|Table of Contents|

Research on thermal protection coating technique of bipropellant thrust chamber(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2018年02期
Page:
76-81
Research Field:
专论与综述
Publishing date:

Info

Title:
Research on thermal protection coating technique of bipropellant thrust chamber
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
Keywords:
Nb-Hf alloy;  silicide coating;  anti-oxidation;  thermal shock
PACS:
V261-34
DOI:
-
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.

References:

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