Throughflow Calculation and Model Optimization Method for Transonic Axial-Flow Compressors

ZHANG Chao; ZHANG Xiawen; XU Yanbo; LI Zhen; JU Yaping; ZHANG Chuhua

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Throughflow Calculation and Model Optimization Method for Transonic Axial-Flow Compressors

更新时间：2026-09-29

- Throughflow Calculation and Model Optimization Method for Transonic Axial-Flow Compressors
- JOURNAL OF XI’AN JIAOTONG UNIVERSITY (2026)
- 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：
- DOI：
  CLC： TH453
- Received：23 June 2026，
  
  Revised：2026-08-28，
  
  Accepted：11 September 2026，
- 稿件说明：
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ZHANG Chao, ZHANG Xiawen, XU Yanbo, et al. Throughflow Calculation and Model Optimization Method for Transonic Axial-Flow Compressors[J/OL]. JOURNAL OF XI’AN JIAOTONG UNIVERSITY,2026-09-29. http://zkxb.xjtu.edu.cn/en/article/172884361/.
DOI：

ZHANG Chao, ZHANG Xiawen, XU Yanbo, et al. Throughflow Calculation and Model Optimization Method for Transonic Axial-Flow Compressors[J/OL]. JOURNAL OF XI’AN JIAOTONG UNIVERSITY,2026-09-29. http://zkxb.xjtu.edu.cn/en/article/172884361/. DOI：

摘要

针对跨声速轴流压气机气动分析设计中落后角与损失经验模型精度低、适用范围窄等问题，发展了跨声速轴流压气机通流特性计算方法，并提出了一种基于多转速特性曲线实验数据的经验模型优化校准方法。利用典型跨声速压气机级的多转速特性曲线的实测数据，对经验模型组合中的15个经验参数进行了优化校准，并在多台跨声速轴流压气机/风扇上进行了通用性验证。研究结果表明：基于落后角和损失系数实测数据的多转速通流计算相对误差小于1%；相较于传统经验模型组合高达6%的通流计算误差，优化后的经验模型可将压气机级多转速通流特性计算误差降低1%~4%；在两级跨声速风扇与三级跨声速压气机验证算例中，设计转速通流特性计算相对误差均降低至1%以内。该研究工作可为多级跨声速轴流压气机分析设计和模型开发提供有参考价值的通流计算方法和经验模型。

Abstract

To address the issues of low accuracy and limited applicability of existing deviation angle and loss empirical models in the aerodynamic analysis and design of transonic axial compressors

this paper develops a throughflow performance calculation method for transonic axial compressors and proposes an empirical model optimization and calibration method based on experimental multi-speed characteristic curve data. Using measured multi-speed characteristic data from typical transonic compressor stages

15 empirical parameters in the model combination are optimized and calibrated

and the generality of the optimized model is validated on multiple transonic axial compressors/fans. The results show that the relative error of multi-speed throughflow calculations based on measured deviation angles and loss coefficients is less than 1%. Compared with the up to 6% calculation error of conventional empirical model combinations

the optimized empirical model reduces the multi-speed throughflow calculation error for compressor stages by 1%–4%. In the validation cases of a two-stage transonic fan and a three-stage transonic compressor

the relative errors of throughflow calculations at the design rotational speed are all reduced to within 1%. This work provides valuable throughflow calculation methods and empirical models for the analysis

design

and model development of multi-stage transonic axial compressors.

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references

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