| 冯贞伟1，杨树林1，梅飞强1，吴会萍2，李中生1.GH2909 合金锻件缺口持久敏感性试验与分析[J].航空发动机,2021,47(S1):124-132 |
| GH2909 合金锻件缺口持久敏感性试验与分析 |
| Test and Analysis of Notch Rupture Sensitivity of GH2909 Alloy Forging |
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| DOI： |
| 中文关键词: GH2909合金 热加工 锻件 缺口持久 热处理 航空发动机 |
| 英文关键词:GH2909 alloy thermal process forging notch rupture heat treatment aeroengine |
| 基金项目: |
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| 中文摘要: |
| 针对低膨胀高温合金GH2909锻造及热处理后锻件持久性能不合格问题，确定合适的热加工工艺参数及合理的工艺方
法，改善其锻件缺口持久敏感性，对该合金采用不同的锻造工艺和热处理制度进行试验，观察显微组织和检测室温及高温性能。
结果表明：控制锻件热料回炉不低于900 ℃，模具预热；锻件预热时间系数控制在0.6～0.8 min/mm 范围，加热时间系数控制在
0.4～0.6 min/mm范围；当第一步锻造和最后一步锻造的加热温度分别为1050 ℃和1000 ℃时，变形量增加可使GH2909 合金的显
微组织细小且分布均匀；2次固溶+2段式时效热处理制度对GH2909 合金组织析出物有明显影响，并使室温和高温拉伸强度提高。
锻件合格率由6.25%提高到90%以上。 |
| 英文摘要: |
| In order to solve the problem that the rupture property of low expansion superalloy GH2909 forging was not qualified after
forging and heat treatment，the appropriate thermal process parameters and reasonable process methods were determined to improve the
notch rupture sensitivity of the forging. Different forging processes and thermal process systems were used to observe the microstructure，
test the room and high temperature properties of the alloy. The results show that the hot material return of forgings is not less than 900 ℃
and the die is preheated. The preheating time coefficient of forgings should be controlled in the range of 0.6～0.8 min / mm and the heating
time coefficient should be controlled in the range of 0.4～0.6 min / mm. When the heating temperature of the first step forging and the last
forging is 1050℃ and 1000℃，the increase of deformation can make the microstructure of GH2909 alloy fine and evenly distributed. The
secondary solid solution+secondary aging heat treatment system has a significant effect on the precipitates of GH2909 alloy and improves
the tensile strength at room temperature and high temperature. The qualified rate of forgings has been increased from 6.25% to over 90%. |
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