Present Research Situation and Prospect of Hot Working of Cast & Wrought Superalloys for Aero-Engine Turbine Disk in China
ZHANG Rui1, LIU Peng1, CUI Chuanyong1(), QU Jinglong2, ZHANG Beijiang2, DU Jinhui2, ZHOU Yizhou1, SUN Xiaofeng1
1.Shi -Changxu Innovation Center for Advanced Materials, Institute of Metal Research, Chinese Academy of Sciences, Shenyang 110016, China 2.High-Temperature Materials Division, Central Iron and Steel Research Institute, Beijing 100081, China
Cite this article:
ZHANG Rui, LIU Peng, CUI Chuanyong, QU Jinglong, ZHANG Beijiang, DU Jinhui, ZHOU Yizhou, SUN Xiaofeng. Present Research Situation and Prospect of Hot Working of Cast & Wrought Superalloys for Aero-Engine Turbine Disk in China. Acta Metall Sin, 2021, 57(10): 1215-1228.
In recent years, the demand for high-performance aero-engines has become crucial in China, and the service environment of turbine disk alloy becomes increasingly severe. A series of high resistant cast & wrought superalloys for turbine disks, such as GH4065, GH4720Li, GH4068, and GH4151, with working temperatures > 700°C, have been studied, produced, and applied widely. The current studies on cast & wrought alloys for turbine disks in China were summarized under the categories of homogenization treatment, cogging, disk forging, and microstructure and property regulation to promote the development of these superalloys and improve their comprehensive properties. The difficulties encountered during the research and preparation of these hard-to-deform superalloys and explored the alloys' potential development trend were outlined. The review would improve the production stability of the disk superalloys and promote their development.
Fund: National Key Research and Development Program of China(2019YFA0705300、2017YFA-0700703);National Science and Technology Magjor Project of China(2019-VI-0006-0120);Doctoral Foundation of Liaoning Province(2020-BS-007);IMR Innovation Fund(2021-PY09)
About author: CUI Chuanyong, professor, Tel: (024)83978292, E-mail: chycui@imr.ac.cn
Fig.1 Alloying elements present in nickel-based superalloys[10]
Alloy
Co
Cr
Ti
Al
Nb
Mo
W
C
Ni
GH4065[11]
13.0
16.0
3.7
2.1
0.7
4.0
4.0
0.020
Bal.
GH4720Li[12]
15.0
15.0
5.0
2.5
-
3.0
1.2
0.015
Bal.
GH4068[13]
25.0
14.0
5.7
2.2
-
2.8
1.2
0.015
Bal.
GH4151[14]
15.0
9.0
2.8
3.7
3.4
4.5
2.5
0.080
Bal.
Table 1 Normal compositions of cast & wrought superalloys for aero-engine turbine disk[11-14]
Alloy
w(Al + Ti + Nb)
w(W + Mo)
w(W) / w(Mo)
w(Al) / w(Ti)
w(γ') at 760oC
γ' solvus temperature
%
%
%
oC
GH4065
6.5
8.0
1.00
0.57
36
1113
GH4720Li
7.5
4.2
0.40
0.50
45
1158
GH4068
7.9
3.9
0.43
0.39
48
1160
GH4151
9.9
7.0
0.56
1.32
54
1176
Table 2 Characteristic parameters of cast & wrought superalloys for aero-engine turbine disk[15]
Fig.2 Microstructure of as-cast GH4151 alloy (vacuum induction melting (VIM) ingot with diameter of 80 mm)[26]
Fig.3 Backscattered electron image of the interdendritic area (a) and elements distributions in the dendrite (b-h) of the solidified GH4720Li alloy[27]
Fig.4 Microstructures of GH4065 alloy prepared by improper cogging process[15]
Fig.5 Schematic of double-cone compression test[34]
Fig.6 Microstructures of GH4068 alloy after homogenization treatment (a) and cogging (b) (Insets show the magnification of select boxes)
Fig.7 Dynamic recrystallization mechanisms of GH4068 alloy[43]
Fig.8 Processing map of GH4068 alloy based on microstructure evolution (—strain rate)[37]
Fig.9 Processing map of U720Li alloy based on microstructure evolution [42]
Fig.10 Superplasticity of GH4068 alloy with γ + γ' micro-duplex microstructure
Fig.11 Microstructures of γ' phase in GH4068 with different cooling of solution treatment[48]
Alloy
Temperature
σ
τ
A
oC
MPa
h
%
GH4065[5]
650
970
297
4
750
590
51
9
GH4720Li[19]
680
830
209
11
730
530
166
32
GH4068
680
830
500
6
750
530
208
15
GH4151
650
1010
172
5
750
620
132
8
Table 3 High temperature endurance performances of cast & wrought superalloys for aero-engine turbine disk[5,19]
Fig.12 Creep mechanisms of several typical disk superalloys[48]
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