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飛機(jī)APU渦輪導(dǎo)向葉片高溫防護(hù)涂層失效模式分析
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作者單位:

1.沈陽工業(yè)大學(xué)，遼寧 沈陽 110870;2.中國南方航空公司，遼寧 沈陽 110169;3.中國民航大學(xué) 天津市民用航空器適航與維修重點(diǎn)實(shí)驗(yàn)室，天津 300300

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基金項(xiàng)目:

Scientific Research Project of Tianjin Municipal Education Commission (2020KJ016); Central University Basic Scientific Research Operation Cost Special Fund of Civil Aviation University of China (3122020065)


Failure Modes of High Temperature Protective Coating for Aircraft APU Turbine Guide Vanes
Author:
Affiliation:

1.Shenyang University of Technology, Shenyang 110870, China;2.China Southern Airlines, Shenyang 110169, China;3.Tianjin Key Laboratory of Civil Aircraft Airworthiness and Maintenance, Civil Aviation University of China, Tianjin 300300, China

Fund Project:

Scientific Research Project of Tianjin Municipal Education Commission (2020KJ016); Opening Fund of Tianjin Provincial and Ministerial Scientific Research Institution (TKLAM202202)

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    摘要:

    利用掃描電鏡（SEM）、能譜分析儀（EDS）等分析了國內(nèi)某型在役APU渦輪導(dǎo)向葉片的結(jié)構(gòu)特征與熱防護(hù)機(jī)理，研究了葉片失效件中高溫防護(hù)涂層的厚度變化與失效模式。結(jié)果表明：飛機(jī)APU導(dǎo)向葉片中存在滲鋁涂層+MCrAlY涂層與單一滲鋁涂層2種不同的涂層結(jié)構(gòu)；APU導(dǎo)向葉片失效件的MCrAlY涂層厚度從葉片尾緣—葉盆—前緣區(qū)域呈先增大后減小的趨勢；受葉片構(gòu)型影響，葉片尾緣區(qū)域涂層的氧化程度較嚴(yán)重，而葉盆區(qū)域越靠近前緣的位置涂層氧化損傷程度越低，但葉片前緣區(qū)域由于受CMAS腐蝕與高溫氧化的耦合作用使得該區(qū)域涂層損傷最為嚴(yán)重。

    Abstract:

    The structural characteristics and thermal protection mechanism of a certain type of auxiliary power unit (APU) turbine guide vane in service were analyzed by scanning electron microscope (SEM) and energy dispersive analyzer (EDS). Then, the thickness variation and failure mode of the high temperature protective coating after removal from aircraft were investigated. The results show that there are two different coating structures in the aircraft APU guide vanes: aluminized coating+MCrAlY coating and mono aluminized coating. The MCrAlY coating thickness of the scrapped APU guide vane components increases first and then decreases from the area of trailing edge to the pressure side and then to the leading edge. Affected by the configuration and the service environment of APU guide vanes, the coatings at the trailing edge and pressure side present an oxidation-predominant damage mode. The oxidation degree of the coating on the trailing edge is more serious, while the closer the pressure-side region to the leading edge, the less severe the oxidative damage. However, due to the coupling effect of CMAS (CaO, MgO, Al2O3, SiO2) corrosion and high temperature oxidation, the damage to the coating at the leading edge of vanes is the most serious.

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引用本文

王璐璐,劉延寬,費(fèi)宇杰,王源生,戰(zhàn)金瀅,王志平.飛機(jī)APU渦輪導(dǎo)向葉片高溫防護(hù)涂層失效模式分析[J].稀有金屬材料與工程,2023,52(2):470~477.[Wang Lulu, Liu Yankuan, Fei Yujie, Wang Yuansheng, Zhan Jinying, Wang Zhiping. Failure Modes of High Temperature Protective Coating for Aircraft APU Turbine Guide Vanes[J]. Rare Metal Materials and Engineering,2023,52(2):470~477.]
DOI：10.12442/j. issn.1002-185X.20220391

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  • 收稿日期:2022-05-06
  • 最后修改日期:2023-02-03
  • 錄用日期:2022-08-11
  • 在線發(fā)布日期: 2023-03-03
  • 出版日期: 2023-02-28