航空发动机燃烧室光学可视模型试验件及其流场测量研究进展

Development of optically accessible gas turbine model combustor and its flow field testing

航空发动机燃烧室内的燃烧组织是高温高压受限空间内多级旋流复杂流场结构的气动、燃油雾化、蒸发、油气混合和燃烧化学反应多场耦合过程,而其流场特性影响雾化和燃烧过程,从而对燃烧室的燃烧性能具有决定性影响。对燃烧室内复杂强旋流流场组织机理的认识和高精度测试一直是发动机燃烧室研制过程中的难点之一。本文针对光学可视模型燃烧室试验件设计方法及典型发动机燃烧室的流场组织机理和特性进行总结,希望给发动机燃烧室研制过程中光学模型燃烧室试验件的设计提供一定的借鉴,深刻认识目前两类典型的传统旋流杯模型燃烧室和基于分区分级耦合燃烧技术的新型燃烧室的流场特性,促进航空发动机燃烧室的研制。

The combustion in the chamber of aero-engine involving the aerodynamics of swirling air streams,fuel atomization,evaporation,the mixing of fuel droplets with air streams,and chemical reactions is a multiphase complex process under the conditions of high pressure and high temperature.The characteristics of the flow field play a significant role in determining combustion performances of the combustors by affecting the processes of fuel atomization and combustion.The interpretations off low mechanism and accurate tests of the highly swirling flows inside the combustors are always being one of the major challenges posed to the combustion researchers and engineers.In order to learn the knowledge of experimental setups of optically accessible gas turbine combustor facilities,and to have a grasp of swirling flow characteristics in swirl-cup traditional combustors and staged combustors combining premixed and diffusion combustion technologies,the design methods of the optically accessible model combustor,the organization mechanism of swirling flow,and the flow structures in typical combustors of aero-engines are analyzed and summarized in this study.The discussions in this paper may facilitate the research and development of aero-engine combustors.