Theoretical Analysis and Numerical Simulation of Tip Clearance of 12-Stage High-pressure Compressor Rotor
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摘要: 以某型发动机轴流高压压气机为对象,研究该压气机第12级转子与机匣在运行过程中受温度、气动和离心载荷综合作用下的径向变形。先通过改进预测涡轮叶尖间隙的理论简化模型,来预测该压气机在各工况下叶尖间隙变化规律;再通过三维建模,运用有限元软件ANSYS对压气机各工况进行流-固-热耦合瞬态分析模拟,得到叶尖间隙变化规律,提取间隙变化最大时的各部件径向变形并沿轴向展开。结果表明:两种方法获取的间隙变化规律趋于一致,但理论分析能较快获取规律,而数值模拟结果更加精确,并可以确定叶片顶端最易刮伤的结构位置。研究结果对快速预测叶尖间隙,确定装配间隙和机匣涂层的分布有着重要的参考价值。Abstract: To study the changes in the tip clearance of a 12-stage high-pressure compressor rotor in different engine operation conditions, with its thermal, mechanical and aerodynamic loads considered, a modified and reduced theoretical model was set up. With the model, the changes in different engine operation conditions were studied. Then the 3D model of the compressor rotor was built and more changes in the tip clearance were studied through computer simulation, which turned out to coincide with the changes in different engine operation conditions. The great changes in the moment of the tip clearance were simulated with the finite element analysis software ANSYS. The fluid-solid-thermal coupling method was adopted; the precise radial displacement of the compressor rotor and the compressor case along the axial direction was obtained, and the changes in the maximum tip clearance were calculated. In the maximum tip clearance, the compressor blade may probably scratch the compressor case. The study has a reference value for determining the tip clearance in compressor installation and the distribution of coating.
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Key words:
- compressors /
- rotors /
- tip clearance /
- computer simulation /
- mathematical model /
- fluid-solid-thermal coupling
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表 1 材料性能参数
部件材料 热膨胀系数α/(℃-1) 热传导系数k/(W·(m·℃)-1) 杨氏模量E/GPa 泊松比ν 比热容c/(J·(kg·℃) -1) 机匣(S/SJ2) 1.13×10-5 23.93 195.47 0.3 502.3 叶片(S/SAV) 1.17×10-5 25.8 176.71 0.32 490 轮盘(N901) 1.50×10-5 16.7 171.68 0.35 460 -
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