燃烧室涡轮交互作用尺度自适应模拟

江立军; 曹俊; 陶焰明; 熊清勇; 肖为

doi:10.13224/j.cnki.jasp.20200493

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燃烧室涡轮交互作用尺度自适应模拟

燃烧、传热、传质 | 更新时间：2025-04-07

- 燃烧室涡轮交互作用尺度自适应模拟
- Combustor turbine interaction based on scale adaptive simulation
- 航空动力学报 2021年36卷第10期页码：2186-2196
- 作者机构：
  
  中国航空发动机集团有限公司湖南动力机械研究所，湖南株洲 412002
- 作者简介：
  
  江立军（1982-），男，研究员，博士，主要从事中小型航空发动机设计及仿真。
- 基金信息：
  
  中国航发自主创新专项资金(ZZCX⁃2017⁃018);国家科技重大专项（2017⁃Ⅰ⁃0001⁃0001）
- DOI：10.13224/j.cnki.jasp.20200493
  中图分类号：
- 稿件说明：
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江立军, 曹俊, 陶焰明, 等. 燃烧室涡轮交互作用尺度自适应模拟[J]. 航空动力学报, 2021,36(10):2186-2196.

Lijun JIANG, Jun CAO, Yanming TAO, et al. Combustor turbine interaction based on scale adaptive simulation[J]. Journal of Aerospace Power, 2021, 36(10): 2186-2196.
江立军, 曹俊, 陶焰明, 等. 燃烧室涡轮交互作用尺度自适应模拟[J]. 航空动力学报, 2021,36(10):2186-2196. DOI： 10.13224/j.cnki.jasp.20200493.

Lijun JIANG, Jun CAO, Yanming TAO, et al. Combustor turbine interaction based on scale adaptive simulation[J]. Journal of Aerospace Power, 2021, 36(10): 2186-2196. DOI： 10.13224/j.cnki.jasp.20200493.

摘要

为了揭示燃烧室涡轮交互作用机理，采用尺度自适应模拟方法对某航空发动机燃烧室和燃气涡轮开展了跨部件联合数值模拟研究，分析了燃气涡轮导叶对燃烧室内部流场和温度场的影响、燃烧室出口速度分布和热斑对涡轮气动和传热的影响。结果表明：尺度自适应模拟方法在预测燃烧室和燃气涡轮部件性能方面具有较高精度，并能有效捕捉燃烧室及涡轮流道中的复杂涡系结构。同时，涡轮对燃烧室内部速度场的影响一直可以回溯至导叶上游0.3倍弦长的距离，燃烧室出口速度分布对涡轮内部流动、热斑对燃气涡轮导叶及动叶绝热壁温均有较大影响。

Abstract

In order to study the mechanisms of combustor turbine interactions，integrated simulation of a realistic aero engine configuration，including combustor and turbine，was conducted by using scale adaptive simulation method.The impacts of the turbine nozzle guide vane on flow and temperature fields inside the combustor together with the effect of the velocity profile in the outlet of combustor and hot⁃streaks on turbine thermodynamics characteristics were both analyzed by the integrated simulation.The results demonstrated that the scale adaptive simulation method obtained a fine prediction on combustor and turbine performances and the complicated vortex structures were well resolved.Moreover，the velocity field inside combustor was distinctly influenced by the nozzle guide vane up to a distance of 0.3 axial chord length in front of the stator's leading edge，and the impacts of velocity profile in the outlet of combustor and hot⁃streaks on the turbine aerodynamics and heat transfer were quite significant.

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references

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