30min）下，蠕變損傷占主導(dǎo)地位，降低了材料的蠕變-疲勞壽命。而后,斷口的SEM分析表明：隨著保持時間的增加,裂紋形成區(qū)由穿晶和沿晶混合斷裂向沿晶斷裂轉(zhuǎn)化；裂紋擴(kuò)展區(qū)由穿晶斷裂向穿晶、沿晶的混合模式轉(zhuǎn)化。最后,基于GH720Li合金的蠕變-疲勞試驗數(shù)據(jù),分別選取載荷譜轉(zhuǎn)換法和機(jī)械功密度法進(jìn)行GH720Li合金的蠕變-疲勞壽命預(yù)測,并研究了2種模型的工程適用性。"/>

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GH720Li鎳基高溫合金蠕變-疲勞試驗研究
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北京航空航天大學(xué)能源與動力工程學(xué)院,北京航空航天大學(xué)能源與動力工程學(xué)院,北京航空航天大學(xué)能源與動力工程學(xué)院,北京航空航天大學(xué)能源與動力工程學(xué)院

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中圖分類號:

V252.1

基金項目:

國家自然科學(xué)基金(51305012, 51375031), 航空科學(xué)基金(2014ZB51)


Experimental study on creep-fatigue test of nickel-based superalloy GH720Li
Author:
Affiliation:

School of Energy and Power Engineering,Beihang University,School of Energy and Power Engineering,Beihang University,School of Energy and Power Engineering,Beihang University,School of Energy and Power Engineering,Beihang University

Fund Project:

National Natural Science Foundation of China (No. 51305012, 51375031) ；Aeronautical Science Foundation of China（No. 2014ZB51）

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    摘要:

    本文對先進(jìn)航空發(fā)動機(jī)渦輪盤的典型材料—鎳基高溫合金GH720Li的蠕變-疲勞特性進(jìn)行了試驗研究。通過對真實渦輪盤上取樣的圓棒試驗件,開展了650°C不同保持時間下的GH720Li合金蠕變-疲勞試驗。結(jié)果表明,650°C溫度下保持時間對GH720Li合金的蠕變-疲勞特性影響較大,即,在較長的保持時間（>30min）下，蠕變損傷占主導(dǎo)地位，降低了材料的蠕變-疲勞壽命。而后,斷口的SEM分析表明：隨著保持時間的增加,裂紋形成區(qū)由穿晶和沿晶混合斷裂向沿晶斷裂轉(zhuǎn)化；裂紋擴(kuò)展區(qū)由穿晶斷裂向穿晶、沿晶的混合模式轉(zhuǎn)化。最后,基于GH720Li合金的蠕變-疲勞試驗數(shù)據(jù),分別選取載荷譜轉(zhuǎn)換法和機(jī)械功密度法進(jìn)行GH720Li合金的蠕變-疲勞壽命預(yù)測,并研究了2種模型的工程適用性。

    Abstract:

    In this paper, the creep-fatigue behavior of a nickel-based superalloy GH720Li widely used for the turbine disk of an aero-engine was experimentally investigated. The cylindrical bars cut from an actual turbine disk were employed. The creep-fatigue tests with different dwell times were performed at 650°C. Experimental results revealed GH720Li is very sensitive to dwell time at 650°C, i.e., at the longer hold time (> 30min), the creep damage is dominant, thus decreases the creep-fatigue life. Then, the mechanism of creep-fatigue failure was discussed by using the SEM analyses of the fracture surface. It was found that with the increase of dwell time, the failure mode of the crack formation zone is transformed from a mixture of transgranular and intergranular to an intergranular failure. In addition, the crack formation zone is transformed from an intergranular fracture to a mixture failure mode. Finally, based on the experimental data, loading patterns transformation method and AMWD method were applied to predict the creep-fatigue life, and the applicability of two models was discussed.

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胡殿印,馬琦航,高曄,王榮橋. GH720Li鎳基高溫合金蠕變-疲勞試驗研究[J].稀有金屬材料與工程,2018,47(7):2185~2191.[Hu Dianyin, Ma Qihang, Gao Ye, Wang Rongqiao. Experimental study on creep-fatigue test of nickel-based superalloy GH720Li[J]. Rare Metal Materials and Engineering,2018,47(7):2185~2191.]
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  • 收稿日期:2016-07-01
  • 最后修改日期:2016-07-18
  • 錄用日期:2016-08-18
  • 在線發(fā)布日期: 2018-10-10
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