摘要
为了控制航空发动机压气机叶片损伤继续发展,通常采用孔探打磨进行修理。为研究其带来的影响,选取跨声速压气机Rotor37为研究对象,构建了不同叶高的叶片前缘打磨修理模型,采用数值模拟方法,研究了打磨修理对跨声速压气机气动性能的影响,结果表明:叶片前缘打磨修理使压气机整体性能下降,压比减小,效率降低,使堵塞点流量减小,而对失速流量点基本没有影响;不同叶高的打磨修理中心对压气机气动性能影响趋势一致影响幅度相当,但打磨叶高的不同造成压气机内部流场变化;叶片前缘打磨后,打磨处激波前马赫数增加,激波强度增大,影响效果随着叶高的增加而增加;压气机进口因为叶片打磨而造成相对动能在叶片打磨处附近降低。
In order to control the damage of aero-engine compressor blade,it is usually repaired by borescope blending.The compressor models with different blending location of blade height are built for numerical simulation for researching on influence of blending repair on transonic compressor performance which are based on Rotor 37.The results show that the blade leading edge blending leads to the decrease of overall performance,pressure ratio and efficiency,reduce choke point flow,and no effect on the stall point flow.The influence of blending repair center with different blade height on the compressor aerodynamic performance is the same,with the same amplitude.But the different blade height causes the change of compressor internal flow field.The Mach number before the shock wave increases at the blending location,and the shock wave intensity increases.The effect increases with the increase of blade height.The relative kinetic energy at the compressor inlet decreases near the blade blending location due to blending.
作者
赖安卿
李世林
谭燕
LAI An-qing;LI Shi-lin;TAN Yan(Civil Aviation Flight University of China,Sichuan Guanghan618307,China)
出处
《机械设计与制造》
北大核心
2021年第3期19-21,26,共4页
Machinery Design & Manufacture
基金
国家自然科学基金—航空发动机叶片检测与性能分析关键技术研究(u1633127)
中国民用航空飞行学院科学研究基金—民航发动机叶片缺陷机理及性能分析研究(J2019-001)
民航发动机部件健康管理技术研究(J2016-35)
航空发动机叶片积垢的数值模拟研究(Q2018-122)。
关键词
压气机
打磨
修理
气动性能
数值模拟
Compressor
Borescope Blending
Repair
Aerodynamic Performance
Numerical Simulation
