Theoretical Analysis and Numerical Simulation of Tip Clearance of 12-Stage High-pressure Compressor Rotor

Zhan Jiangzheng; Zhang Guang; Song Wenyan; Huang Chuanbing; Zhang Weigang

doi:10.13433/j.cnki.1003-8728.20190003

Volume 38 Issue 10

Oct. 2019

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Article Navigation > Mechanical Science and Technology for Aerospace Engineering > 2019 > 38(10): 1632-1640

Zhan Jiangzheng, Zhang Guang, Song Wenyan, Huang Chuanbing, Zhang Weigang. Theoretical Analysis and Numerical Simulation of Tip Clearance of 12-Stage High-pressure Compressor Rotor[J]. Mechanical Science and Technology for Aerospace Engineering, 2019, 38(10): 1632-1640. doi: 10.13433/j.cnki.1003-8728.20190003

Citation:

Zhan Jiangzheng, Zhang Guang, Song Wenyan, Huang Chuanbing, Zhang Weigang. Theoretical Analysis and Numerical Simulation of Tip Clearance of 12-Stage High-pressure Compressor Rotor[J]. Mechanical Science and Technology for Aerospace Engineering, 2019, 38(10): 1632-1640. doi: 10.13433/j.cnki.1003-8728.20190003

Citation:

Zhan Jiangzheng, Zhang Guang, Song Wenyan, Huang Chuanbing, Zhang Weigang. Theoretical Analysis and Numerical Simulation of Tip Clearance of 12-Stage High-pressure Compressor Rotor[J]. Mechanical Science and Technology for Aerospace Engineering, 2019, 38(10): 1632-1640. doi: 10.13433/j.cnki.1003-8728.20190003

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Theoretical Analysis and Numerical Simulation of Tip Clearance of 12-Stage High-pressure Compressor Rotor

doi: 10.13433/j.cnki.1003-8728.20190003

1.
School of Mechanical Engineering, Guilin University of Aerospace Technology, Guangxi Guilin 541004, China
2.
School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China
3.
School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China
4.
State Key Laboratory of Multi-phase Complex Systems, Institute of Process Engineering, Chinese Academy of Sciences, Beijing 100190, China

Received Date: 2018-09-19
Publish Date: 2019-10-05

Abstract

Abstract

To study the changes in the tip clearance of a 12-stage high-pressure compressor rotor in different engine operation conditions, with its thermal, mechanical and aerodynamic loads considered, a modified and reduced theoretical model was set up. With the model, the changes in different engine operation conditions were studied. Then the 3D model of the compressor rotor was built and more changes in the tip clearance were studied through computer simulation, which turned out to coincide with the changes in different engine operation conditions. The great changes in the moment of the tip clearance were simulated with the finite element analysis software ANSYS. The fluid-solid-thermal coupling method was adopted; the precise radial displacement of the compressor rotor and the compressor case along the axial direction was obtained, and the changes in the maximum tip clearance were calculated. In the maximum tip clearance, the compressor blade may probably scratch the compressor case. The study has a reference value for determining the tip clearance in compressor installation and the distribution of coating.
- compressors,
- rotors,
- tip clearance,
- computer simulation,
- mathematical model,
- fluid-solid-thermal coupling

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References(21)

References

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