基于燃烧室压力振荡的火焰筒结构优化

秦皓; 付镇柏; 林宇震; 李继保

doi:10.13224/j.cnki.jasp.2015.05.007

基于燃烧室压力振荡的火焰筒结构优化

doi: 10.13224/j.cnki.jasp.2015.05.007

1. 北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室, 北京 100191;
2. 中国航空工业集团公司商用航空发动机有限责任公司, 上海 200241

详细信息

作者简介:
秦皓(1988-),男,湖南汨罗人,博士生,主要从事民用航空发动机燃烧不稳定性研究.

中图分类号: V231.2
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- 被引次数: 0
出版历程
- 收稿日期: 2013-11-30
- 刊出日期: 2015-05-28

Liner structure optimization based on pressure oscillation in combustor

1. National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics of Astronautics, Beijing 100191, China;
2. Commercial Aircraft Engine Company Limited, Aviation Industry Corporation of China, Shanghai 200241, China

摘要

摘要: 实验对比了双层与单层火焰筒的燃烧室压力振荡特性.实验结果表明:在相同的实验工况下,前者的压力振荡幅值要小.检验了基于叠加原理的多孔共振腔模型在分析上述压力振荡特性中的适用性.通过敏感性分析,探讨了在保证火焰筒冷却气分配不变的情况下,用于减小燃烧室压力振荡幅值的火焰筒结构改良方向.分析结果表明:火焰筒壁面的孔数量(孔直径)是用于减小燃烧室压力振荡工程优化的主要参数.
- 压力振荡 /
- 火焰筒结构 /
- 多孔共振腔 /
- 叠加原理 /
- 低排放燃烧室设计
Abstract: Pressure oscillation characteristics of combustor were tested and compared between double-plate liner and single liner, and the test results show that pressure oscillation amplitude of the former is minor under the same test conditions. Applicability of perforated resonators model based on superposition principle in analyzing pressure oscillation characteristics mentioned above was checked. After sensitivity analysis, liner structure improvements for decreasing pressure oscillation amplitude of combustor without changing cooling air allocation were investigated. Analysis results show that the hole number (or hole diameter) in linear wall is the key parameter in mitigating pressure oscillation in combustor in an engineering optimization way.
- pressure oscillation /
- liner structure /
- perforated resonator /
- superposition principle /
- low emissions combustor design

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参考文献(18)

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