基于正反问题耦合的压气机特性快速预测方法

宋召运; 王宝潼; 范腾博; 郑新前; 冯旭栋

doi:10.13224/j.cnki.jasp.20210072

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基于正反问题耦合的压气机特性快速预测方法

叶轮机械 | 更新时间：2025-04-07

- 基于正反问题耦合的压气机特性快速预测方法
- Rapid prediction method of compressor characteristics with coupling direct and inverse problems
- 航空动力学报 2022年37卷第3期页码：619-628
- 作者机构：
  
  1.清华大学航空发动机研究院，北京 100084
  2.清华大学汽车安全与节能国家重点实验室，北京 100084
  3.中国航空发动机集团有限公司四川燃气涡轮研究院，四川绵阳 621000
- 作者简介：
  
  宋召运（1990-），男，助理研究员，博士，研究方向为压气机气动热力学。
  郑新前（1977-），男，教授、博士生导师，博士，研究方向为航空发动机气动热力学。E⁃mail：zhengxq@tsinghua.edu.cn
- 基金信息：
  
  国家科技重大专项（2017⁃Ⅱ⁃0004⁃0016）
- DOI：10.13224/j.cnki.jasp.20210072
  中图分类号：
- 稿件说明：
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宋召运, 王宝潼, 范腾博, 等. 基于正反问题耦合的压气机特性快速预测方法[J]. 航空动力学报, 2022,37(3):619-628.

Zhaoyun SONG, Baotong WANG, Tengbo FAN, et al. Rapid prediction method of compressor characteristics with coupling direct and inverse problems[J]. Journal of Aerospace Power, 2022, 37(3): 619-628.
宋召运, 王宝潼, 范腾博, 等. 基于正反问题耦合的压气机特性快速预测方法[J]. 航空动力学报, 2022,37(3):619-628. DOI： 10.13224/j.cnki.jasp.20210072.

Zhaoyun SONG, Baotong WANG, Tengbo FAN, et al. Rapid prediction method of compressor characteristics with coupling direct and inverse problems[J]. Journal of Aerospace Power, 2022, 37(3): 619-628. DOI： 10.13224/j.cnki.jasp.20210072.

摘要

提出一种基于正反问题耦合的压气机特性快速预测方法，根据压气机一维设计理论，通过对满足流量及压比设计指标的反问题求解快速得出压气机的气动布局方案，在此基础上结合非设计点损失和落后角模型通过正问题求解得出全工况压气机特性，再根据预测特性与目标的偏差调整气动布局方案，以此通过对正反问题的耦合求解实现对压气机特性的合理快速预测。为了提高压气机特性预测精度，发展了基于遗传算法的压气机损失和落后角模型参数优化校准方法，该方法利用优化理论及实验数据对传统的压气机损失和落后角模型进行改进。利用三台压气机的实验结果对模型进行了校准与验证，验证结果表明：设计点效率预测误差为0.23%，非设计点为1.34%，满足发动机需求分析及概念设计阶段对压气机效率的预测精度要求。

Abstract

A rapid method of compressor characteristics prediction with coupling inverse design and direct problems was proposed.According to one⁃dimensional meanline design theory of the compressor，the aerodynamics layout of the compressor was quickly obtained by solving the inverse problem to satisfy the design targets such as mass flow rate and pressure ratio.Then，by adopting the models of loss and deviation angle at off⁃design conditions，the compressor characteristics of the whole working condition were obtained by solving the direct problem.The aerodynamics layout was adjusted according to the deviation angle between the predicted characteristics and the targets，and the reasonable and rapid prediction of the compressor characteristics was realized through the coupling of inverse and direct problems.Moreover，a parameter calibration method of compressor loss and deviation angle model based on genetic algorithm was created.This method used optimization theory and experiment data of compressors to improve the traditional models of loss and deviation angle for enhancing the prediction accuracy of compressor characteristics.Experimental data of three compressors were used for calibration and validation of the proposal method.The results showed that the efficiency prediction errors at design and off⁃design conditions were 0.23% and 1.34%，which satisfied the requirement in the stage of requirement analysis and concept design for aero⁃engine.

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references

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