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Investigation on the influence of the structure parameters of blade tip recess on the performance of axial flow compressor
Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering ( IF 1.1 ) Pub Date : 2021-03-11 , DOI: 10.1177/0954410021998101
Song Yan 1 , WuLi Chu 1
Affiliation  

As one of the important components of an aero engine, the compressor plays an important role in improving the performance of the aero engine. The blade tip recess (BTR) has great potential and advantages in improving the performance of the compressor. It is very important to clarify the influence of the structure parameters of the BTR on the performance of the compressor. In this study, the two-dimensional results of the BTR were analyzed by using the method of variance analysis, and the two-dimensional calculation results of the BTR were used to guide the design of the BTR of axial flow compressor rotor. In the NASA Rotor 35, the influence rules of the structure parameters of BTR on the recess effect that was basically the same as the two-dimensional conditions. The optimization of the rotor BTR structure parameters may be achieved by the two-dimensional calculation. The flow field analysis showed the BTR can retard the growth rate of the blockage area of the leading edge of blade tip by weakening the tip clearance leakage flow intensity that delayed the occurrence of blade tip blockage and improved the aerodynamic stability of the rotor.



中文翻译:

叶片尖端凹槽结构参数对轴流压缩机性能的影响研究

作为航空发动机的重要部件之一,压缩机在改善航空发动机的性能方面起着重要作用。叶片尖端凹槽(BTR)在改善压缩机性能方面具有巨大潜力和优势。阐明BTR的结构参数对压缩机性能的影响非常重要。本研究采用方差分析的方法对BTR的二维结果进行了分析,并以BTR的二维计算结果指导了轴流压气机转子BTR的设计。在NASA转子35中,BTR的结构参数对凹陷效应的影响规律与二维条件基本相同。转子BTR结构参数的优化可以通过二维计算来实现。流场分析表明,BTR可以通过减弱叶尖间隙泄漏流强度来延迟叶尖前缘堵塞区域的生长速度,从而延迟叶尖堵塞的发生并提高转子的空气动力学稳定性。

更新日期:2021-03-11
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