Effects of Grain Refinement on the Low-Cycle Fatigue Behavior of IN792 Superalloys

Abstract

The Ni-based IN792 superalloy is widely applied as a component in industrial turbines and aircraft engines due to its good high-temperature properties and excellent corrosion resistance. Since these components have to suffer from cyclic thermal and mechanical stresses during service, the high-temperature fatigue failure becomes one of the major factors affecting their service lives. Grain refinement has been considered as an effective way to improve the mechanical performance of superalloys. However, due to the complexity of alloy composition, microstructure and service condition, there is no unified theory about the influence of grain refinement on the fatigue performance and fracture mechanism of superalloys. In the present research, the IN792 superalloy with different grain sizes was manufactured. Then, fully reversed, strain-controlled, low-cycle fatigue (LCF) tests with four different total strain amplitudes were carried out on the alloy at 700 °C and 800 °C to clarify the effects of grain refinement on its LCF behavior. The results show that grain refinement improved the fatigue life significantly, which is mainly attributed to increasing the grain boundary content and refining MC carbides, eutectic structures and dendritic structures. During fatigue test under lower strain amplitude, the alloy exhibits a pronounced initial fatigue hardening followed by a continuous well-defined stability stage, which is caused by the formation of dislocation networks and coarsening of primary γ’ phases. However, during fatigue test under higher strain amplitude, the alloy exhibits continuous hardening response because the dislocations could shear primary γ’ phases, which could give rise to resistance to dislocation movement. In addition, the fracture surface observation shows that the fatigue fracture mode is mainly affected by the total strain amplitude. Under lower total strain amplitude, the fatigue microcracks mainly initiate at the porosities near the specimen surface, while under higher total strain amplitude, the fatigue microcracks tend to form at the interior of the specimen.

1. Introduction

Ni-based polycrystalline cast superalloys have relatively low manufacturing costs, excellent mechanical properties and microstructure stability in the range of 600–900 °C, and they are widely used in aeroengines, gas turbines and automobiles components [1,2,3,4]. It has been regarded that the service performance of polycrystalline superalloys is closely related to their grain size, and the refining of grains is always considered as an effective means to improve the mechanical properties and retard their failure [5,6,7].

However, extensive studies [8,9,10,11,12] have shown that the influence of grain size on the mechanical properties of superalloys is closely related to the experimental conditions. It is generally believed that [9,11,13,14,15,16,17,18,19] with the increase in temperature, the strengthening effect of grain refinement on polycrystalline superalloys gradually decreases, because the grain boundary strength drops faster than grain interior strength as the temperature increases. The authors have investigated the tensile properties of Ni-based K417G superalloys with different grain sizes [11], and found that grain refinement could improve the tensile strength but decrease the ductility at 700 °C. At 900 °C, grain refinement has little influence on the tensile strength but would decrease the ductility. Wei [8] manufactured IN713LC superalloys with different grain sizes by adjusting the pouring temperature and the results show that the room temperature yield strength increases along with grain refinement. However, when the grains are refined to 25 μm, the elongation drops significantly, which may be attributed to the existence of porosities. Moreover, studies [4,16,17,18,19] have proved that grain refinement would reduce the creep property of superalloys at high temperature, because the grain boundaries would slide and produce intergranular cracks. The creep performance of K417G superalloys with different grain sizes is also studied by the authors of [20], who found that with the refining of grains, the creep life is improved under 760 °C/645 MPa. The creep life under 900 °C/315 MPa first increases and then decreases, while the creep life under 950 °C/235 MPa continuously decreases.

Aeroengine components often suffer from fatigue damages, including high-cycle fatigue (HCF) and low-cycle fatigue (LCF). Kobayashi [21] has investigated the influence of grain size on the HCF properties of an IN718 superalloy, and found that the HCF strength of fine-grain alloys is higher than coarse-grain alloys beyond 10⁵ cycles. The research of Chan [22] reveals that HCF crack initiation is favored in coarse-grained alloy compared to fine-grained alloys. The previous investigation of the authors of [10] on the HCF behavior of an IN792 superalloy found that through grain refinement, the “fatigue hot spots” would tend to transfer from specimen subsurface to the center gradually, and the initiation and propagation of fatigue cracks would be impeded. In addition, during the start and stop process of the aeroengine, the components would bear cyclic stress with high stress amplitude and low loading frequency, causing LCF fracture. Morrison [12] has conducted LCF tests on polycrystalline nickel of two grain sizes, and found that the alloy with a fine grain has a longer fatigue life, especially at low strain amplitude, because the refining of grains changed the crack initiation characteristics. Consequently, it can be found that the effect of grain refinement on the fatigue performance and fatigue fracture mechanism of superalloys is closely related to the alloy composition, microstructure, experimental conditions and other factors, and the existing studies have not obtained unified conclusions. Based on our previous research on the HCF properties of IN792 superalloys, in order to clarify the effects of grain refinement on the LCF performance of an IN792 superalloy, different melting and pouring temperatures are applied to this alloy to obtain different grain sizes, and then the microstructures are characterized and LCF tests at different temperatures and total strain amplitudes are conducted. The LCF fracture mode and deformation mechanism are analyzed, and the effects of grain refinement on the LCF performance of IN792 superalloy are discussed.

