High Cycle Fatigue Behavior of Second Generation Single Crystal Superalloy

doi:10.11900/0412.1961.2019.00110

Acta Metall Sin

2019, Vol. 55

Issue (9): 1195-1203 DOI: 10.11900/0412.1961.2019.00110

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High Cycle Fatigue Behavior of Second Generation Single Crystal Superalloy

LI Jiarong(

),XIE Hongji,HAN Mei,LIU Shizhong

Science and Technology on Advanced High Temperature Structural Materials Laboratory, Beijing Institute of Aeronautical Materials, Beijing 100095, China

Cite this article:

LI Jiarong,XIE Hongji,HAN Mei,LIU Shizhong. High Cycle Fatigue Behavior of Second Generation Single Crystal Superalloy. Acta Metall Sin, 2019, 55(9): 1195-1203.

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Abstract

Ni-based single crystal superalloys have excellent comprehensive properties and become the preferred material for advanced aeroengine turbine blades. DD6 alloy which has been widely used in China and DD5 alloy are the second generation single crystal superalloy, and their chemical compositions and mechanical properties are quite different. In the past few decades, high cycle fatigue failure has become one of the main causes of turbine blade failure. More and more attention has been paid to the high cycle fatigue properties of single crystal superalloys. Therefore, it is important to study the high cycle fatigue behavior of single crystal superalloys, especially the second generation single crystal superalloys. In order to compare high cycle fatigue performance, two typical second generation single crystal (SC) superalloys DD6 and DD5 with [001] orientation were subjected to high cycle fatigue (HCF) loading at temperatures of 760 and 980 ℃ in ambient atmosphere. The results demonstrate that the fatigue limit of DD6 alloy is 414 and 403 MPa at temperatures of 760 and 980 ℃, respectively. DD6 alloy exhibits an excellent HCF performance under a condition of stress ratio of -1 regardless of medium or high temperature. Analysis on fracture surfaces of DD6 and DD5 alloys at 760 and 980 ℃ demonstrate that quasi-cleavage mode is observed. In addition, different types of dislocation structures were developed during the cyclic deformation. When the stress amplitude is low, dislocation movement in the γ matrix by bowing and cross slip is the main deformation mechanism and shearing γ' particles by dislocation pairs occurs occasionally under high stress level. The analysis shows that the carbon content of DD5 alloy is eight times than that of DD6 alloy, which makes the carbide content much higher than DD6 alloy, and there are significant differences in carbide morphology. In the process of fatigue fracture, carbide plays two roles of secondary crack initiation position and crack propagation channel, which greatly accelerates the fatigue crack growth rate. In the end, the fatigue resistance of DD5 alloy is reduced.

Key words: second generation single crystal superalloy high cycle fatigue behavior carbide

Received: 10 April 2019

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	Jiarong LI
	Hongji XIE
	Mei HAN
	Shizhong LIU

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https://www.ams.org.cn/EN/10.11900/0412.1961.2019.00110 OR https://www.ams.org.cn/EN/Y2019/V55/I9/1195

Table 1 Nominal compositions of DD6 and DD5 alloys (mass fraction / %)

Fig.1 Schematic of smooth specimen for high cycle fatigue test (unit: mm)

Fig.2 Comparisons of high cycle fatigue property between DD6 and DD5 alloys at 760 ℃ (a) and 980 ℃ (b) (σ_a—stress amplitude, N_f—fatigue life)

Fig.3 Fracture surface SEM images of DD6 and DD5 alloys(a) DD6, 760 ℃, σ_a=700 MPa, N_f=5.74×10⁴ cyc (b) DD5, 760 ℃, σ_a=600 MPa, N_f =8.96×10⁴ cyc(c) DD6, 980 ℃, σ_a=460 MPa, N_f =4.57×10⁶ cyc (d) DD5, 980 ℃, σ_a=500 MPa, N_f =5.84×10⁵ cyc

Fig.4 Low (a, b) and high (c, d) magnified microscopic fracture surface SEM images of DD6 alloy at 760 ℃ (a, c) and 980 ℃ (b, d)

Fig.5 SEM images of longitudinal sections near the fracture surface of fatigue-ruptured DD6 and DD5 alloys at 760 ℃(a, b) center and edge of DD6 alloy, respectively, σ_a=600 MPa, N_f =1.19×10⁵ cyc(c, d) center and edge of DD5 alloy, respectively, σ_a=500 MPa, N_f =1.73×10⁵ cyc (Arrow in Fig.5c shows the stress direction)

Fig.6 TEM images of dislocation configuration near fatigue fractures of DD6 and DD5 alloys at 760 ℃(a) DD6, σ_a=500 MPa, N_f =8.45×10⁵cyc (b) DD6, σ_a=700 MPa, N_f =5.74×10⁴ cyc(c) DD5, σ_a=400 MPa, N_f=1.41×10⁶ cyc (d) DD5, σ_a=600 MPa, N_f =8.96×10⁴ cyc

Fig.7 SEM images of carbides in DD6 (a) and DD5 (b) alloys

Fig.8 Fatigue crack initiation of DD6 (a, c) and DD5 (b, d) alloys at 760 ℃ (a, b) and 980 ℃ (c, d)

Fig.9 SEM images of longitudinal sections near the fatigue fracture surface of DD5 alloy specimens(a~c) 760 ℃, σ_a=400 MPa, N_f =1.41×10⁶ cyc (d~f) 980 ℃, σ_a=400 MPa, N_f =8.48×10⁶ cyc

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