实验流体力学Issue(5)：81-85,5.DOI:10.11729/syltlx20130083
0．6m连续式跨声速风洞AV90-3轴流压缩机喘振边界测试研究
Surge margin test and research of AV90-3 axial compressor in 0 .6m continuous transonic wind tunnel
周恩民 1程松 1许靖 2刘恺 1张文 1熊波 1王仪田2
作者信息
- 1. 中国空气动力研究与发展中心，四川 绵阳 621000
- 2. 陕鼓鼓风机 集团 有限公司，西安 710075
- 折叠
摘要
Abstract
In order to determine the AV90-3 axial compressor’s safe working area in the 0.6m continuous wind tunnel,the test method of reducing the compressor’s inlet volume flow to deter-mine the surge point and that of monitoring the pressure to distinguish the surge are employed. The surge margin of the AV90-3 axial compressor is accurately determined.It comes to the con-clusion that the surge margin is extended to the top-right as the static blade angle increases and the surge margins both above and below atmospheric pressure fit well with that at atmospheric pressure.The surge is prevented occurring effectively by selecting the ratio of the inlet volume flow to the pressure as the anti-surge control parameter,setting alarm and anti-surge curve,and taking by-pass circumfluence.It can provide reference to large-scale continuous wind tunnel com-pressor’s surge margin test and anti-surge control.关键词
连续式风洞/轴流压缩机/喘振点/喘振边界/防喘振曲线Key words
continuous wind tunnel/axial compressor/surge point/surge margin/anti-surge curve分类
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周恩民,程松,许靖,刘恺,张文,熊波,王仪田..0．6m连续式跨声速风洞AV90-3轴流压缩机喘振边界测试研究[J].实验流体力学,2014,(5):81-85,5.