2. Materials and Methods

2.1. IN792 Superalloy Preparation

An IN792 superalloy, the nominal composition of which is shown in

Table 1. Nominal composition of IN792 superalloy (wt. %).

C	Cr	Co	Mo	W	Ta	Al	Ti	B	Zr	Ni
0.089	12.60	8.99	1.97	3.98	4.25	3.43	3.92	0.014	0.030	Balance

, was melted in a vacuum induction furnace. The alloy melt was poured into the mold, which was preheated at 850 °C. As it is known that grain refinement could be achieved by reducing the melting and pouring temperature, two different casting parameters were used to obtain two different grain sizes. The first casting parameters adopt a melting temperature of 1540 °C and a pouring temperature of 1480 °C to obtain a coarse-grain alloy, and the secondary casting parameters adopt a melting temperature of 1510 °C and a pouring temperature of 1360 °C to obtain a fine-grain alloy. Then, LCF bars of IN792 superalloy with two different grain sizes was acquired. After that, these fatigue bars were heat treated according to the following procedure: 1120 °C/2 h AC + 1080 °C/4 h AC + 845 °C/24 h AC. (AC: air cooling.)

2.2. Microstructure Observation

A cylindrical specimen was cut from the heat-treated fatigue bars, and then mechanically ground, polished and chemically etched in a solution of 5 g CuSO₄ + 20 mL HCl + 25 mL H₂O for microstructure observation. The microstructures of the IN792 superalloy, including grain size and precipitates, were observed through optical microscope (OM) and S3400N scanning electron microscope (SEM). An Image-Pro Plus (IPP) software was used to measure the volume fraction and average size of the grains and precipitates. The casting defects were observed through OM. Thin slices were cut for γ’ phase observation on transmission electron microscope (TEM). The slices were first mechanically ground to 50 μm thick, then twin-jet thinned in a solution of 10% perchloric acid and 90% alcohol at −20 °C; the twin-jet current is maintained at 40 mA. TEM observation was performed on JEM2100.

2.3. LCF Tests

The heat-treated bars were machined into standard LCF specimens, as shown in Figure 1. The LCF tests were conducted on a PLG-100C testing machine. All the specimens were tested under strain control at a strain ratio R = ɛ_min/ɛ_max = −1. The testing temperatures were 700 °C and 800 °C. A tensile-compressive loading mode was adopted and sinusoidal waveform was performed on the specimens. Four different total strain amplitudes (Δɛ_t), 0.4%, 0.5%, 0.6% and 0.8%, were used for each temperature.

2.4. Fractured Specimen Observation

After LCF tests, the fracture surfaces were examined on SEM to analyze the fracture mode. Longitudinal section samples were cut from the fractured specimens and mounted in epoxy resin. After grinding, polishing and chemical etching, the longitudinal sections were observed on SEM to study the microstructure evolution and deformation mechanism of the superalloy. In addition, TEM observation was conducted on the fatigue fractured specimens to analyze the crystal defects. Samples for TEM observation were obtained from thin slices cut at a distance of 5 mm away from the fracture surfaces of the failed specimens. Thin slices were prepared by twin-jet thinning electrolytically in a solution of 10% perchloric acid and 90% alcohol at −20 °C, 40 mA. TEM observation was performed on JEM2100.

3. Results

3.1. Microstructure

The microstructures of the IN792 superalloys with two different grain sizes are characterized through OM and SEM, as shown in Figure 2. The average sizes of the grains and precipitates were calculated and are shown in

Table 2. The average size of the grain, γ’ phase, carbide and eutectic of coarse- and fine-grain specimens.

