The development of advanced military aero-engines with high thrust-to-weight ratios requires high-temperature-rise (HTR) technology for core component combustors. This poses a major challenge to multidisciplinary design and optimization of combustors. This paper analyzes the technical characteristics of the HTR combustor and summarizes and proposes three current major technical challenges. For each technical challenge, systematic analysis and comprehensive discussion are conducted from the aspects of technical strategies and research progress. The three technologies reviewed in this paper include (1) combustion configuration technology, (2) liner thermal protection technology involving advanced liner cooling and ceramic matrix composite (CMC) liners, and (3) outlet distribution control technology. We also present our insights regarding current solutions and future research trends related to the three major technical limitations of the HTR combustor.

开发高推重比的先进军用航空发动机需要核心部件燃烧室采用高温升（HTR）技术。这对燃烧器的多学科设计和优化提出了重大挑战。本文分析了高温气冷堆燃烧器的技术特点，总结并提出了当前的三大技术挑战。针对每一个技术挑战，从技术策略和研究进展等方面进行系统分析和全面讨论。本文综述的三项技术包括（1）燃烧配置技术，（2）涉及先进缸套冷却和陶瓷基复合材料（CMC）缸套的缸套热保护技术，以及（3）出口分布控制技术。