Influence of shock waves/leakage vortex/boundary layer separation interaction in a single-stage transonic axial compressor

Fang Xie; Wu Li Chu; Hao Guang Zhang

Influence of shock waves/leakage vortex/boundary layer separation interaction in a single-stage transonic axial compressor

Fang Xie, Wu Li Chu, Hao Guang Zhang

School of Power and Energy

Research output: Contribution to journal › Article › peer-review

16 Scopus citations

Abstract

Three-dimensional (3-D) numerical simulations were conducted to analyze the flow field in transonic rotors Rotar 37. The results with design tip clearance were compared with no tip clearance condition. Mutual influence of shock, boundary layer separation, clearance leakage the vortex accelerated the occurrence of stalled. Reduce clearance can enlarge the steady border. The suction position applied on passive control technology to improve port flow condition was given.

Original language	English
Pages (from-to)	425-430
Number of pages	6
Journal	Hangkong Dongli Xuebao/Journal of Aerospace Power
Volume	27
Issue number	2
State	Published - Feb 2012

Keywords

Axial compressor
Boundary layer separation
Shock
Tip leakage vortex (TLV)
Transonic

Cite this

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title = "Influence of shock waves/leakage vortex/boundary layer separation interaction in a single-stage transonic axial compressor",

abstract = "Three-dimensional (3-D) numerical simulations were conducted to analyze the flow field in transonic rotors Rotar 37. The results with design tip clearance were compared with no tip clearance condition. Mutual influence of shock, boundary layer separation, clearance leakage the vortex accelerated the occurrence of stalled. Reduce clearance can enlarge the steady border. The suction position applied on passive control technology to improve port flow condition was given.",

keywords = "Axial compressor, Boundary layer separation, Shock, Tip leakage vortex (TLV), Transonic",

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AU - Chu, Wu Li

AU - Zhang, Hao Guang

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Y1 - 2012/2

N2 - Three-dimensional (3-D) numerical simulations were conducted to analyze the flow field in transonic rotors Rotar 37. The results with design tip clearance were compared with no tip clearance condition. Mutual influence of shock, boundary layer separation, clearance leakage the vortex accelerated the occurrence of stalled. Reduce clearance can enlarge the steady border. The suction position applied on passive control technology to improve port flow condition was given.

AB - Three-dimensional (3-D) numerical simulations were conducted to analyze the flow field in transonic rotors Rotar 37. The results with design tip clearance were compared with no tip clearance condition. Mutual influence of shock, boundary layer separation, clearance leakage the vortex accelerated the occurrence of stalled. Reduce clearance can enlarge the steady border. The suction position applied on passive control technology to improve port flow condition was given.

KW - Axial compressor

KW - Boundary layer separation

KW - Shock

KW - Tip leakage vortex (TLV)

KW - Transonic

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JO - Hangkong Dongli Xuebao/Journal of Aerospace Power

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IS - 2

ER -

Influence of shock waves/leakage vortex/boundary layer separation interaction in a single-stage transonic axial compressor

Abstract

Keywords

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