火箭推进2018，Vol.44Issue(2)：76-81,6.
双组元推力室热防护涂层工艺技术研究
Research on thermal protection coating technique of bipropellant thrust chamber
王堃 1王国强2
作者信息
- 1. 海装西安局,陕西西安710065
- 2. 西安航天发动机有限公司,陕西西安710100
- 折叠
摘要
Abstract
The coating technology for protecting the Nb-Hf alloy bipropellant thrust chamber of atti-tude and orbital control engine from high-temperature oxidation is studied in this paper.The Si-Cr-Ti system silicide coating was prepared on the surface of Nb-Hf alloy.The forming process,morphology, structure,properties and protective mechanism of the coating were analyzed by vacuum sintering,high-temperature anti-oxidation experiment, thermal shock experiment and microstructure analysis.The re-sults show that the silicide coating formed by vacuum sinitering consists of transition/bonding layer,dense layer and loose layer; the distribution of transistion layer is uniform, the dense layer is thick and the loose layer is relatively thin but has a good morphology.With two generation of process optimization,the oxidation life of the coating reaches up to 7 h at 1 700 ℃and the air-cooling and thermal shock cycle life reaches to 4 000 times at 1 400~800℃.During the hot test assessment process,the maximum oper-ating temperature of the coating reached 1 350℃.After the test,the coating still has a certain thickness dense layer.The test result indicates that the silicide coating can provide high-temperature protection and meet the coating performance requirements.关键词
铌铪合金/硅化物涂层/抗氧化/热震Key words
Nb-Hf alloy/silicide coating/anti-oxidation/thermal shock分类
航空航天引用本文复制引用
王堃,王国强..双组元推力室热防护涂层工艺技术研究[J].火箭推进,2018,44(2):76-81,6.
