三维内转进气道凭借其结构紧凑、压缩效率高、流量捕获能力强、总压恢复系数高以及便于一体化等优势，已逐渐成为吸气式高超声速飞行器进气道设计的发展趋势。自概念提出以来，一直吸引着国内外众多学者与研究机构的广泛关注。首先，围绕三维内转进气道设计状态下的气动设计与性能优化，以激波为主线综述了激波解析理论、基本流场构建以及内转进气道设计三个方面的进展。随后，从低马赫数起动特性和抗反压特性两个角度分别梳理了改善三维内转进气道非设计性能方面的研究。接着，对三维内转进气道在TBCC组合动力系统中的应用现状进行介绍。最后，在对国内外研究现状分析总结的基础上，指出了三维内转进气道的四个未来核心研究方向。

The hypersonic three-dimensional inward-turning inlet has gradually become the preferred design for air-breathing vehicles due to its advantages of compact structure, high compression efficiency, high flow capture capability, high total pressure recovery coefficient, and ease of integration. Since the introduction of the inward-turning inlet concept, it has attracted extensive attention from scholars and research institutions worldwide. Firstly, focusing on the inward-turning inlet’s aerodynamic design and optimization, the recent advancements in shock wave analytic theory, basic flowfield construction, and inward-turning inlet design are summarized. Subsequently, the research on improving the inward-turning inlet’s performances under off-design conditions is introduced from the perspectives of low Mach number starting and anti-backpressure characteristics. The current application of the inward-turning inlet in TBCC combined propulsion systems is then discussed in detail. Finally, based on the analysis and summary of the current research status at home and abroad, four key future research spots of the three-dimensional inward-turning inlet are pointed out.