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周向非均匀叶尖间隙对压气机性能影响的试验

向宏辉1,葛宁2,高杰3,唐凯1,4,杨荣菲5   

  1. 1. 中国航发四川燃气涡轮研究院
    2. 南京航空航天大学
    3. 中国燃气涡轮研究院
    4.
    5. 北京航空航天大学 能源与动力工程学院
  • 收稿日期:2017-06-07 修回日期:2017-08-26 发布日期:2017-08-31
  • 通讯作者: 向宏辉
  • 基金资助:
    四川省应用基础研究项目;航空动力基金

Experimental investigation of circumferential non-uniform tip clearance effect on axial compressor performance

  • Received:2017-06-07 Revised:2017-08-26 Published:2017-08-31

摘要: 以单级跨声速轴流压气机为研究对象,通过改变转子外机匣椭圆度产生周向稳态非均匀叶尖间隙布局结构,在高转速压气机试验器上详细开展了周向非均匀叶尖间隙对压气机性能特性与稳定边界影响的试验研究。同时,结合转子叶尖间隙流场动态压力精细化测量,揭示了周向非均匀叶尖间隙触发压气机内部流动失稳的物理机制。试验结果表明:转子叶尖周向非均匀间隙对压气机流量、压比和效率基本没有产生影响,但对气动稳定性具有显著影响。随着转子机匣椭圆度增大,稳定工作边界逐渐向右下方偏移,压气机稳定工作范围不断减小;不同转速下,压气机稳定裕度损失程度并不相同,高转速工作区域的压气机稳定裕度损失程度要大于中低转速工作区域;周向非均匀叶尖间隙会导致原有转子叶片气动负荷沿径向重新分布,弱化转子叶片尖部气动加功能力;设计转速时,相比于小间隙情况,大间隙下的泄漏涡与通道激波相互作用,使得相邻叶片压力面侧的高静压低速区域扩大,加重对转子通道的堵塞作用。

关键词: 跨声速轴流压气机, 周向非均匀叶尖间隙, 流动失稳, 叶尖泄漏涡, 试验研究

Abstract: The steady circumferential non-uniform tip clearance structure was given by changing the ellipticity of rotor casing in a transonic single axial compressor. The effect of circumferential non-uniform rotor tip clearance on perfor-mance characteristic and stability working boundary of the compressor was experimented detailly on a high rotating speed compressor test facility. The mechanism of the internal flow instability of the compressor induced by the circumferential non-uniform tip clearance was also presented by measuring the dynamic pressure flowfield parameters of rotor tip clearance. The experimental results show that the circumferential non-uniform tip clearance has almost no effect on the mass flow, pressure ratio and adiabatic efficiency of the compressor, but it has significant effect on the aerodynamic stability of the compressor. As the ellipticity of rotor casing raised, the stability operation range of the compressor decreased. The stability margin loss is higher at high speed working area than that at middle and low speed working area. The circumferential non-uniform tip clearance can lead to the radial redistribution of aerodynamic load of the compressor rotor blade and weaken work capacity at rotor blade tip area. At design speed, compared to the small tip clearance, as a result of the interaction between tip leakage vortex and passage shock with the large tip clearance, the high static pressure area at the pressure surface of adjacent blade enlarges, and the blocking effect on rotor passage becomes more serious.

Key words: transonic axial compressor, circumferential non-uniform tip clearance, flow instability, tip clearance leakage vortex, experimental investigation