离心压缩机的内蜗壳气动设计方法研究

高科; 党凌兮; 邓清华; 李军

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离心压缩机的内蜗壳气动设计方法研究

更新时间：2026-08-11

- 离心压缩机的内蜗壳气动设计方法研究
- Investigation on Aerodynamic Design Method of Inner Volute for Centrifugal Compressors
- 西安交通大学学报 2026年
- 作者机构：
  
  西安交通大学能源与动力工程学院，710049，西安
- 作者简介：
- 基金信息：
  
  国家重点研发计划资助项目(2023YFB4102203);国家自然科学基金联合基金资助项目。(U20A20303)
- DOI：
  中图分类号： TK14
- 收稿：2026-04-19，
  
  修回：2026-07-17，
  
  录用：2026-07-30，
- 稿件说明：
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高科, 党凌兮, 邓清华, 等. 离心压缩机的内蜗壳气动设计方法研究[J/OL]. 西安交通大学学报, 2026.

GAO Ke, DANG Lingxi, DENG Qinghua, et al. Investigation on Aerodynamic Design Method of Inner Volute for Centrifugal Compressors[J/OL]. JOURNAL OF XI’AN JIAOTONG UNIVERSITY, 2026.
高科, 党凌兮, 邓清华, 等. 离心压缩机的内蜗壳气动设计方法研究[J/OL]. 西安交通大学学报, 2026. DOI：

GAO Ke, DANG Lingxi, DENG Qinghua, et al. Investigation on Aerodynamic Design Method of Inner Volute for Centrifugal Compressors[J/OL]. JOURNAL OF XI’AN JIAOTONG UNIVERSITY, 2026. DOI：

摘要

为缩小离心压缩机蜗壳的径向尺寸、探究内蜗壳中的流动特性并提高其气动性能，本文基于角动量守恒原理提出了一种内蜗壳气动设计方法，借助全三维数值模拟，结合熵产理论与涡量分析方法，开展了流动损失分析与损失源定位。仿真结果表明，与平均速度法相比，在设计工况下角动量守恒法设计的蜗壳出口静压恢复系数提高了21.8%，总压损失系数降低了31.6%，速度均匀度增加了174%，该蜗壳流场整体较好，蜗舌处回流区域较小，保证了下游部件工作的稳定性；在蜗壳的轮盘侧与轮盖侧有两个流动损失较大的二次涡区域，蜗壳0-90°的周向流域内有较高的熵产率；在角动量守恒法设计的蜗壳的基础上，通过截面型线优化，使气流流动通畅并抑制二次涡的形成，蜗壳内熵产率与涡量均减小，二次涡强度降低，0-90°周向流域内流动情况改善，流动损失降低；与优化前相比，在设计工况下优化后的蜗壳出口静压恢复系数增加了13.7%，总压损失系数降低了18.1%，速度均匀度基本不变，蜗壳的综合性能得到提升。研究结果可以为蜗壳的气动设计方法和离心压缩机性能优化提供重要参考。

Abstract

To reduce the radial size of centrifugal compressor volutes

investigate the flow characteristics

and improve its aerodynamic performance

an aerodynamic design method based on angular momentum conservation principal is proposed for inner volute. Using full three-dimensional numerical simulations

combined with entropy generation theory and vorticity analysis

flow loss analysis and loss source identification are carried out. The simulation results show that

compared with the average velocity method

the static pressure recovery coefficient at the volute outlet under design conditions is increased by 21.8%

the total pressure loss coefficient is reduced by 31.6%

and the velocity uniformity is increased by 174% when using the angular momentum conservation method. The overall flow field of the volute is improved

with a smaller recirculation zone near the tongue

ensuring the operational stability of downstream components. Two secondary vortex regions with significant flow losses are identified on the hub side and shroud side of the volute. High entropy production rates are observed in the circumferential region of 0–90° within the volute. Based on the volute designed by the angular momentum conservation method

cross-sectional profile optimization is carried out to smooth the flow and suppress the formation of secondary vortices. As a result

both entropy production rate and vorticity inside the volute decrease

the intensity of secondary vortices is reduced

the flow condition in the 0–90° circumferential region is improved

and flow losses are lowered. Compared with the pre-optimization design

under design conditions

the optimized volute shows 13.7% increase in static pressure recovery coefficient

18.1% reduction in total pressure loss coefficient

and nearly unchanged velocity uniformity

indicating enhanced overall performance of the volute. The research results can provide an important reference for the aerodynamic design of volutes and the performance optimization of centrifugal compressors.

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references

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