Research Papers

Numerical Investigations of the Coupled Flow Through a Subsonic Compressor Rotor and Axial Skewed Slot

[+] Author and Article Information
Xingen Lu

School of Power and Energy, Northwestern Polytechnical University, Xi’an, 710072, P.R.C.xingenlu@hotmail.com

Wuli Chu, Yangfeng Zhang

School of Power and Energy, Northwestern Polytechnical University, Xi’an, 710072, P.R.C.

Junqiang Zhu

 Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 10080, P.R.C.

J. Turbomach 131(1), 011001 (Sep 25, 2008) (8 pages) doi:10.1115/1.2948959 History: Received June 14, 2005; Revised November 16, 2006; Published September 25, 2008

In order to advance the understanding of the fundamental mechanisms of axial skewed slot casing treatment and their effects on the subsonic axial-flow compressor flow field, the coupled unsteady flow through a subsonic compressor rotor and the axial skewed slot was simulated with a state-of-the-art multiblock flow solver. The computational results were first compared with available measured data, that showed the numerical procedure calculates the overall effect of the axial skewed slot correctly. Then, the numerically obtained flow fields were interrogated to identify the physical mechanism responsible for improvement in stall margin of a modern subsonic axial-flow compressor rotor due to the discrete skewed slots. It was found that the axial skewed slot casing treatment can increase the stall margin of subsonic compressor by repositioning of the tip clearance flow trajectory further toward the trailing of the blade passage and retarding the movement of the incoming∕tip clearance flow interface toward the rotor leading edge plane.

Copyright © 2009 by American Society of Mechanical Engineers
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Figure 1

Tested axial skewed slots casing treatment configuration

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Figure 2

Blade-to-blade view of grids on the rotor-casing treatment sliding interface

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Figure 3

Unsteady pressure signal in a representative slot and its Fourier transformation

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Figure 4

Computed and measured compressor map for 71% design speed: (a) total-to-static pressure ratio; (b) isentropic efficiency

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Figure 5

Comparison of predicted and experimental radial isentropic efficiency for the rotor with and without axial skewed slot casing treatment

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Figure 6

The distribution of circumferentially averaged total pressure loss coefficient at smooth wall stall mass flow: (a) smooth wall; (b) axial skewed slot

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Figure 10

Predicted treatment slot velocity vector patterns for different instants during one blade passing period: (a) t=T∕4, (b) t=2T∕4, (c) t=3T∕4, and (d) t=4T∕4

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Figure 8

Computed tip clearance vortex particle traces at smooth wall stall mass flow rate: (a) smooth wall; (b) axial skewed slot

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Figure 9

Comparison of predicted near rotor tip blade loading

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Figure 7

Comparison of relative Mach number at 99% blade span at smooth wall stall mass flow: (a) smooth wall; (b) axial skewed slot




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