热力耦合模拟服役条件对DZ406合金组织和持久性能的影响

贾新云; 宗毳; 郭婧; 陈升平; 郑真; 赵文侠; 黄朝晖

doi:10.11868/j.issn.1005-5053.2021.000172

热力耦合模拟服役条件对DZ406合金组织和持久性能的影响

doi: 10.11868/j.issn.1005-5053.2021.000172

1.
中国航发北京航空材料研究院先进高温结构材料重点实验室，北京 100095
2.
中国航发湖南动力机械研究所，湖南株洲 412002
3.
中国航发北京航空材料研究院航空材料检测与评价北京市重点实验室，北京 100095

详细信息

通讯作者:
贾新云（1971—），女，硕士，高级工程师，主要从事铸造高温合金的研究，E-mail: jiaxinyun@sina.com

中图分类号: TG132.3
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- 被引次数: 0
出版历程
- 收稿日期: 2021-10-21
- 录用日期: 2022-02-07
- 修回日期: 2022-03-11
- 刊出日期: 2022-04-22

Effect of thermodynamic coupled simulation condition on microstructure and stress rupture properties of DZ406 alloy

1.
AECC Science and Technology on Advanced High Temperature Structural Materials Laboratory, AECC Beijing Institute of Aeronautical Materials, Beijing 100095, China
2.
AECC Hunan Powerplant Research Institute, Zhuzhou 412002, Hunan，China
3.
Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation，AECC Beijing Institute of Aeronautical Materials, Beijing 100095, China

摘要

摘要: 在高温长期服役条件下高温合金涡轮叶片的组织存在老化和性能退化问题。通过对DZ406合金试样进行预先加载处理，模拟涡轮叶片的高温服役环境，热力耦合模拟条件分别为980 ℃/70 MPa，980 ℃/110 MPa，980 ℃/140 MPa与980 ℃/180 MPa，再对试样进行980 ℃/275 MPa持久实验。观察分析不同服役载荷条件下试样的显微组织和980 ℃/275 MPa持久寿命。结果表明：DZ406合金标准热处理组织由碳化物、残余（γ+γ´）共晶和规则立方状的γ´相组成；在模拟服役条件热力耦合作用下，随着服役载荷应力的增加，合金的共晶和碳化物形貌及尺寸无明显变化，平行于[001]方向试样的γ´相呈现不同程度的筏排化，垂直于[001]方向截面的γ´相尺寸明显增大；随着服役载荷应力的增加，不同热力耦合作用试样的剩余持久寿命迅速降低。
- 定向高温合金DZ406 /
- 热力耦合模拟 /
- 持久寿命 /
- 筏排化
Abstract: There is a problem about microstructure evolution and properties degradation for the superalloy turbine blades in long term service conditions. DZ406 alloy samples were pre-loaded to simulate the high temperature service environment of turbine blades. The thermodynamic coupling simulation conditions were 980 ℃/70 MPa, 980 ℃/110 MPa, 980 ℃/140 MPa and 980 ℃/180 MPa respectively. And then the samples were subjected to stress rupture property test at 980 ℃/275 MPa. The microstructure and 980 ℃/275 MPa rupture life of the samples under different service loading conditions were observed and analyzed. The results show that the heat treatment microstructure of DZ406 alloy is composed of carbides, residual γ +γ´ eutectic and regular γ´ phase. The morphology and size of carbides and eutectic have no obvious change with the increase of loading stress under simulated service conditions. The γ´ phase of the sample parallel to [001] direction presents different degrees of rafting, and the size of γ´ phase perpendicular to [001] direction obviously increases. The residual stress rupture life of the sample declines rapidly with the increase of service stress.
- directional DZ406 superalloy /
- thermodynamic coupled simulation /
- stress rupture life /
- rafting

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图 1 DZ406合金标准热处理组织　（a）碳化物和共晶相；（b）枝晶干γ´相.

Figure 1. Microstructure of DZ406 alloy after heat treatment 　(a) carbides and eutectic；(b) γ´ phase at the dendrite

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图 2 980 ℃/70 MPa条件下时效500 h的显微组织　（a）垂直[001]取向的碳化物和共晶相；（b）平行[001]取向的碳化物和共晶相；（c）垂直[001]取向的枝晶干γ´相；（d）平行[001]取向的枝晶干γ´相

Figure 2. Microstructures of the alloy after aging at 980 ℃/70 MPa for 500 h 　(a) carbides and eutectic perpendicular to [001] direction；(b) carbides and eutectic parallel to [001] direction； (c) γ´ phase at the dendrite perpendicular to [001] direction；(d) γ´ phase at the dendrite parallel to [001] direction

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图 3 980 ℃/110 MPa条件下时效500 h的显微组织　（a）垂直[001]取向的碳化物和共晶相；（b）平行[001]取向的碳化物和共晶相；（c）垂直[001]取向的枝晶干γ´相；（d）平行[001]取向的枝晶干γ´相

