three clearance heights. The results show that the suction side squealer leading edge cutback can change the tip leakage flow path around the leading edge and push the beginning of the leakage vortex backward，so the leakage loss decreases slightly. The suction side squealer trailing edge cutback can change the tip leakage flow path around the trailing edge and suppress the mixing of the leakage flow and the main stream，so the leakage loss decreases effectively，and the maximum reduction is up to 8% at the research range. The suction side leading edge and trailing edge cutback both can increase leakage flow rate，and the leakage flow rate increases with the increase of the cutback length，and the maximum increase is up to 32% at the research range. The suction side squealer leading edge cutback can reduce the squealer surface area which has high heat transfer coefficient and increase the heat transfer coefficient of cavity surface，the trailing edge cutback can also reduce the squealer surface area and increase the low heat transfer coefficient area of cavity surface.

Key words: High pressure turbine；Tip clearance height；Tip leakage flow；Tip leakage loss；Heat transfer coefficient

成锋娜,常海萍,张镜洋,田兴江,杜治能. 突肩叶尖吸力侧开槽对叶尖间隙流动换热特性的影响[J]. 推进技术, 2016, 37(8): 1543-1550.

CHENG Feng-na¹,CHANG Hai-ping¹,ZHANG Jing-yang²,TIAN Xing-jiang¹,DU Zhi-neng³. Effects of Squealer Tip Suction Side Cutback on Tip Leakage[J]. Journal of Propulsion Technology, 2016, 37(8): 1543-1550.

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