	Average Grain Size (μm)	Average Size of MC Carbide (μm)	Average Size of Eutectic (μm)	Average Size of γ’ Phase in the Dendrite Core (nm)
CG	2300	2.6	10.7	430
FG	400	1.9	8.1	420

. The coarse-grain alloy is named CG, and the fine-grain alloy is named FG. It can be found that both the CG and FG superalloys are composed of equiaxed grains with dendritic structure inside the grains. The average grain size of the CG alloys is calculated to be about 2.3 mm, while the average grain size of the FG alloys is about 0.4 mm. The dendritic structure of the FG alloy is also finer than that of CG alloy, as illustrated in Figure 2a,e. Block and strip MC carbides precipitate in the interdendritic regions and at the grain boundary, as indicated in Figure 2b,f. According to measurements, the average sizes of MC carbides of the CG alloy and the FG alloy are 2.6 μm and 1.9 μm, respectively. In addition, flower-like γ/γ’ eutectic structures formed in the interdendritic regions and at the grain boundary of IN792 superalloys, as in Figure 2c,g. The average sizes of the γ/γ’ eutectic structures of CG alloy and FG alloy are 10.7 μm and 8.1 μm. In conclusion, the grain refinement has refined the dendritic structures, MC carbides and γ/γ’ eutectic structures of IN792 superalloy. In addition, our previous studies [23,24,25] found M₅B₃ borides at the grain boundary of IN792 superalloys. In the present research, fine granular borides of about 1 to 2 microns disperse at the grain boundary of CG and FG alloys, as shown in Figure 2d,h, and there is no difference between the grain boundary M₅B₃ borides of CG and FG alloys.

It is known that γ’ phase is the main strengthening phase of Ni-based superalloy. The γ’ phase of IN792 superalloys is observed through SEM and TEM, as shown in Figure 3. The primary γ’ phase is regular cuboidal shaped with an average size of about 400 nm, as can be found from Figure 3a,c and Table 2. Therefore, the γ’ phase is not refined by grain refinement. In the TEM bright-field images, granular secondary γ’ phases are found around primary γ’ phases. These secondary γ’ phases are about 60 nm for both the CG and FG alloys, as exhibited in Figure 3b,d.

The casting defects such as porosities are inevitable in cast superalloys, which would influence the mechanical properties, especially the fatigue property. It has been reported [10,26,27] that the casting defects could act as fatigue crack initiation sites, thus leading to the fracture of superalloys. The casting defects of IN792 superalloys in the present study are observed through OM, and it can be found that granular porosities about 10 to 30 μm are dispersed in the areas near the specimen surface for both grain size alloys, as shown in Figure 4a,c. In the center areas of the specimen, however, there are some irregular-shaped porosities gathering areas, as shown in Figure 4b,d. This is because the center of the specimen is the final solidification area, and the mobility of the melt is poor at this time; thus, the porosity formation tendency is higher than the edge area. These irregular-shaped porosities gathering areas in FG alloys are larger than that in CG alloys, which is because of the low pouring temperature.

3.2. Cyclic Stress Response Behavior

The LCF properties of IN792 superalloys with different grain sizes were tested at 700 °C and 800 °C, and four different total strain amplitudes (Δɛt), 0.004, 0.005, 0.006 and 0.008, were applied. The cyclic stress response behaviors are shown in Figure 5. When the total strain amplitude is 0.004, the IN792 superalloys show an obvious cyclic hardening response soon after several cycles of loading. Until after dozens of cycles, the cyclic hardening response ends, and the alloys gradually present a cyclic stability, as illustrated in Figure 5a. The cyclic hardening content at 700 °C is higher than 800 °C. Moreover, the stress amplitude of the FG alloy is always higher than the CG alloy. When the total strain amplitude is 0.005, the stress response shows a similar tendency with the total strain amplitude of 0.004, except for a cyclic softening at the final stage of fatigue, especially for the CG alloys, as can be found from Figure 5b. As the total strain amplitude increases to 0.006, the IN792 superalloys show continuous cyclic hardening response during the whole fatigue process. When the total strain amplitude is 0.008, the IN792 superalloys show continuous cyclic hardening response at 700 °C, but when these alloys are fatigue tested under 800 °C, there is a short steady stage at the end of the fatigue test, as indicated in Figure 5d.

3.3. Fatigue Life Curves

The relationship curves between total strain amplitudes and number of cycles to failure are plotted in Figure 6. It can be found that the fatigue life decreases with the increase in total strain amplitude. The fatigue life of the FG alloy is higher than the CG alloy at the same total strain amplitude.

