Effect of circumferential non-uniform tip clearance on performance of axial compressor

XIANG Honghui; GE Ning; GAO Jie; TANG Kai; YANG Rongfei

doi:10.7527/S1000-6893.2017.121491

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2018 , Vol. 39 >Issue 2: 121491 - 121491

DOI: https://doi.org/10.7527/S1000-6893.2017.121491

Fluid Mechanics and Flight Mechanics

Effect of circumferential non-uniform tip clearance on performance of axial compressor

XIANG Honghui ,
GE Ning ,
GAO Jie ,
TANG Kai ,
YANG Rongfei

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1. Laboratory of Turbomachinery Experiment, AECC Sichuan Gas Turbine Establishment, Jiangyou 621703, China;
2. College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received date: 2017-06-07

Revised date: 2017-08-31

Online published: 2018-02-11

Supported by

Aviation Power Foundation of China (6141B090303); Applied Basic Research Project of Sichuan Province (2017JY0040)

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Abstract

A steady circumferential non-uniform tip clearance structure is developed by changing the ellipticity of the rotor casing in a transonic single axial compressor. The effect of the circumferential non-uniform rotor tip clearance on the performance characteristics and stability working boundary of the compressor is experimented on a test facility of the high rotating speed compressor. The mechanism of the internal flow instability of the compressor induced by the circumferential non-uniform tip clearance is also presented by measuring the dynamic pressure flowfield parameters of the 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 the rotor casing increases, the stability operation range of the compressor decreases. The stability margin loss is higher at the high speed working area than that at the middle and low speed working areas. The circumferential non-uniform tip clearance can lead to radial redistribution of aerodynamic load of the compressor rotor blade, and then weaken the work capacity at the rotor blade tip area. Different from that with the small tip clearance, with the large tip clearance, the tip leakage vortex interacts with the passage shock at the design speed, and the high static pressure area at the pressure surface of the adjacent blade enlarges to result in more serious blocking effect on the rotor passage.

Key words： axial compressors; tip leakage vortex; aerodynamic performance; tip clearance; elliptic casing; experimental investigation

Cite this article

XIANG Honghui , GE Ning , GAO Jie , TANG Kai , YANG Rongfei . Effect of circumferential non-uniform tip clearance on performance of axial compressor[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018 , 39(2) : 121491 -121491 . DOI: 10.7527/S1000-6893.2017.121491

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