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[1]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(02):76-81.
　WANG Kun,WANG Guoqiang.Research on thermal protection coating technique of bipropellant thrust chamber[J].Journal of Rocket Propulsion,2018,44(02):76-81.
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双组元推力室热防护涂层工艺技术研究

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 44 期数: 2018年02期 页码: 76-81 栏目: 专论与综述 出版日期: 2018-04-30
Title:
Research on thermal protection coating technique of bipropellant thrust chamber
文章编号:
1672-9374(2018)02-0076-06
作者:
王 堃1; 王国强2
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
Author(s):
WANG Kun1;  WANG Guoqiang2
1. Xi'an Bureau, Naval Equipment Department of China, Xi'an 710065, China;2. Xi'an Space Engine Company Limited, Xi'an 710100, China
关键词:
铌铪合金;  硅化物涂层;  抗氧化;  热震
Keywords:
Nb-Hf alloy;  silicide coating;  anti-oxidation;  thermal shock
分类号:
V261-34
文献标志码:
A
摘要:
针对双组元姿轨控发动机推力室铌铪合金材料的高温抗氧化防护进行了涂层工艺技术研究,在合金表面制备了Si-Cr-Ti体系硅化物涂层,通过真空烧结、高温抗氧化和热震试验、显微组织分析,对涂层的成型过程、形貌、组织结构、性能和防护机理进行了分析。结果表明,通过真空烧结形成了过渡/结合层、致密层和疏松层结构的硅化物涂层,过渡层分布均匀,致密层厚实,疏松层相对较薄且成型较好,经过两代工艺优化,涂层在1 700 ℃下的氧化寿命达到7 h,1 400～8 00 ℃空冷热震循环寿命达到4 500次,在热试车考核过程中涂层最高工作温度可达到1 350 ℃,试后涂层依然具有一定厚度的致密层,具有高温防护作用,满足型号对涂层性能的要求。
Abstract:
The coating technology for protecting the Nb-Hf alloy bipropellant thrust chamber of attitude 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 results 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 operating 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.

参考文献/References:

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相似文献/References:

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　PAN Zhaoyi,CAI Gang,SONG Guoxin.Research on thermal protection coatings on body surface of Nb-Hf alloy thrust chamber[J].Journal of Rocket Propulsion,2016,42(02):68.
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[3]潘兆义,赵青芮,王国强,等.铌铪合金表面硅化物涂层的高温失效行为分析[J].火箭推进,2019,45(02):66.
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备注/Memo

收稿日期:2017-07-20
作者简介: 王堃(1983— ),男,工程师,研究领域为液体火箭发动机特种加工技术

更新日期/Last Update: 1900-01-01