Research Papers: Flows in Complex Systems

Calculation of Stall Margin Enhancement With Micro-Tip Injection in an Axial Compressor

[+] Author and Article Information
Xiaohua Liu

School of Aeronautics and Astronautics,
Shanghai Jiao Tong University,
Shanghai 200240, China
e-mail: xiaohua-liu@sjtu.edu.cn

Jinfang Teng

School of Aeronautics and Astronautics,
Shanghai Jiao Tong University,
Shanghai 200240, China

Jun Yang

School of Energy and Power Engineering,
University of Shanghai for Science
and Technology,
Shanghai 200093, China
e-mail: yangjun@usst.edu.cn

Xiaofeng Sun, Dakun Sun, Chen He

School of Energy and Power Engineering,
Beihang University,
Beijing 100191, China

Juan Du

Institute of Engineering Thermophysics, CAS,
Beijing 100190, China

1Corresponding author.

Contributed by the Fluids Engineering Division of ASME for publication in the JOURNAL OF FLUIDS ENGINEERING. Manuscript received September 20, 2018; final manuscript received January 9, 2019; published online March 4, 2019. Assoc. Editor: Kwang-Yong Kim.

J. Fluids Eng 141(8), 081109 (Mar 04, 2019) (10 pages) Paper No: FE-18-1631; doi: 10.1115/1.4042561 History: Received September 20, 2018; Revised January 09, 2019

Although steady micro-injection is experimentally validated as an attractive method in improving the stall margin of axial compressors, up to now a fast prediction of stall boundary remains some way off. This investigation is to propose such a prediction model. A flow stability model is developed to further consider the effect of high-speed micro-injection. After the base flow field is calculated by steady computational fluid dynamics simulation, a body force model is applied to reproduce the effect of blade on the flow turning and loss. A group of homogeneous equations are obtained based on linearized Navier–Stokes equations and harmonic decomposition of small flow disturbance. The stall onset point can be judged by the imaginary part of the resultant eigenvalue. After the existing experimental results are summarized, an unsteady numerical simulation reveals that the computed characteristics and radial profile of pressure rise coefficient are almost unchanged. The unsteady response of compressor to the micro-injection is preliminarily verified based on the observation of the disturbed spillage of tip leakage flow. It is verified that this approach can provide a qualitative assessment of stall point with acceptable computational cost. Both high injection velocity and short axial gap between injector and rotor leading edge are beneficial for the stall margin extension. These theoretical findings agree well with experimental measurements. It is inferred that the spillage of tip clearance flow, which is inward pushed by higher speed injection with shortened distance away from rotor, could lead to further stable flow field.

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Fig. 1

Meridional plane of a compressor with an arbitrary streamline

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Fig. 2

Sketch of a simplified body force model

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Fig. 3

Low-speed three-stage compressor test rig (Adapted from Nie et al. [18])

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Fig. 4

Stall margin improvement for different axial gap between injectors and leading edge

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Fig. 5

Stall margin enhancement with the increased nondimensional injection velocity

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Fig. 6

Schematic of single rotor with tip injector

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Fig. 7

Contour of nondimensional axial velocity at 99.0% span

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Fig. 8

Computed performance line of the steady and unsteady cases with high-speed and low-speed injection. Figure (b) is an enlarged view of local range.

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Fig. 9

Comparison of radial profile of relative total pressure coefficient in front of and behind rotor

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Fig. 10

Numerical probe at 98.9% span inside the blade passage (PS = pressure side and SS = suction side)

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Fig. 11

Unsteady static pressure rise coefficient monitored by the numerical probe in one period Tb

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Fig. 12

Contour of negative axial velocity for three time steps in one blade passing period Tb at flow coefficient of 0.345

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Fig. 13

Comparison of computed static pressure rise and measured performance line of the single rotor

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Fig. 14

Computed damping factors of the theoretical model

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Fig. 15

Computed damping factor versus nondimensional injection velocity

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Fig. 16

Computed damping factor versus nondimensional gap between injector and rotor leading edge

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Fig. 17

Computed stall margin improvement versus nondimensional injection velocity



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