Research Papers: Flows in Complex Systems

Basic Studies of Flow-Instability Inception in Axial Compressors Using Eigenvalue Method

[+] Author and Article Information
Xiaohua Liu

Aeroengine Airworthiness Certification Center Preparatory Office,
China Academy of Civil Aviation
Science and Technology,
School of Energy and Power Engineering,
Beihang University,
No. 37 Xueyuan Road,
Haidian District, Beijing 100191, China
e-mail: Liuxh@sjp.buaa.edu.cn

Dakun Sun

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

Contributed by the Fluids Engineering Division of ASME for publication in the JOURNAL OF FLUIDS ENGINEERING. Manuscript received June 15, 2013; final manuscript received December 23, 2013; published online January 27, 2014. Assoc. Editor: Zvi Rusak.

J. Fluids Eng 136(3), 031102 (Jan 27, 2014) (9 pages) Paper No: FE-13-1377; doi: 10.1115/1.4026417 History: Received June 15, 2013; Revised December 23, 2013

This paper applies a theoretical model developed recently to calculate the flow-instability inception of an axial transonic single stage compressor. After several calculation methods are compared, the singular value decomposition method is adopted to solve the resultant eigenvalue problem in which the involved matrix is rather large due to multistage configuration. The onset point of flow instability is judged by the imaginary part of the resultant eigenvalue. The effect of flow compressibility on the stall onset point calculation for the transonic rotor is studied. It is shown that the compressibility of flow perturbation plays a major role in computing high speed compressor flow stability.

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Fig. 1

Sketch of one stage compressor on the meridian plane

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Fig. 2

Sketch of body force in blade-to-blade surface and two points (a and b) on one streamline

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Fig. 3

Sketch of the entries distribution of matrix involved in the established stability equation

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Fig. 4

An example of the contour of the reciprocal number of condition number of matrix X on coarse grids of eigenvalue

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Fig. 5

Schematic of stage 35 (from Reid and Moore [28])

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Fig. 6

Total-to-static pressure ratio of stage 35 at design rotational speed

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Fig. 7

Distribution of computational grids

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Fig. 8

Computed eigenvalues of stage 35 at design rotational speed: (a) Relative speed, and (b) damping factor

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Fig. 9

Computed eigenvalues of rotor 37 at 60% design rotational speed: (a) Relative speed, and (b) damping factor

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Fig. 10

Computed eigenvalues of rotor 37 at design rotational speed: (a) Relative speed, and (b) damping factor




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