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Research Papers

Calculation of Flow Instability Inception in High Speed Axial Compressors Based on an Eigenvalue Theory

[+] Author and Article Information
Xiaohua Liu

Aeroengine Airworthiness Certification Center,
China Academy of Civil Aviation Science
and Technology, CAAC,
No. 31 Guangximen Beili Jia,
Chaoyang District,
Beijing 100028, China
School of Energy and Power Engineering,
No. 37 Xueyuan Road,
Haidian District,
Beijing 100028, China
e-mail: Liuxh@sjp.buaa.edu.cn

Yanpei Zhou

Aeroengine Airworthiness Certification Center,
China Academy of Civil Aviation Science
and Technology, CAAC,
No. 31 Guangximen Beili Jia,
Chaoyang District,
Beijing 100028, China
e-mail: Zhouyp@mail.castc.org.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

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

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 22, 2014; final manuscript received October 2, 2014; published online December 11, 2014. Editor: Ronald Bunker.

J. Turbomach 137(6), 061007 (Jun 01, 2015) (9 pages) Paper No: TURBO-14-1250; doi: 10.1115/1.4028768 History: Received September 22, 2014; Revised October 02, 2014; Online December 11, 2014

This paper applies a theoretical model developed recently to calculate the flow instability inception point in axial high speed compressors system with tip clearance. After the mean flow field is computed by 3D steady computational fluid dynamics (CFD) simulation, a body force approach, which is a function of flow field data and comprises of one inviscid part and the other viscid part, is taken to duplicate the physical sources of flow turning and loss. Further by applying appropriate boundary conditions and spectral collocation method, a group of homogeneous equations will yield from which the stability equation can be derived. The singular value decomposition (SVD) method is adopted over a series of fine grid points in frequency domain, and the onset point of flow instability can be judged by the imaginary part of the resultant eigenvalue. The first assessment is to check the applicability of the present model on calculating the stall margin of one single stage transonic compressors at 85% rotational speed. The reasonable prediction accuracy validates that this model can provide an unambiguous judgment on stall inception without numerous requirements of empirical relations of loss and deviation angle. It could possibly be employed to check overcomputed stall margin during the design phase of new high speed compressors. The following validation case is conducted to study the nontrivial role of tip clearance in rotating stall, and a parameter study is performed to investigate the effects of end wall body force coefficient on stall onset point calculation. It is verified that the present model could qualitatively predict the reduced stall margin by assuming a simplified body force model which represents the response of a large tip clearance on the unsteady flow field.

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References

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Figures

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Fig. 1

Sketch of one stage compressor in meridian plane

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Fig. 2

The grids of NASA Rotor 37 for steady flow field calculation

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Fig. 3

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

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Fig. 4

Schematic of stage 35 (from Ref. [31])

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Fig. 9

The computed eigenvalues of Rotor 37 with 1.0 and 2.0 times design tip at 100% design speed: (a) RS and (b) DF

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Fig. 10

The effects of the end wall body force coefficient on the stall inception calculation: (a) mass flow on computed stall onset point and (b) RS

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Fig. 8

The computed performance of Rotor 37 with 1.0 and 2.0 times design tip at 100% design rotational speed: (a) total pressure ratio and (b) efficiency

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Fig. 7

The computed eigenvalues of stage 35 at 85% design speed: (a) RS and (b) DF

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Fig. 6

Distribution of computational grids

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Fig. 5

The total-to-static pressure ratio of stage 35 at 85% design rotational speed

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