Vortex control over end wall flow in compressor cascades

Yan Ping Tang; Mao Zhang Chen

Vortex control over end wall flow in compressor cascades

Yan Ping Tang^*
, Mao Zhang Chen

^*Corresponding author for this work

School of Aeronautic Science and Engineering

Beihang University

Research output: Contribution to journal › Conference article › peer-review

Abstract

Three methods of vortex control over the end wall flow in compressor cascades have been investigated experimentally. The total pressure loss at the exit of a linear compressor cascade is reduce 6.5%, 10.5% and 26.5% respectively by these methods for different incidences over a range of moderate-high values. The physics of these methods has been discussed and some new concepts of vortex control techniques in compressor cascades have been proposed.

Original language	English
Pages (from-to)	GT228 8p
Journal	American Society of Mechanical Engineers (Paper)
State	Published - 1990
Event	International Gas Turbine and Aeroengine Congress and Exposition - Brussels, Belg Duration: 11 Jun 1990 → 14 Jun 1990

Cite this

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title = "Vortex control over end wall flow in compressor cascades",

abstract = "Three methods of vortex control over the end wall flow in compressor cascades have been investigated experimentally. The total pressure loss at the exit of a linear compressor cascade is reduce 6.5\%, 10.5\% and 26.5\% respectively by these methods for different incidences over a range of moderate-high values. The physics of these methods has been discussed and some new concepts of vortex control techniques in compressor cascades have been proposed.",

author = "Tang, \{Yan Ping\} and Chen, \{Mao Zhang\}",

year = "1990",

language = "英语",

pages = "GT228 8p",

journal = "American Society of Mechanical Engineers (Paper)",

issn = "0402-1215",

note = "International Gas Turbine and Aeroengine Congress and Exposition ; Conference date: 11-06-1990 Through 14-06-1990",

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TY - JOUR

T1 - Vortex control over end wall flow in compressor cascades

AU - Tang, Yan Ping

AU - Chen, Mao Zhang

PY - 1990

Y1 - 1990

N2 - Three methods of vortex control over the end wall flow in compressor cascades have been investigated experimentally. The total pressure loss at the exit of a linear compressor cascade is reduce 6.5%, 10.5% and 26.5% respectively by these methods for different incidences over a range of moderate-high values. The physics of these methods has been discussed and some new concepts of vortex control techniques in compressor cascades have been proposed.

AB - Three methods of vortex control over the end wall flow in compressor cascades have been investigated experimentally. The total pressure loss at the exit of a linear compressor cascade is reduce 6.5%, 10.5% and 26.5% respectively by these methods for different incidences over a range of moderate-high values. The physics of these methods has been discussed and some new concepts of vortex control techniques in compressor cascades have been proposed.

UR - https://www.scopus.com/pages/publications/0025233216

M3 - 会议文章

AN - SCOPUS:0025233216

SN - 0402-1215

SP - GT228 8p

JO - American Society of Mechanical Engineers (Paper)

JF - American Society of Mechanical Engineers (Paper)

T2 - International Gas Turbine and Aeroengine Congress and Exposition

Y2 - 11 June 1990 through 14 June 1990

ER -

Vortex control over end wall flow in compressor cascades

Abstract

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