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汽车安全与节能学报 ›› 2015, Vol. 6 ›› Issue (04): 392-398.DOI: 10.3969/j.issn.1674-8484.2015.04.013

• 汽车节能与环保 • 上一篇    下一篇

具有前缘前掠叶片的跨音速离心压气机流场的数值研究

刘艳明1，崔 庆1，郑新前2，郭龙凯1   

  1. 1. 北京理工大学 宇航学院，北京 100081 ；2. 清华大学 汽车安全与节能国家重点实验室，北京 100084
  • 收稿日期:2015-09-07 出版日期:2015-12-25 发布日期:2015-12-28
  • 作者简介:第一作者 / First author ： 刘艳明(1976 － )，女( 汉)，河南，副教授。E-mail: liuym@bit.edu.cn. 第二作者 / Second author ： 崔庆(1986 － )，男( 汉)，陕西，硕士研究生。E-mail: cuiqing-bit@163.com.
  • 基金资助:

    汽车安全与节能国家重点实验室开放基金(KF14011)

Numerical investigation of flow field for transonic centrifugal compressor with blade leading edge forward sweep

LIU Yanming1, CUI Qing1, ZHENG Xinqian2, GUO Longkai1   

  1. 1. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;
    2. State Key Laboratory of Automotive Safety and Energy, Tsinghua University, Beijing 100084, China
  • Received:2015-09-07 Online:2015-12-25 Published:2015-12-28

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摘要：

采用商业叶片造型软件Concepts NREC 压气机设计出具有不同前缘前掠角 (α 为10°﹑15°﹑
20°) 叶片的3 种方案的涡轮增压跨音速离心压气机，并进行数值模拟和对比分析，研究叶片前缘前掠
对压气机流场特性的影响。结果表明：与无掠方案相比，主叶片前缘前掠在提高压气机流通能力及失
速裕度方面有一定的优势，其中15° 方案的流通能力最强，20° 方案的失速裕度最大；随着前缘掠角由0°
增加到20°，在堵塞工况下压气机内部激波强度减弱7.2%，在最高效率工况下减弱3.4%，同时，叶
轮通道下游低能流团范围及强度均有一定改善；在3 种掠叶片方案中，10° 掠角方案的压气机内部流动
情况最好，其整体效率较普通压气机提高0.72%，压比提高0.62%。

关键词:  , 离心压气机, 前缘前掠, 流场特性, 激波结构, 低能流团

Abstract:

Three turbo-charged transonic centrifugal compressors were designed with different forward-swept
angles (10°, 15°, 20°) of blade leading edge by means of the commercial software Concepts NREC. Numerical
simulation and comparative analysis were conducted to investigate the influence of blade leading edge forward
sweep on the flow field characteristics in the compressors. The results show that the compressors with forwardswept
main blade possess certain advantages in flow capacity and stall margin over unswept compressor, the
scheme of 15° has the largest flow capacity, and the scheme of 20° has the biggest stall margin. As forwardswept
angle increases from 0°to 20°, the passage shock strength decreases 7.2% under the choke condition,
while decreases 3.4% under the peak efficiency condition; the range and strength of low-energy flow mass in
impeller channel are improved in some degree. The scheme of 10° is the optimal scheme among the 3 different
forward-swept blades with the compressor efficiency increasing by 0.72% and pressure ratio increasing by 0.62%.

Key words: centrifugal compressors, forward-swept leading edge, flow field characteristics, shock wave structure, low-energy fluid