论文部分内容阅读
针对航空发动机高压压气机,综合考虑气动载荷、离心力载荷、温度载荷耦合作用,建立了压气机径向间隙分析模型,获得了3个典型工况下的流场特征以及叶片的变形、应力分布,高压压气机转子叶尖径向间隙沿轴向变化的分布规律以及轴流压气机转子与机匣的间隙范围。计算结果显示在设计点和转速最高点,斜流压气机转子叶尖与机匣发生碰磨,与试验结果一致,验证了计算方法的正确性,也为建立合理有效的压气机径向间隙分析方法提供了思路。
Considering aerodynamic, centrifugal and temperature load coupling, aero-engine radial clearance analysis model is established for the high-pressure compressor of aeroengine. The flow field characteristics and the deformation and stress distribution of the blade under three typical operating conditions are obtained. Axial distribution of radial clearance of rotor tip in high-pressure compressor and the range of clearance between axial compressor rotor and receiver. The calculated results show that at the design point and the highest rotational speed, the tip of the rotor of the oblique-flow compressor collides with the casing, which is consistent with the experimental results, which verifies the correctness of the calculation method and establishes a reasonable and effective radial clearance analysis for the compressor Method provides ideas.