[1]馮強,童錦艷,鄭運榮,等.燃氣渦輪葉片的服役損傷與修復[J].中國材料進展,2012,(12):021-30.[doi:10.7502/j.issn.1674-3962.2012.12.03]
FENG Qiang,TONG Jinyan,ZHENG Yunrong,et al.Service Induced Degradation and Rejuvenation of Gas Turbine Blades[J].MATERIALS CHINA,2012,(12):021-30.[doi:10.7502/j.issn.1674-3962.2012.12.03]
點擊復制
燃氣渦輪葉片的服役損傷與修復(
)
中國材料進展[ISSN:1674-3962/CN:61-1473/TG]
- 卷:
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- 期數:
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2012年第12期
- 頁碼:
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021-30
- 欄目:
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- 出版日期:
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2012-12-31
文章信息/Info
- Title:
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Service Induced Degradation and Rejuvenation of Gas Turbine Blades
- 作者:
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馮強; 童錦艷; 鄭運榮; 王美玲; 魏文娟; 趙海龍; 袁曉飛; 丁賢飛
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（1國家材料服役安全科學中心 北京科技大學， 北京 100083）
（2北京科技大學新金屬材料國家重點實驗室，北京 100083）
- Author(s):
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FENG Qiang; TONG Jinyan1; ZHENG Yunrong1; WANG Meiling1; WEI Wenjuan2; ZHAO Hailong1; YUAN Xiaofei; DING Xianfei1
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（1 National Center for Materials Service Safety, University of Science and Technology Beijing, Beijing 100083, China)
(2 State Key Laboratory for Advanced Metals and Materials, University of Science and Technology Beijing, Beijing 100083, China）
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- 關鍵詞:
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高溫合金; 服役; 組織損傷; 性能退化; 恢復熱處理
- DOI:
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10.7502/j.issn.1674-3962.2012.12.03
- 摘要:
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渦輪葉片是燃氣輪機最重要的熱端部件之一。它長期在不均勻的溫度場、應力場以及燃氣腐蝕和高溫氧化的環境下工作，面臨著蠕變、低周疲勞和高溫腐蝕等多種失效威脅。系統地研究渦輪葉片在服役過程中的組織損傷與性能退化規律是揭示其失效機理、探索適宜的恢復熱處理工藝以延長渦輪葉片使用壽命的必然途徑。對目前已有的渦輪葉片服役損傷研究進行了總結，同時結合本課題組對不同類型的渦輪葉片長期服役后（空中飛行時間：1 200 h~20 000 h）組織和性能損傷評估的研究結果，對存在的各種服役組織損傷形式進行了歸類和介紹，主要包括涂層的退化、拓撲密排相（TCP）的析出、二次反應區（SRZ）的形成，γ′相的粗化與筏排化，碳化物的分解與析出，蠕變孔洞與裂紋的形成等。此外，還總結了前人研究的服役渦輪葉片性能退化規律以及恢復熱處理工藝。熱端部件服役損傷的研究對燃氣輪機關鍵部件的壽命管理和安全服役具有重要的指導意義和經濟意義。
- Abstract:
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Turbine blades are one of the most important hot section components in gas turbine systems. They are subjected to complex combination of inhomogenous stresses and temperature distribution as well as high temperature corrosion and oxidation environment, resulting in failures caused by creep, low cycle fatigue and high temperature corrosion/oxidation. In order to understand failure mechanisms and develop proper rejuvenation heattreatment to extend the life time of turbine blades, it is of great necessity to study the relationship between microstructure and mechanical property degradation of turbine blades during service. This paper is to review the previous studies associated with service induced degradation of turbine blades. Various kinds of typical microstructural degradations are also classified, combined with the investigation of microstructural degradation of different types of turbine blades in aeroengines by our group (service time in air:1 200~20 000 h, respectively). The following microstructural degradation is included: surface coating degradation, precipitation of Topologically ClosePacked Phases (TCPs), formation of second reaction zone (SRZ), coarsening and rafting of γ′ phase, decomposition or precipitation of carbides, and initiation of creep cavities and cracks, etc. In addition, previous studies of mechanical property degradation and the rejuvenation heattreatment of turbine blades are also summarized. It is suggested that the investigation of the mechanism for the service induced degradation of hot section components is of great importance and economic significance for the life management and materials safety in gas turbines.
更新日期/Last Update:
2012-11-30