火箭推进

GH4586合金涡轮盘是新一代液体火箭发动机的核心部件之一,服役环境极其恶劣,提高涡轮盘模锻件微观组织均匀性有益于提高产品力学性能的稳定性和可靠性。通过热压缩试验,研究了变形温度、应变对GH4586合金微观组织和再结晶行为的影响,得到了GH4586合金热成形工艺参数范围; 结合有限元仿真和模锻成形试验,分析了不同预制坯形状对涡轮盘模锻件应变分布和组织均匀性的影响,采用从边缘到中心梯度升高的双陀螺形预制坯形状、在1 060 ℃条件下进行模锻成形,可以获得组织均匀的涡轮盘模锻件,心部晶粒度等级达到6～7级,盘部R/2处和边缘处晶粒度等级7～8级; 室温、低温和高温力学性能均满足标准要求,特别是-196 ℃时延伸率和600 ℃时抗拉强度相较原工艺方案分别提高了37%和12%。

GH4586 alloy turbine disk is one of the core components of the new generation liquid rocket engine.Due to the extremely terrible service environment, it is necessary to improve the microstructure uniformity of turbine disk in die forging and therefore is beneficial to improve the stability and reliability of mechanical properties. The effects of temperature and strain on the microstructures and recrystallization behavior of GH4586 alloy were studied by hot compression tests, and the range of hot forming process parameters were obtained. Based on finite element simulation and die forging experiment, the effects of different preformed blanks on strain distribution and uniformity of microstructure were compared and analyzed. The turbine disk die forging with uniform microstructure was obtained by using the double gyro preform shape with gradient rising from edge to center, and forged at 1 060 ℃. The grain size reached 6～7 at the core, and 7～8 when locating at the middle and edge. The mechanical properties of GH4586 alloy turbine disk made by the preformed blank at room temperature, cryogenic and high temperature all meet the requirement of the standards, especially the elongation at -196 ℃ and the ensile strength at 600 ℃ were increased by 37% and 12% compared with the one made by original scheme,respectively.

引言
1 热成形参数对GH4586合金微观组织的影响
2 涡轮盘模锻成形预制坯仿真优化
3 GH4586涡轮盘模锻成形试验
4 结论

表1 GH4586合金化学成分的质量分数<br/>Tab.1 Chemical composition of the compression samples of GH4586 alloy 单位:%

表1 GH4586合金化学成分的质量分数
Tab.1 Chemical composition of the compression samples of GH4586 alloy 单位:%

图1 变形温度对GH4586合金微观组织的影响<br/>Fig.1 Effects of deformation temperature on the microstructure of GH4586 alloy

图1 变形温度对GH4586合金微观组织的影响
Fig.1 Effects of deformation temperature on the microstructure of GH4586 alloy

表2 不同应变量条件下的GH4568合金晶粒度<br/>Tab.2 Grain size of GH4586 alloy under different strain

表2 不同应变量条件下的GH4568合金晶粒度
Tab.2 Grain size of GH4586 alloy under different strain

图2 应变对GH4586合金微观组织的影响<br/>Fig.2 Effects of strain on the microstructure of GH4586 alloy

图2 应变对GH4586合金微观组织的影响
Fig.2 Effects of strain on the microstructure of GH4586 alloy

图3 涡轮盘模锻件零件轮廓尺寸<br/>Fig.3 Dimensions of the turbine disc die forging

图3 涡轮盘模锻件零件轮廓尺寸
Fig.3 Dimensions of the turbine disc die forging

图4 3种不同预制坯方案<br/>Fig.4 Three different performed blanking schemes

图4 3种不同预制坯方案
Fig.4 Three different performed blanking schemes

图5 不同温度、应变量条件下GH4586合金真实应力应变曲线<br/>Fig.5 True stress-strain curve at different temperature and strain

图5 不同温度、应变量条件下GH4586合金真实应力应变曲线
Fig.5 True stress-strain curve at different temperature and strain

图6 3种预制坯方案模锻成形等效应变(PEEQ)分布云图<br/>Fig.6 Equivalent plastic strain distribution of die forgings with three performed blanking schemes

图6 3种预制坯方案模锻成形等效应变(PEEQ)分布云图
Fig.6 Equivalent plastic strain distribution of die forgings with three performed blanking schemes

图7 涡轮盘模锻件金相取样位置示意图<br/>Fig.7 Sketch diagram of sampling position of turbine disk die forging

图7 涡轮盘模锻件金相取样位置示意图
Fig.7 Sketch diagram of sampling position of turbine disk die forging

表3 不同工艺方案模锻件与原始棒料晶粒度对比<br/>Tab.3 Comparison of grain size of turbine disk die forgings under different process schemes and initial bar

表3 不同工艺方案模锻件与原始棒料晶粒度对比
Tab.3 Comparison of grain size of turbine disk die forgings under different process schemes and initial bar

图8 涡轮盘模锻件不同位置与原始棒料显微组织对比<br/>Fig.8 Comparison of microstructure of turbine disk die forgings in different deformation zones and initial bar

图8 涡轮盘模锻件不同位置与原始棒料显微组织对比
Fig.8 Comparison of microstructure of turbine disk die forgings in different deformation zones and initial bar

表4 涡轮盘模锻件力学性能与原始棒料对比<br/>Tab.4 Comparison of mechanical properties of turbine disk die forgings, initial bar and original scheme

表4 涡轮盘模锻件力学性能与原始棒料对比
Tab.4 Comparison of mechanical properties of turbine disk die forgings, initial bar and original scheme

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备注

引言

1 热成形参数对GH4586合金微观组织的影响

2 涡轮盘模锻成形预制坯仿真优化

3 GH4586涡轮盘模锻成形试验

4 结论

期刊信息