大预旋下离心压缩机进口结构与导叶掠角的改进研究

赵家毅; 王志恒; 席光; 赵阳

doi:10.7652/xjtuxb201711001

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大预旋下离心压缩机进口结构与导叶掠角的改进研究

更新时间：2025-07-09

- 大预旋下离心压缩机进口结构与导叶掠角的改进研究
- Improvements of Inlet Structure and Sweep-Angle of Guide Vane Inside a Centrifugal Compressor at Large Pre-Swirl
- 西安交通大学学报 2017年51卷第11期页码：1-6+50
- 作者机构：
  
  西安交通大学能源与动力工程学院,西安,710049
- 作者简介：
- 基金信息：
  
  : 2017-03-01。作者简介: 赵家毅(1990—),男,博士生;席光(通信作者),男,教授,博士生导师。基金项目: 国家自然科学基金项目资助(51236006,51576153)
- DOI：10.7652/xjtuxb201711001
  中图分类号： TK123
- 网络首发：2017-11-10，
  
  纸质出版：2017
- 稿件说明：
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赵家毅, 王志恒, 席光, 等. 大预旋下离心压缩机进口结构与导叶掠角的改进研究[J]. 西安交通大学学报, 2017,51(11):1-6+50.

Improvements of Inlet Structure and Sweep-Angle of Guide Vane Inside a Centrifugal Compressor at Large Pre-Swirl[J]. 2017, 51(11): 1-6+50.
赵家毅, 王志恒, 席光, 等. 大预旋下离心压缩机进口结构与导叶掠角的改进研究[J]. 西安交通大学学报, 2017,51(11):1-6+50. DOI： 10.7652/xjtuxb201711001.

Improvements of Inlet Structure and Sweep-Angle of Guide Vane Inside a Centrifugal Compressor at Large Pre-Swirl[J]. 2017, 51(11): 1-6+50. DOI： 10.7652/xjtuxb201711001.

摘要

为了解决大预旋下进口导叶诱发流动损失而降低进口预旋调节经济性的问题

将原进口导叶截面中前缘掠角改为相对顶端型线呈前掠

同时将传统衔接进口导叶处进气管道的顶端形状改为锥面。改进结构下进口导叶内部的二次流克服了大预旋下离心力引发的进口轮盘侧的大规模分离状况

改善了叶轮进口段的熵增情况。预旋角分别为+60°、-60°时

改进结构在宽流量范围内可以有效提升离心压缩机多变效率和总压比性能

提升幅值随流量的增大而升高; 在工况范围左边界基本保持不变的情况下

改进结构对大预旋下压缩机工况范围右边界的扩展效果明显。该结果表明

改进结构可以有效提升大预旋下压缩机的性能

具有良好的应用前景及推广潜力。

Abstract

At large pre-swirl

the flow loss induced by the inlet guide vane(IGV)usually degrades the economy of the regulation scheme. Aiming at reducing flow loss at large pre-swirl

the sweep angle at the leading edge of the IGV is changed in forward direction relative to the shroud line. The traditional shape of the shroud of the inlet pipe connecting with the IGV is modified to the cone. The secondary flow initiated within the improved design overcomes the considerable hub flow separation caused by the centrifugal force at the high pre-swirl. The situation of the entropy increase is heightened at the impeller inlet. The new structure efficiently improves the polytropic efficiency and the total pressure ratio of the centrifugal compressor within a wide operation range for the pre-swirl of +60 and -60 degrees. The improvements are enhanced with the increasing flow rate. While the left margin in the operation range remains constant

the right margin obviously widens.

关键词

Keywords

references

ZHAO J, WANG Z, XI G, et al. Investigation of performance and flow field of a centrifugal compressor under negative pre-swirl [C]∥ASME Turbo Expo 2015. New York, USA: ASME, 2015: V02CT42A026.

COPPINGER M, SWAIN E. Performance prediction of an industrial centrifugal compressor inlet guide vane system [J]. Proceedings of the Institution of Mechanical Engineers: Part A Journal of Power Energy, 2000, 214(2): 153-164.

MOHSENI A, BRAEMBUSSCHE R A V D, GOLDHAHN E, et al. Novel IGV designs for centrifugal compressors and their interaction with the impeller [J]. ASME Journal of Turbomachinery, 2012, 134(2): 2019-2029.

ZHANG Y, QI D, MAO Y. Experimental investigation and improvement of the inlet guide vane with plate vane in a centrifugal fan [J]. Proceedings of the Institution of Mechanical Engineers: Part A Journal of Power Energy, 2009, 223(4): 401-413.

谭佳健, 毛义军, 祁大同, 等. 离心式压缩机可调进口导叶研究综述 [J]. 风机技术, 2006(3): 44-48.

TAN Jiajian, MAO Yijun, QI Datong, et al. Research overview on adjustable inlet guide vane for centrifugal compressor [J]. Compressor Blower Fan Technology, 2006(3): 44-47.

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LIU Tianyi, QI Datong, TAN Jiajian, et al. Influence of equivalent prewhirl radius of guide vane passage on performance of centrifugal compressor [J]. Journal of Xi'an Jiaotong University, 2011, 45(3): 91-94.

范朝阳. 某离心式压缩机可调进口导叶叶型研究 [D]. 大连: 大连理工大学, 2013.

ZHENG X, HUANG Q, LIU A. Loss mechanisms and flow control for improved efficiency of a centrifugal compressor at high inlet prewhirl [J]. ASME Journal of Turbomachinery, 2016, 138: 101011.

XI G, ZHAO H, WANG Z. Trailing edge filings and a modified Stodola's slip factor for centrifugal impeller [C]∥ASME Turbo Expo 2015. New York, USA: ASME, 2015: V001T09A009.

SPALART P, ALLMARAS S. A one-equation turbulence model for aerodynamic flows [J]. La Recherche Aérospatiale, 2003, 439(1): 5-21.

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