摘要
铌铪合金具有较高的高温强度，是轨姿控液体火箭发动机推力室身部的主要结构材料，但在工作环境中易发生氧化“粉化”，必须在合金表面涂覆高温抗氧化涂层。本文主要研究了硅化物涂层对铌铪合金热防护行为，包括涂层的成型过程、高温抗氧化行为及高温抗热震行为等。试验结果为：涂层在1700℃下的氧化寿命7h，1400～800℃的空冷热震循环次数4700次，表面粗糙度30-60μm。并对铌铪合金推力室身部涂层热试车情况进行了详细分析研究，对涂层在富氧高温燃气冲刷作用下的工作机理进行研究分析，总结了硅化物涂层的热防护机理，研究的新型硅化物涂层在高温条件下具有较好的性能。
The Nb-Hf alloy possesses high elevated temperature strength and is an important structure material for body of the rocket engine thrust chamber. The Nb-Hf alloy is easily oxidized and chalked in the oxidizing environment, so the anti-oxidation coatings must be used to overcome this problem. In this paper, the silicide coating thermal protection towards the Nb-Hf alloy are studied, including the formation of silicide coating, the oxidation resistance, the thermal shock resistance and anti-ablation. Thetest results indicate thatoxidation lifetime of Nb-Hf alloys is 7 h at 1 700 ~C, the times of air cold-thermal shocking cycles are 4 700 at 800 ~ 1 400 ~C, and the surface roughness is 30-60 la m. The thermal test status of the coating on the body of Nb-Hf alloy thrust chamber is analyzed and researched in detail. The dynamic properties and thermal protection mechanism of silieide coating at high temperature are studied. The designed silicide coating has good performance under the condition ofhida temnerature.
出处
《火箭推进》
CAS
2016年第4期68-73,共6页
Journal of Rocket Propulsion
基金
中国航天科技集团公司重大工艺专项资助项目(ZDGY2013-25)
关键词
铌铪合金
硅化物涂层
热防护
机理分析
Nb-Hf alloy
silicide coating
thermal protection
mechanism analysis
作者简介
潘兆义（1984-），男，博士，研究领域为热防护涂层设计与研发
