Effect of Aging Treatment at 750℃ on Fatigue Crack Propagation Behavior of GH4742 Superalloy

doi:10.11901/1005.3093.2019.138

Chinese Journal of Materials Research

2019, Vol. 33

Issue (10): 721-727 DOI: 10.11901/1005.3093.2019.138

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Effect of Aging Treatment at 750℃ on Fatigue Crack Propagation Behavior of GH4742 Superalloy

ZHANG Xingshuo^1,²,WANG Lei^1,²(

),LIU Yang^1,²,WANG Sikun^1,²

1. Key Laboratory for Anisotropy and Texture of Materials (Ministry of Education), Northeastern University, Shenyang 110819, China
2. School of Materials Science and Engineering, Northeastern University, Shenyang 110819, China

Cite this article:

ZHANG Xingshuo,WANG Lei,LIU Yang,WANG Sikun. Effect of Aging Treatment at 750℃ on Fatigue Crack Propagation Behavior of GH4742 Superalloy. Chinese Journal of Materials Research, 2019, 33(10): 721-727.

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Abstract

The effect of the microstructure of GH4742 superalloy after aging at 750℃ on the fatigue crack propagation behavior were investigated. The results show that during aging the primary block like γ′-phase grows up with a smooth boundary, the secondary petal-shaped γ′-phase breaks along the boundary, and the thrice γ′-phase re-dissolves into the matrix or coarsens into corner square like γ′-phase. The main fatigue crack easily propagates across the region without the primary γ′-phase or the secondary γ′-phase. With the increasing aging time the fatigue crack propagation rate increases. Within the near-threshold region the fatigue crack propagation rate is very sensitive to the microstructure. The smooth boundaries of the primary γ′-phase and the secondary γ′-phase lead to the increase of fatigue crack propagation rate, but the fatigue crack propagation resistance increases with the appropriate coarsening of the thrice γ′-phase within the low ΔK region. Because the range of stress intensity factor ΔK is higher in both the Paris region and the rapid propagation region, the influence of the microstructure on the fatigue crack propagation rate is decreased.

Key words: metallic materials GH4742 superalloy aging fatigue crack propagation behavior

Received: 04 March 2019

ZTFLH:

TG132.3

Fund: National Natural Science Foundation of China(U1708253);Major Projects in Aviation Engines and Gas Turbines(2017-VI-0002)

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	Xingshuo ZHANG
	Lei WANG
	Yang LIU
	Sikun WANG

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https://www.cjmr.org/EN/10.11901/1005.3093.2019.138 OR https://www.cjmr.org/EN/Y2019/V33/I10/721

Fig.1 Dimensions of tensile specimen of GH4742 superalloy

Fig.2 Compact-tension specimen of GH4742 superalloy used for fatigue crack growth rate testing

Fig.3 SEM morphology of γ′ phase of GH4742 superalloy (a) SHTed; aged at 750℃ for (b) 100 h; (c) 500 h; (d) 1000 h

Fig.4 SEM morphology of MC carbide of GH4742 superalloy

Fig.5 Fatigue crack growth rate da/dN versus ΔK of GH4742 superalloy

Table 1 Paris formula of GH4742 superalloy aged at 750℃

Fig.6 Fatigue crack growth morphology in near-threshold regions of GH4742 superalloy (a) SHTed; aged at 750℃ for (b) 100 h; (c) 500 h; (d) 1000 h

Table 2 The RT tensile property and hardness of GH4742 superalloy aged at 750℃

Fig.7 Fatigue crack growth morphology of GH4742 superalloy aged at 750℃ (a), (b) SHTed in Paris regions and in rapid propagation regions; (c), (d) aged at 750℃ for 1000 h in Paris regions and in rapid propagation regions

Fig.8 Roughness of fatigue crack growth path of GH4742 superalloy aged at 750℃

Fig.9 Fatigue crack growth morphology of near-threshold regions (a, d, g, j), Paris regions (b, e, h, k) and rapid propagation regions (c, f, i, l) of GH4742 superalloy (a-c) SHTed; aged at 750℃ for (d-f) 100 h; (g-i) 500 h and (j-l) 1000 h

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