The strain-controlled low-cycle fatigue performance of superalloys is generally described by the Coffin–Manson relationship, which separates the total strain amplitude into plastic and elastic strain amplitude, expressed as follows [28]:

$$\frac{\Delta {\epsilon }_t}{2}=\frac{\Delta {\epsilon }_p}{2}+\frac{\Delta {\epsilon }_e}{2}={\epsilon }_f^{\prime }{\left(2N_f\right)}^{-c}+\frac{{\sigma }_f^{\prime }}{E}{\left(2N_f\right)}^{-b}$$

where $\frac{\Delta {\epsilon }_t}{2}$ is total strain amplitude, $\frac{\Delta {\epsilon }_p}{2}$ is plastic strain amplitude, $\frac{\Delta {\epsilon }_e}{2}$ is elastic strain amplitude, $2N_f$ is the number of cycles to failure, ${\epsilon }_f^{\prime }$ and ${\sigma }_f^{\prime }$ are the fatigue ductility and fatigue strength coefficients, respectively, and c and b are ductility and strength exponents. The fitting curves of the IN792 superalloys with two different grain sizes LCF tested at 700 °C and 800 °C are shown in Figure 7, and the parameters in the Coffin–Mansion relationship are indicated in

Table 3. Parameters in the Coffin–Mansion relationship of IN792 superalloys with different grain sizes under different LCF temperatures.

	${\mathit{\sigma }}_{\mathit{f}}^{\prime }$	b	${\mathit{\epsilon }}_{\mathit{f}}^{\prime }$	c
FG-700 °C	1710	0.114	0.238	0.912
CG-700 °C	1568	0.110	0.085	0.901
FG-800 °C	1524	0.099	0.742	1.188
CG-800 °C	1423	0.110	0.503	1.285

. It can be found that the grain refinement increased all the parameters when LCF tested at 700 °C, which means that both the LCF strength and deformation resistance is improved. For LCF tests at 800 °C, the grain refinement increased the fatigue ductility and strength coefficient, but slightly decreased the ductility and strength exponent. Therefore, increasing the temperature weakened the LCF property improvement of IN792 superalloys caused by grain refinement.

The surface of the LCF fractured specimens were observed through SEM and the results are shown in Figure 8. Basically, two different fracture modes are found for the IN792 superalloys in the present study, and the fracture mode changes with the applied total strain amplitude. When the total strain amplitude is low, such as 0.004 or 0.005, the fatigue crack mainly initiates from the porosities near the specimen surface, and then propagate towards the specimen interior transgranularly, as shown in Figure 8a,b,e and 8f. The crack extension path is flat and perpendicular to the cyclic stress direction, and the river-like patterns exhibit the expansion direction of the crack. According to our previous study [10], the porosities near the sample surface are more likely to incubate a crack under HCF load. Therefore, the LCF fracture mode of IN792 superalloys at a low total strain amplitude is similar to HCF fracture. Meanwhile, when the total strain amplitude is high, such as 0.006 or 0.008, the fatigue life is rather short, and the fatigue crack are more likely to produce in the center of the specimen and then expand around transgranularly. The crack extension path is rough with obvious dendritic characteristics, indicating that the crack expands along the interdendritic region. The LCF fracture mode of IN792 superalloys at a high total strain amplitude is similar to the tensile fracture mode, as demonstrated in our previous study of the tensile properties of IN792 superalloys [29].

3.4. Microstructure of Fractured Specimens

After LCF tests, the fractured specimens were cut up along the longitudinal section, and the microstructures near the fracture surface were observed through SEM. It was found that the when the total strain amplitude is low, the specimen bears relatively low cyclic stress, the MC carbides would not break and produce cracks and the grain boundaries would not crack whether LCF tested at 700 °C or 800 °C, as shown in Figure 9a,d. However, when the total strain amplitude is high, the cyclic stress that the specimen bears is high; thus, the MC carbides would break and become crack initiate sites, as indicated in Figure 9b,e. The grain boundary M₅B₃ borides maintain a fine granular shape, and no obvious differences are found compared from the before tests, regardless of the testing temperature and applied total strain amplitude in the present study, as in Figure 9c,f. Therefore, the M₅B₃ borides could play a grain boundary pinning role during LCF tests under 700 °C and 800 °C, which would hinder the grain boundary cracking. As a result, the grain boundary could keep good structure stability and high strength during LCF tests at 700 °C and 800 °C. As a result, the increase in grain boundary content through grain refinement could improve the LCF property of this superalloy.

