液体火箭发动机辐射冷却身部材料研究进展

Recent development of radiation cooling body materials for liquid rocket engines

辐射冷却是上面级和空间液体火箭发动机推力室身部最常用的冷却形式,近年来在部分大推力、高性能二级火箭发动机喷管中也得到了应用。辐射冷却身部材料的耐高温性能和密度,直接影响液体火箭发动机的比冲、推重比和可靠性。通过查阅国内外文献,综述了钛合金、高温合金、难熔金属和碳纤维复合材料等材料在国内外液体火箭发动机辐射冷却身部中研究和应用情况,结合液体火箭发动机推力室身部燃烧室段和喷管段服役工况,对不同材料特点进行了分析。研究对标未来高性能、高可靠和低成本液体火箭发动机的发展需求,并对近年来发展起来的铱/铼/碳-碳复合材料、低密度铌合金和3D打印难熔合金进行了概述。

Radiation cooling is the most commonly used cooling method for the upper stage and space liquid rocket engine thrust chamber body,it has also been applied in several high thrust and high-performance second stage rocket engine nozzle recently.The high temperature resistance and density of radiation cooling body materials directly affect the specific impulse,thrust weight ratio and reliability of liquid rocket engine.By searching domestic and overseas literatures,researches and applications of titanium alloy,superalloy,refractory metal and C fiber composite in radiant cooling body of liquid rocket engines were reviewed.Combined with the working conditions of combustion chamber and nozzle of liquid rocket engines,the characteristics of different materials were analyzed.To study the development needs of high performance,high reliability and low cost liquid rocket engines in the future,an overview of the Ir/Re/C-C composites materials,low density niobium alloy and 3D printing refractory alloy that have gradually developed in recent years was carried out.