Figure 3. Microstructures of the alloy after aging at 980 ℃/110 MPa for 500 h 　(a) carbides and eutectic perpendicular to [001] direction；(b) carbides and eutectic parallel to [001] direction； (c) γ´ phase at the dendrite perpendicular to [001] direction；(d) γ´ phase at the dendrite parallel to [001] direction

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图 4 980 ℃/140 MPa条件下时效500 h的显微组织　（a）垂直[001]取向的碳化物和共晶相；（b）平行[001]取向的碳化物和共晶相；（c）垂直[001]取向的枝晶干γ´相；（d）平行[001]取向的枝晶干γ´相

Figure 4. Microstructures of the alloy after aging at 980 ℃/140 MPa for 500 h　 (a) carbides and eutectic perpendicular to [001] direction；(b) carbides and eutectic parallel to [001] direction； (c) γ´ phase at the dendrite perpendicular to [001] direction；(d) γ´ phase at the dendrite parallel to [001] direction

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图 5 980 ℃/180 MPa条件下时效500 h的显微组织　（a）垂直[001]取向的碳化物和共晶相；（b）平行[001]取向的碳化物和共晶相；（c）垂直[001]取向的枝晶干γ´相；（d）平行[001]取向的枝晶干γ´相

Figure 5. Microstructure of the alloy after aging at 980 ℃/180 MPa for 500 h　 (a) carbides and eutectic perpendicular to [001] direction；(b) carbides and eutectic parallel to [001] direction； (c) γ´ phase at the dendrite perpendicular to [001] direction；(d) γ´ phase at the dendrite parallel to [001] direction

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图 6 模拟服役环境条件下试样的980 ℃/275 MPa剩余持久寿命

Figure 6. 980 ℃/275 MPa residual stress rupture lives of sample at the simulated service environment

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图 7 模拟服役条件下试样持久性能断口宏观形貌　（a）980 ℃/70 MPa断口正面; （b）980 ℃/70 MPa断口侧面; （c）980 ℃/140 MPa断口正面; （d）980 ℃/140 MPa断口侧面

Figure 7. Fractograph macro-morphologies of stress rupture of the samples at the simulated service environment 　(a) 980 ℃/70 MPa, fracture frontage; (b) 980 ℃/70 MPa, fracture profile; (c) 980 ℃/140 MPa, fracture frontage; (d) 980 ℃/140 MPa， fracture profile

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图 8 模拟服役载荷试样断口形貌　（a）980 ℃/70 MPa，低倍; （b）980 ℃/70 MPa，高倍;（c）980 ℃/140 MPa，低倍; （d）980 ℃/140 MPa，高倍

Figure 8. Fracture morphologies of samples at the simulated service environment　 (a) 980 ℃/70 MPa, low magnification; (b) 980 ℃/70 MPa, high magnification; (c) 980 ℃/140 MPa, low magnification; (d) 980 ℃/140 MPa, high magnification

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图 9 试样近断口显微组织　（a）70 MPa服役载荷试样；（b） 140 MPa服役载荷试样

Figure 9. Microstructure near the fracture surface of ruptured samples 　 (a) 70 MPa service load sample; (b) 140 MPa service load sample

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表 1 DZ406合金的化学成分(质量分数/%)

Table 1. Nominal chemical compositions of DZ406 alloy (mass fraction/%).

Cr	Co	W	Al	Ta	Mo	Re	Hf	B	C	Ni
6.5-7.0	11.4-12.1	4.7-5.1	5.8-6.3	6.1-6.5	1.3-1.7	2.6-3.0	1.3-1.7	0.01-0.02	0.08-0.14	Bal

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表 2 筏状γ´相垂直[001]方向的厚度尺寸测量结果

Table 2. Rafted γ´ thickness perpendicular to [001] orientation

Simulated service sample	γ´ thickness 1/nm	γ´thickness 2/nm	γ´thickness 3/nm	γ´thickness 4/nm	γ´thickness 5/nm	Mean value/nm
180 MPa	648.1	688.0	527.6	634.2	485.8	596.7
140 MPa	594.2	649.7	702.0	647.5	634.2	645.5
110 MPa	716.1	569.1	582.9	675.0	664.4	641.5
70 MPa	612.4	553.1	418.4	522.8	584.0	538.1

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表 3 模拟服役环境条件下试样的980 ℃/275 MPa剩余持久寿命

Table 3. 980 ℃/275 MPa residual stress rupture lives of sample at the simulated service environment

Load condition	Sample group 1	Sample group 2	Sample group 3	Average value
180 MPa	8.8 h	1.2 h	—	5 h
140 MPa	15.3 h	17.3 h	20.4 h	17.7 h
110 MPa	14.8 h	23.2 h	20.6 h	19.5 h
70 MPa	35.3 h	24.2 h	31.8 h	30.4 h

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