As the main strengthening phase of superalloy, γ’ phase would evolve during service of superalloy under high temperature, which could affect the deformation resistance of superalloy. The average size of primary γ’ phase after LCF tests under different conditions is measured through the area method, and the results are shown in Figure 10. It can be found that the γ’ phase would grow larger gradually during LCF tests, and the lower the total strain amplitude, the longer the fatigue life and the larger the γ’ phase size after LCF tests. Comparing Figure 10a,b, there is no significant difference in the size evolution of γ’ phase of FG alloy and CG alloy during LCF tests. Moreover, as the testing temperature rises from 700 °C to 800 °C, the γ’ phase size after LCF tests would increase slightly.

3.5. Dislocation Structure after LCF Tests

The dislocation structures of IN792 superalloys after LCF tests were observed through TEM to analyze the deformation mechanism, and the results are revealed in Figure 11. Since the γ’ phases of CG and FG alloys do not show differences, their dislocation structure is also the same. When the applied total strain amplitude is relatively low, the stress that the superalloy bears is low. The dislocations could only slip in the γ channel between γ’ phases, and no stacking fault was found in γ’ phases, which means that there is not enough shear stress for dislocations to shear the γ’ phases, and the dislocations would accumulate at the interface of γ/γ’ phase, thus forming dislocation networks, as indicated in Figure 11a. However, as the applied total strain amplitude increases to 0.006 and 0.008, stacking faults appear in the primary γ’ phases, as can be seen in Figure 11b, which implies that the $\frac{a}{2}<1\overline{1}0>$ dislocations could dissociate at γ/γ’ interface, creating two partial dislocations according to the following reaction [30]:

$$\frac{a}{2}<1\overline{1}0>\to \frac{a}{3}<1\overline{2}1>+SISF+\frac{a}{6}<11\overline{2}>$$

where SISF is superlattice intrinsic stacking fault. The $\frac{a}{3}<1\overline{2}1>$ partial dislocation could shear the primary γ’ phases, and SISF is left in the primary γ’ phases. Moreover, the dislocations are quite curved because they would bypass the fine secondary γ’ phases through the Orowan mechanism. Some Orowan loops can be found around the secondary γ’ phases, as shown in Figure 11c. When the LCF testing temperature rises to 800 °C, the dislocation structure morphology is similar to that of 700 °C under low total strain amplitude, and the γ channel is filled with dislocation networks, and no stacking fault is formed, as indicated in Figure 11d. Under high total strain amplitude, besides the stacking faults in primary γ’ phases, Orowan loops are also found around the primary γ’ phases, as revealed in Figure 11e. Therefore, the dislocations would interact with the primary γ’ phases through two ways: shearing and Orowan bypass mechanism when the LCF testing temperature is 800 °C and the total strain amplitude is relatively high. In addition, for the fine secondary γ’ phases, the dislocations would also bypass them through Orowan mechanism, as indicated in Figure 11f.

4. Discussion

4.1. The Cyclic Stress Response Behavior of IN792 Superalloy

The cyclic stress response behavior is always explained by the dislocation movement and interaction between dislocations and precipitates [31,32,33,34]. It is generally believed that at the beginning of fatigue loading, dislocations start to multiply, and the precipitates would block the dislocation movement, thus causing cyclic hardening. Under a low total strain amplitude, the above analysis has shown that a large number of dislocation networks are formed in the interface of γ/γ’ phases, which would decrease the coherence of the interface and result in fatigue softening. Moreover, when the total strain amplitude is low, the fatigue life is long, and the primary γ’ phases grow large after LCF tests, as shown in Figure 10. It has been reported [33] that the coarsening of γ’ phases would cause a reduction in coherent interfaces, thus lead to a softening behavior. As a result, the softening effects brought by dislocation networks and coarsening of primary γ’ phases would counteract the hardening effect, thus creating a stable stress response behavior after dozens of loading cycles, as illustrated in Figure 5a,b. In addition, there are a lot of dislocations that accumulate at the grain boundary, as in Figure 11d, which proved that the grain boundary could block dislocation movement [9,35,36]. The grain refinement increased the grain boundary content of the IN792 superalloy and brought greater hindrance to the dislocation movement, and therefore, the stress amplitude of FG alloys is higher than CG alloys, as demonstrated in Figure 5.

