航空发动机高温升燃烧室技术分析

Analysis of Combustion Technology of High Temperature Rise for Aero Engines

随着先进军用航空发动机推重比要求的不断提高,主燃烧室向更高温升方向发展。本文基于高推重比航空发动机主燃烧室的主要特征与面临的技术挑战,综述了多旋流燃烧、中心分级燃烧、驻涡燃烧和可变几何燃烧等四类高温升燃烧组织的工作原理和发展现状,分析它们的技术优势及挑战。就当前高油气比燃烧室来说,多旋流燃烧与中心分级燃烧是主要发展方向,但随着燃烧室油气比的持续提高,燃烧组织技术将面临更大技术挑战。通过综合分析,作者提出同心圆分区燃烧也可能是一种值得研究的适合更高油气比燃烧室的优选燃烧组织模式。

With the development of thrust-to-weight ratio of advanced military aero engines, the main combustor is developing towards higher temperature rise. Based on the main characteristics and technical challenges of high thrust-to-weight ratio aero engine main combustor, the working principles and development status of four kinds of high temperature rise combustion technologies, including multi-swirl combustion, centrally staged combustion, trapped vortex combustion and variable geometry combustion, have been reviewed in this paper, and their technical advantages and challenges have been analyzed. In terms of the current combustor with high fuel air ratio, multi-swirl combustion and centrally staged combustion are the main development directions. However, with the continuous increase of the fuel air ratio of combustor, the combustion technology will face greater technical challenges. Through comprehensive analysis, the author suggests that concentric circle zoning combustion may also be an optimal combustion organization mode suitable for combustor with higher fuel-air ratio.