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GH4169合金不同孔形氣膜冷卻孔疲勞性能對(duì)比分析
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作者單位:

1.四川大學(xué) 空天科學(xué)與工程學(xué)院;2.北京衛(wèi)星環(huán)境工程研究所;3.清華大學(xué)航空發(fā)動(dòng)機(jī)研究院,北京

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中圖分類號(hào):

TG113.25+5

基金項(xiàng)目:

航天創(chuàng)新基金(CAST-BISEE2019-017)


Fatigue Property Investigation of GH4169 Alloy Film Cooling Holes with Different Shapes
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Affiliation:

1.School of Aeronautics and Astronautics,Sichuan University;2.Institute of Aero Engine,Tsinghua University,Beijing ,China

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    摘要:

    氣膜冷卻孔是航空航天高溫部件常見冷卻設(shè)計(jì)，但屬于典型結(jié)構(gòu)疲勞危險(xiǎn)點(diǎn)。為了優(yōu)化氣膜冷卻孔熱-機(jī)械性能，本文通過疲勞試驗(yàn)和有限元建模分析，研究GH4169合金相同底孔尺寸下的氣膜冷卻孔疲勞性能。研究表明：相同底孔直徑下，90°圓孔疲勞壽命遠(yuǎn)低于傾斜圓孔、扇形孔和扇形后傾孔；相同孔傾角下，孔形對(duì)疲勞壽命影響較?。?0°圓孔發(fā)生單斷口疲勞斷裂，斷口與加載方向基本垂直，而傾斜圓孔、扇形孔、扇形后傾孔在孔根部附近發(fā)生疲勞斷裂，斷口向孔軸方向傾斜，除主斷口外在孔根部均出現(xiàn)亞斷口；90°圓孔斷口疲勞裂紋在孔壁中間萌生，而傾斜圓孔和扇形孔疲勞裂紋在孔口部位萌生，且呈現(xiàn)多源萌生特征；裂紋萌生區(qū)平整光滑，隨著裂紋擴(kuò)展斷口表面韌窩明顯增多；孔軸傾角和孔口形狀對(duì)孔周應(yīng)力分布及最大應(yīng)力水平具有顯著影響。

    Abstract:

    Film cooling is a common cooling design in aerospace high temperature components, and it is also a typical fatigue risk point of the whole structure. To optimize designs of film cooling holes, an experimental and numerical study was conducted to investigatred fatigue properties of GH4169 alloy film cooling holes with different shapes. Results showed that the fatigue life of the circular shaped hole was obviously lower than those of both the oval shaped hole and the dust-pan shaped hole, and the hole shape exhibited a few influence on the fatigue life of the specimens corresponding to the same skew angle of holes. The specimens of the circular shaped hole failed with only one fracture surface, and the fracture surface was perpendicular to the loading direction. However, the specimens of the oval shaped hole and the dust-pan shaped hole failed with master fracture surface and slave master fracture surface, and the fracture surface was along the hole axis direction. Fatigue crack initiation occurred at the middle region of the circular shaped hole, while fatigue crack initiation occurred at both the entrance and the exit of the oval shaped and the dust-pan shaped hole. The crack initiation zone was flat and smooth, moreover, more dimples were observed on the fracture surface with fatigue crack propagating. Both the skew angle of holes and the shape hole orifice exhibited significant influence on the tress distribution and the peak stress of the hole under quasi-static loading.

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引用本文

左楊杰,楊艷靜,陳偉,徐全勇. GH4169合金不同孔形氣膜冷卻孔疲勞性能對(duì)比分析[J].稀有金屬材料與工程,2022,51(6):2224~2230.[Zuo Yangjie, Yang Yanjing, Chen Wei, Xu Quanyong. Fatigue Property Investigation of GH4169 Alloy Film Cooling Holes with Different Shapes[J]. Rare Metal Materials and Engineering,2022,51(6):2224~2230.]
DOI：10.12442/j. issn.1002-185X.20210509

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  • 收稿日期:2021-06-10
  • 最后修改日期:2021-07-23
  • 錄用日期:2021-08-06
  • 在線發(fā)布日期: 2022-07-06
  • 出版日期: 2022-06-29