轴流压气机转子叶尖片削机理研究  

The Analysis of Attenuated Blade Tip Mechanism on Axial Compressor Rotor

作　　者：王维[1] 楚武利[1] 张皓光[1] 米攀[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《机械科学与技术》2012年第10期1578-1583,共6页Mechanical Science and Technology for Aerospace Engineering

基　　金：西北工业大学研究生创业种子基金项目(z2011038)资助

摘　　要：为了分析叶尖片削对压气机转子气动性能影响的机理,对一亚音速轴流压气机转子试验研究的基础上,采用全三维的数值方法计算了原型及6种片削结构的全工况特性。从压比、效率和失速裕度3个方面分析了片削对转子气动性能影响的机理,得出以下结论:叶尖片削使总压比和效率有所提升,失速裕度略有下降;片削通过增大压力面曲率及吸力面前缘来流攻角增加了叶顶加功能力;片削降低了叶顶后部泄漏流的反流程度,从而降低了叶顶吸力面附面层分离损失、主流/泄漏流掺混损失及尾迹损失,压力面潜流损失略有增加,总体上流动损失降低;片削增大了叶顶前部泄漏流的反流程度,连同吸力面来流攻角的增加造成主流/泄漏流交接面前移,导致转子失速裕度下降。In order to clarify the mechanism of attenuated blade tip effect on the aerodynamic performance of com- pressor rotor, the three-dimensional numerical simulation investigation is performed on the original model and six new models based on the experimental results of a subsonic compressor rotor. Following the analysis of total pres- sure ratio,efficiency and stall margin we draw the following conclusions： Attenuated blade tip improves the total pressure ratio and efficiency but at the same time decreases stall margin slightly; The improvement of suction sur- face curvature and the incidence of incoming flow is the main cause of pressure ratio enhancement; Attenuated blade tip weakened the adverse degree of leakage in the rear of blade tip and thus deeresed the boundary layer sepa- ration loss, mainstream / leakage mixing loss and wake loss and the pressure surface flow loss increases slightly, the total loss comes down. The increasing of the adverse degree of leakage in the front of tip, together with the im- proved incoming flow incidence of suction surface, makes the interface of mainstream / leakage move forward which cuts down stall margin of the rotor.

关 键 词：轴流压气机 叶尖片削 失速裕度 泄漏流 机理 

分 类 号：V231.13[航空宇航科学与技术—航空宇航推进理论与工程]