叶片破损对压气机性能的影响  

Effect of blade breakage on compressor performance

作　　者：王忠义[1] 赵佳 张晶 王萌[1] WANG Zhongyi;ZHAO Jia;ZHANG Jing;WANG Meng(College of Power and Energy Engineering,Harbin Engineering University,Harbin 150001,China;CSSC Huangpu Wenchong Shipbuilding Company Limited,Guangzhou 510715,China)

机构地区：[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

出　　处：《哈尔滨工程大学学报》2024年第4期722-729,共8页Journal of Harbin Engineering University

基　　金：国家自然科学基金项目(52101348);国家科技重大专项(J2019-Ⅲ-0017-0061).

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0.6631%、绝热效率降低0.7877%,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。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 0.6631%and 0.7877%,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 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]