火焰筒内参与燃烧空气分布特性数值分析

龚诚; 孔凡夫; 郝颜; 黄序; 何小民

doi:10.7638/kqdlxxb-2023.0173

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火焰筒内参与燃烧空气分布特性数值分析

研究论文 | 更新时间：2026-05-28

- 火焰筒内参与燃烧空气分布特性数值分析
- Numerical analysis of distribution characteristics of air participating in combustion inside combustor liner
- 空气动力学学报 2024年42卷第12期页码：35-43
- 作者机构：
  
  1. 中国空气动力研究与发展中心空天技术研究所,绵阳,621000
  2. 南京航空航天大学能源与动力学院,南京,210016
- 作者简介：
  
  龚诚（1986—），男，湖北宜城人，博士，副研究员，研究方向：航空发动机燃烧室设计. E-mail：gongcheng0903@126.com
  何小民*，男，教授、博士生导师，研究方向：航空航天动力燃烧理论与技术. E-mail：hxm@nuaa.edu.cn
- 基金信息：
  
  中国空气动力研究与发展中心基础和前沿技术研究基金资助项目（PJD20170176）
- DOI：10.7638/kqdlxxb-2023.0173
  中图分类号： V235.1
- 纸质出版：2024
- 稿件说明：
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龚诚, 孔凡夫, 郝颜, 等. 火焰筒内参与燃烧空气分布特性数值分析[J]. 空气动力学学报, 2024, 42(12): 35−43.

GONG Cheng, KONG Fanfu, HAO Yan, et al. Numerical analysis of distribution characteristics of air participating in combustion inside combustor liner[J]. 2024, 42(12): 35-43.
龚诚, 孔凡夫, 郝颜, 等. 火焰筒内参与燃烧空气分布特性数值分析[J]. 空气动力学学报, 2024, 42(12): 35−43. DOI： 10.7638/kqdlxxb-2023.0173

GONG Cheng, KONG Fanfu, HAO Yan, et al. Numerical analysis of distribution characteristics of air participating in combustion inside combustor liner[J]. 2024, 42(12): 35-43. DOI： 10.7638/kqdlxxb-2023.0173.

摘要

航空发动机燃烧室火焰筒内不同气流中参与燃烧化学反应的空气（简称为“燃烧空气”）占比在燃烧室设计中具有重要影响。目前该比例参数仅来源于经验，缺乏有效的评估手段。针对新型航空发动机燃烧组织技术和设计方法的发展需求，推导了火焰筒内不同空气流对应的混合分数和氧气质量分数的时空输运方程，并耦合基于火焰面生成流形（flamelet generated manifold

FGM）模型的航空发动机燃烧室雾化燃烧大涡模拟计算程序，建立了一种针对火焰筒内不同空气流中参与燃烧空气占比的定量评估分析方法，实现了对火焰筒内参与燃烧空气的溯源分析。选取某典型旋流燃烧室对上述方法进行了演示验证，结果表明：该方法能够对火焰筒内不同流束空气混合分数和氧气质量分数进行有效追踪。通过对仿真结果的统计，获得了火焰筒不同空气流的质量流量和参与燃烧的空气占比等参数。分析表明，当前燃烧室内参与燃烧空气的分布特性与经典旋流燃烧室设计理论一致，验证了当前评估方法的合理性。

Abstract

The distribution of air within the combustor liner that participates in combustion reactions is pivotal for the design of gas turbine combustors. To address this

a novel Computational Fluid Dynamics (CFD)-based methodology has been developed to quantitatively assess the distribution of air that is consumed by combustion. This approach involves the derivation of spatial and temporal transport equations for the air mixture fraction and the oxygen mass fraction across each air stream within the combustor liner. These equations are then integrated with an LES-FGM solver

specifically tailored for the simulation of turbulent spray combustion within gas turbine combustors. By analyzing the simulation outcomes

both the airflow rate and the proportion of air involved in combustion for each stream can be determined. The method was validated using a conventional swirling combustor

demonstrating its ability to effectively monitor the air mixture fraction and oxygen mass fraction within individual air streams. The method also provided the proportion of air consumed by combustion in each stream and its spatial distribution. The combustion air distribution derived from these simulations aligns with the established design principles of conventional swirling combustors

confirming the effectiveness of this approach for evaluating gas turbine combustors.

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