耦合热声网络与激励盘模型预测燃烧室的不稳定振荡

邵卫东 1; 2; 高贤智 1

doi:10.7652/xjtuxb202103021

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耦合热声网络与激励盘模型预测燃烧室的不稳定振荡

更新时间：2025-07-09

- 耦合热声网络与激励盘模型预测燃烧室的不稳定振荡
- Prediction of Instable Oscillation in Combustion Chamber Using Thermal-Acoustic Network Coupled with Actuator Disk Model
- 西安交通大学学报 2021年55卷第3期页码：186-194
- 作者机构：
  
  1. 中国航发商用航空发动机有限责任公司,上海,200241
  2. 上海市航空发动机数字孪生重点实验室,上海,200241
- 作者简介：
- 基金信息：
  
  : 2020-08-28。作者简介: 邵卫东(1989—),男,博士,工程师。基金项目: 上海市青年科技英才扬帆计划资助项目(20YF1454200)
- DOI：10.7652/xjtuxb202103021
  中图分类号： V235.13
- 网络首发：2021-03-10，
  
  纸质出版：2021
- 稿件说明：
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邵卫东 1, 2, 高贤智 1. 耦合热声网络与激励盘模型预测燃烧室的不稳定振荡[J]. 西安交通大学学报, 2021,55(3):186-194.

Prediction of Instable Oscillation in Combustion Chamber Using Thermal-Acoustic Network Coupled with Actuator Disk Model[J]. 2021, 55(3): 186-194.
邵卫东 1, 2, 高贤智 1. 耦合热声网络与激励盘模型预测燃烧室的不稳定振荡[J]. 西安交通大学学报, 2021,55(3):186-194. DOI： 10.7652/xjtuxb202103021.

Prediction of Instable Oscillation in Combustion Chamber Using Thermal-Acoustic Network Coupled with Actuator Disk Model[J]. 2021, 55(3): 186-194. DOI： 10.7652/xjtuxb202103021.

摘要

为解决燃烧室出口阻抗边界条件不定问题

提出了一种跨部件热声耦合计算方法:在燃烧室内采用热声网络低阶模型求解热声振荡过程

在涡轮内采用激励盘模型求解熵波、涡波与声波传播过程

在部件交界面上采用声阻抗作为过渡变量

通过部件内迭代与跨部件的外迭代策略获得系统解。耦合计算模型映射了熵波、涡波和声波在燃烧室与涡轮间传播的物理过程

清晰地描述了以燃烧室与涡轮的结构与气动参数为隐变量的等效声阻抗函数。经过算例测试与试验对比验证

结果表明:激励盘模型能够精确评估涡轮前的等效声阻抗; 相对于非耦合计算方法

耦合计算方法能够准确判定热声振荡过程的发生、精确计算振荡频率与燃烧室声模态分布。本文的研究结果可为向高阶模型的耦合计算推广奠定理论基础。

Abstract

To overcome the uncertain impedance boundary condition at the combustor exit

a coupling method of thermo-acoustic computation between combustion chamber and turbine is presented. Firstly

the thermo-acoustic network is used to solve the oscillatory behavior in the combustion chamber. Secondly

the actuator disk model is used to solve the propagation of entropy

vorticity and acoustic waves. Finally

inner and outer iterations are conducted to obtain the solution with the equivalent impedance at the interface between combustion chamber and turbine. The coupling method reflects the motion of entropy

vorticity and acoustic waves in both the combustor and turbine. The equivalent acoustic impedance

which is the implicit function of some geometrical and aerodynamic parameters of both the combustor and turbine

is clearly illustrated. Through verification with benchmark models and validation with experiment

the results show that the actuator disk model could accurately measure the equivalent acoustic impedance at the inlet of turbine. Moreover

the coupling strategy can judge about the occurrence of combustion instability

and accurately capture the oscillatory frequency and modes compared with decoupled strategy. The present result provides the theoretical basis for the extension of coupling strategy to high-order models.

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references

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