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Research Papers

Stall Inception Analysis of Transonic Compressors With Chordwise and Axial Sweep

[+] Author and Article Information
Chen He

School of Energy and Power Engineering,
Beihang University,
No. 37 Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: hechen@buaa.edu.cn

Dakun Sun

School of Energy and Power Engineering,
Beihang University,
No. 37 Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: sundk@buaa.edu.cn

Xiaofeng Sun

School of Energy and Power Engineering,
Beihang University,
No. 37 Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: sunxf@buaa.edu.cn

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received October 22, 2017; final manuscript received November 3, 2017; published online February 21, 2018. Editor: Kenneth Hall.

J. Turbomach 140(4), 041009 (Feb 21, 2018) (11 pages) Paper No: TURBO-17-1195; doi: 10.1115/1.4038873 History: Received October 22, 2017; Revised November 03, 2017

This paper concentrates on the stall inception analysis of transonic compressors with chordwise and axial sweep. A new prediction approach of stall inception is developed based on global stability analysis and immersed boundary theory, which makes it possible to take both the concrete blade geometry and the complicated base flow into consideration. The prediction of stall inception boils down to an eigenvalue problem. Spectral collocation method is adopted to discretize the eigenvalue equations and the eigenvalues are solved by using singular value decomposition method. The developed prediction approach is validated on two different typical transonic compressors, a single stage compressor and an isolated-rotor compressor, which shows a good agreement with the experimental data. The latter is adopted as a baseline rotor for the investigation of chordwise and axial sweep. By adjusting the stacking line of the baseline rotor, a series of swept rotors are modeled and the stall inception behavior of them is predicted by using the developed approach. The comparison of stall inception behaviors between these rotors is presented, and in combination with steady flow analyses, the effects of sweep features on the stall inception in transonic compressors are discussed.

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References

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Figures

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Fig. 1

Experimental and computational characteristics of NASA stage 35: (a) total pressure ratio and (b) adiabatic efficiency

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Fig. 2

Meridional grid of NASA stage 35 for eigenvalue calculation

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Fig. 3

The evolution of eigenvalue along with throttling process for NASA stage 35: (a) damping factor and (b) relative speed

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Fig. 4

Experimental and computational characteristics of NASA rotor 37: (a) total pressure ratio and (b) adiabatic efficiency

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Fig. 5

Two kinds of definition of sweep: (a) chordwise sweep and (b) axial sweep

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Fig. 6

Meridional view of chordwise swept blade and axially swept blade: (a) BCS_10 and (b) BAS_10

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Fig. 7

The comparison of characteristics of swept rotors and that of rotor 37: (a) total pressure ratio of BCS rotors, (b) adiabatic efficiency of BCS rotors, (c) total pressure ratio of BAS rotors, (d) adiabatic efficiency of BAS rotors, (e) total pressure ratio of FCS rotors, (f) adiabatic efficiency of FCS rotors, (g) total pressure ratio of FAS rotors, and (h) adiabatic efficiency of FAS rotors

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Fig. 8

The comparison of eigenvalues of swept rotors and that of rotor 37: (a) damping factor of BCS rotors, (b) relative speed of BCS rotors, (c) damping factor of BAS rotors, (d) relative speed ofBAS rotors, (e) damping factor of FCS rotors, (f) relative speed of FCS rotors, (g) damping factor of FAS rotors, and (h) relative speed of FAS rotors

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Fig. 9

Predicted stall inception point, NCP, and NDP of swept rotors and rotor 37

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Fig. 10

The comparison of spanwise distribution of total pressure: (a) BCS rotors and (b) BAS rotors

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Fig. 11

The comparison of spanwise distribution of adiabatic efficiency: (a) BCS rotors and (b) BAS rotors

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Fig. 12

The comparison of spanwise distribution of entropy production: (a) BCS rotors and (b) BAS rotors

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