叶片破损对压气机性能的影响
Effect of blade breakage on compressor performance
王忠义 1赵佳 1张晶 2王萌1
作者信息
- 1. 哈尔滨工程大学 动力与能源工程学院,黑龙江 哈尔滨 150001
- 2. 中船黄埔文冲船舶有限公司,广东 广州 510715
- 折叠
摘要
为了研究叶片破损对压气机内部流场的影响机理,本文针对带有破损的跨音速压气机叶片进行气动性能变化规律和机理研究.通过NASA rotor 37 实验结果验证了计算方法的准确性,利用数值仿真研究了叶片破损对压气性能的影响规律,并对 2 种典型工况下叶片破损前后的流场结构进行对比分析,探讨引起性能变化的具体原因.研究表明:叶片破损会导致压气机的压比降低 0.663 1%、绝热效率降低 0.787 7%,且压气机的稳定裕度降低更为明显.叶尖破损主要对叶顶流场结构产生影响,使叶顶区域泄漏流增强,当其与激波相互作用时,通道内产生了流动堵塞和流动损失.本文研究成果可为实际服役中的航空发动机特性评定提供理论参考.
Abstract
The change rule and mechanism of the aerodynamic performance of transonic compressor blades with damage are studied to investigate the effect of blade damage on compressor performance.The accuracy of the calcu-lation method is verified by the results of the NASA rotor 37 experiment.The influence rule of blade breakage on compressed air performance is investigated through numerical simulation.The flow field structure before and after blade breakage under two typical working conditions is then compared and analyzed to explore the specific causes for performance changes.The results show that the pressure ratio and adiabatic efficiency of the compressor de-crease by 0.663 1%and 0.787 7%,respectively,and that the stability margin of the compressor decreases more obviously.The tip damage mainly affects the structure of the tip flow field and enhances the leakage flow in the tip area.When it interacts with shock waves,flow blockage and flow loss occur in the channel.The findings of this study can provide a theoretical reference for the performance evaluation of aircraft engines in actual service.
关键词
跨音速压气机/叶片破损/数值模拟/气动性能/压比/效率/稳定裕度/叶顶泄漏流Key words
transonic compressor/blade damage/numerical simulation/aerodynamic performance/pressure ratio/efficiency/stability margin/tip leakage flow引用本文复制引用
基金项目
国家自然科学基金(52101348)
国家科技重大专项(J2019-Ⅲ-0017-0061)
出版年
2024
国家科技期刊平台
NSTL
维普
万方数据