When the total strain amplitude increases to 0.006, the dislocation could shear primary γ’ phases, as exhibited in Figure 11b,e. The shearing of γ’ phases could lead to resistance to dislocation movement, thus increasing the stress amplitude during LCF tests. Therefore, the IN792 superalloys show a continuous cyclic hardening response, as shown in Figure 5c. However, when the total strain amplitude continues to increase to 0.08, a short stable period appears at the end of the cyclic stress response curves. Because the cyclic stress amplitude would rapidly rise to a high value, lots of primary γ’ phases would be sheared and the order of primary γ’ phases is reduced, which could decrease the strengthening effects of the superalloy and cause a softening effect on the superalloy [33].

4.2. The Effect of Grain Refinement on the LCF Property and Fracture of IN792 Superalloy

According to microstructure observation, the grain refinement of IN792 superalloys through reducing the melting temperature and pouring temperature not only caused increased grain boundary contents, but also the refining of MC carbides, eutectic structures and dendritic structures. The γ’ phases are not refined because they are reprecipitated during the heat treatment process, and the same heat treatment process is employed for CG and FG alloys. As for fracture surface observation, the LCF fracture mode of IN792 superalloys in the present research is all transgranular. The microstructure of the longitudinal section of LCF fractured specimens show that there is no crack formed at grain boundary. The fine granular M₅B₃ borides dispersed at grain boundary are very stable during the whole LCF process, which would play a pinning and strengthening role in the grain boundary and prevent it from cracking. Therefore, it can be deduced that the grain boundary strength is higher than the grain interior under the present test conditions. The refining of grains could increase the grain boundary contents, and improve the overall strength and crack growth resistance of IN792 superalloys.

As determined in our previous study [10], the porosities near the sample surface are major HCF crack initiation sites of IN792 superalloys because they could cause stress concentration in the surrounding areas. The LCF fracture mode under low total strain amplitude is similar to HCF regime. Thus, the size and distribution of porosities is very important to the LCF properties. The casting defects observation of CG and FG alloys proved that even though the reducing the melting and pouring temperature could reduce the mobility of the alloy melt and improve the porosity formation tendency, the porosities near the specimen surface does not show much difference, as indicated in Figure 4. The porosities near the center of the specimen would not cause fatigue fracture in the present study; therefore, the increase in porosity content for FG alloy does not show significant influence on the LCF properties of IN792 superalloys.

It has been reported [37,38,39,40] that MC carbides distributed at the interdendritic region and grain boundary could strengthen the superalloy. However, as a microstructure heterogeneity which is incoherent with matrix, it would also cause cyclic plastic strain localization and crack during fatigue tests. The refining of MC carbides could decrease the surrounding cyclic plastic strain localization and thus decrease the crack formation tendency. In addition, the fracture surface observation has shown that the fatigue crack would propagate along interdendritic region under a high total strain amplitude. Since the grain refinement has refined the interdendritic region, the crack propagation would encounter larger hindrance, which would contribute to a longer fatigue life. The refined eutectic structure of FG alloys could also decrease the crack growth tendency because eutectic structure has a relatively low strength. In conclusion, the refinement of MC carbides, eutectic structures and dendritic structures caused by grain refinement could also contribute to the improvement of LCF properties of IN792 superalloy.

5. Conclusions

In this study, IN792 superalloys with two different grain sizes were manufactured through different melting and pouring temperatures, and their microstructures are charactered and LCF properties are tested under 700 °C and 800 °C. The following results are obtained:

(1)

Through decreasing melting and pouring temperatures, the grains, MC carbides, eutectic structures and dendritic structures are refined simultaneously, but the primary and secondary γ’ phases stay consistent due to the same heat treatment process.

(2)

The LCF properties of 700 °C and 800 °C are optimized under four different total strain amplitudes by grain refinement.

(3)

The LCF fracture mode is related to the applied total strain amplitude. Under low total strain amplitude, the fatigue cracks mainly initiate at the porosities near the specimen surface, while under high total strain amplitude, the fatigue cracks tend to form at the center of the specimen, and propagate along interdendritic regions.

(4)

When the total strain amplitude is low, the dislocations could move in the γ channel and form dislocation networks. When the total strain amplitude is high, the dislocations could shear primary γ’ phases and form stacking faults.

(5)

The results obtained in the present study could provide theoretical guidance for improving the service performance of IN792 superalloys.