文章信息/Info

Title:

Study on Failure Mechanism of MoSi2 Coating Under High-Temperature Oxygen-Enriched Flame Erosion

文章編號(hào):

1674-3962(2024)04-0355-11

作者:

羅靖川; 朱昌發(fā); 劉坤; 王鉞淞; 徐向毅; 楊冠軍; 陳林

1．西安交通大學(xué) 金屬材料強(qiáng)度國(guó)家重點(diǎn)實(shí)驗(yàn)室，陜西 西安 710049 2．中國(guó)航天西安航天發(fā)動(dòng)機(jī)有限公司，陜西 西安 710065 3．火箭軍裝備部駐西安地區(qū)第二軍事代表室，陜西 西安 710065 4．空軍裝備部駐西安地區(qū)軍事代表局第八軍事代表室，陜西 西安 710065

Author(s):

LUO Jingchuan;  ZHU Changfa;  LIU Kun;  WANG Yuesong; XU Xiangyi;  YANG Guanjun;  CHEN Lin

1. State Key Laboratory for Mechanical Behavior of Materials, Xi’an Jiaotong University, Xi’an 710049, China 2. Xi’an Aero Engine Corporation in CASC, Xi’an 710065, China 3. The Second Military Representative of Equipment Department of the PLA Rocket Force Office in Xi’an, Xi’an 710065, China 4. The 8th Military Representative of Equipment Department of the Air Force Office in Xi’an, Xi’an 710065, China

關(guān)鍵詞:

MoSi2涂層; 氧化膜; 晶界; 縱向裂紋; 剝落

Keywords:

MoSi2 coating;  oxide film;  grain boundary;  vertical cracks;  transverse spallation

分類號(hào):

TG174.4

DOI:

10.7502/j.issn.1674-3962.202204023

文獻(xiàn)標(biāo)志碼:

A

摘要:

MoSi2高溫氧化時(shí)表面可生成保護(hù)性SiO2，有望用于推力室噴管內(nèi)表面抗高溫氧化涂層材料。然而，在1800 ℃及以上超高溫火焰沖刷考核條件下，MoSi2涂層發(fā)生快速損傷失效。為揭示MoSi2涂層超高溫沖刷失效機(jī)理，系統(tǒng)研究了推力室噴管不同位置涂層的氧化行為和損傷規(guī)律。結(jié)果表明：涂層損傷分為5個(gè)特征區(qū)域，分別為前緣、喉部、過(guò)渡段、中部和尾部，其中喉部發(fā)生整個(gè)涂層剝落，尾部涂層仍保持完整。MoSi2涂層的主要失效形式為：超高溫下MoSi2涂層晶界快速氧化和氧化膜快速揮發(fā)，產(chǎn)生晶界裂紋，晶界裂紋合并形成網(wǎng)狀、貫穿性、大尺度的縱向裂紋，將MoSi2涂層分割成島狀區(qū)域。在熱沖擊載荷作用下，島狀區(qū)域MoSi2涂層發(fā)生剝落失效。指出了MoSi2涂層超高溫沖刷腐蝕機(jī)理，為發(fā)展推力室噴管用長(zhǎng)壽命MoSi2超高溫抗氧化涂層提供了理論方向。

Abstract:

MoSi2 can generate protective SiO2 on the surface during high temperature oxidation, which is expected to be used as a high-temperature oxidation�瞨esistant coating on the inner surface of the thrust chamber nozzle. However, the MoSi2 coatings failed under the flame erosion at temperatures≥1800 ℃. In order to reveal the failure mechanism of MoSi2 coatings, the oxidation behavior of coating at various locations of the thrust chamber nozzle specimen after the flame erosion was clarified. The results show that the coating can be divided into five characteristic regions, namely the leading edge, the throat, the transition section, the middle and the tail. Among them, the entire coating peels off at the throat, and the coating remains intact at the tail. The main failure mode of the MoSi2 coatings is: rapid oxidation and corrosion at the grain boundaries (GB) of the MoSi2 coatings result in the formation of penetrating GB cracks, the coalescence of penetrating GB cracks causes the connected and large�瞫cale vertical cracks, dividing the coatings into island�瞫haped regions. Under the action of thermal shock, island�瞫haped coatings peel off. This research analyzes the erosion behavior of MoSi2 coating, and provides the reference for the development of long-life ultra-high temperature anti-oxidation MoSi2 coatings for thrust chamber nozzles.