Huang Haozhong, Chen Guixin, Long Huigui, Lei Baijun, Liang Jianguo
College of Mechanical Engineering, Guangxi University, Nanning 530004, China.
ACS Omega. 2024 Apr 12;9(16):18674-18685. doi: 10.1021/acsomega.4c02030. eCollection 2024 Apr 23.
Enhancing combustion efficiency and optimizing the thrust-to-weight ratio are critical technical challenges encountered in the development, application, and growth of micro turbojet engines. The high-centrifugal (high-) combustion chamber, as an innovative combustion chamber system, has the capability to replace the primary combustion chamber of the traditional turbojet engine, reducing the length of the combustion chamber while maintaining engine performance. Previous studies on the structure of the high- combustor (HGC) have shown problems such as uneven temperature distribution of the turbojet rotor. To improve the feasibility of HGC integration into micro turbojet engines, this study conducts relevant experiments on a 120 N thrust engine. Subsequently, the results of these experiments were used to analyze the structural design of HGC through a simulation approach. Including six main configurations, the first four structural designs focused on establishing a suitable highly centrifugal environment to stabilize and improve the combustion performance, which was successfully achieved by designing the outer ring gear-shaped inlet with four different angles. Subsequent structural designs were based around improving the uniformity of the temperature distribution at the combustion chamber outlet. The final design of the HGC combustion efficiency is not much different from the original combustion chamber, and it can shorten the axial length of the combustion chamber by nearly 30%. The design of the air inlet holes and the baffle plate effectively improves the temperature uniformity at the outlet of the combustion chamber. Moreover, without changing the combustion chamber material, the corresponding engine weight can be reduced by about 10.7%, and the engine thrust-to-weight ratio can be improved by up to 12% with the same thrust, which provides design ideas for further lightweight applications.
提高燃烧效率和优化推重比是微型涡轮喷气发动机开发、应用和发展过程中面临的关键技术挑战。作为一种创新的燃烧室系统，高离心（高-）燃烧室有能力取代传统涡轮喷气发动机的主燃烧室，在保持发动机性能的同时缩短燃烧室长度。以往对高燃烧室（HGC）结构的研究表明，涡轮喷气转子存在温度分布不均匀等问题。为提高HGC集成到微型涡轮喷气发动机中的可行性，本研究在一台120N推力发动机上进行了相关实验。随后，利用这些实验结果通过模拟方法对HGC的结构设计进行分析。包括六种主要构型，前四种结构设计着重于建立合适的高离心环境以稳定和提高燃烧性能，通过设计四个不同角度的外环齿轮形进气口成功实现了这一点。后续结构设计围绕提高燃烧室出口温度分布的均匀性展开。HGC的最终设计燃烧效率与原燃烧室相差不大，并且可以将燃烧室轴向长度缩短近30%。进气孔和挡板的设计有效提高了燃烧室出口处的温度均匀性。此外，在不改变燃烧室材料的情况下，相应发动机重量可减轻约10.7%，在相同推力下发动机推重比可提高多达12%，为进一步的轻量化应用提供了设计思路。
