Table of Contents
Journal of Metallurgy
Volume 2014, Article ID 972917, 7 pages
http://dx.doi.org/10.1155/2014/972917
Research Article

Closed Die Hammer Forging of Inconel 718

1Materials and Mechanical Entity, Vikram Sarabhai Space Centre, Trivandrum 695 022, India
2Human Spaceflight Project, Vikram Sarabhai Space Centre, Trivandrum 695 022, India

Received 26 July 2014; Revised 6 November 2014; Accepted 10 November 2014; Published 1 December 2014

Academic Editor: Elena V. Pereloma

Copyright © 2014 S. Chenna Krishna et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

Abstract

A method for the production of Inconel 718 (IN-718) hemispherical domes by closed die hammer forging is proposed. Different combination of operations employed for production are as follows: (i) preforging + final forging + air cooling, (ii) preforging + final forging + controlled cooling, (iii) direct forging + controlled cooling, and (iv) direct forging + air cooling. Last three combinations yielded a crack free hemispherical dome. The forged hemispherical domes were solution annealed at 980°C for 1 h and air cooled. The grain size of the domes at all locations was finer than ASTM No 4. Mechanical properties of the forged dome in solution treated and aged condition (STA) were better than feedstock used.

1. Introduction

Inconel 718 (IN-718) is a widely used age-hardenable nickel based superalloy for high temperature applications. In addition, it is also being used for fabrication of gas bottles for storage of high pressure oxygen for space missions. The rationale for selecting IN-718 for oxygen storage is discussed in literature [1, 2]. Realization of gas bottles for oxygen storage involves joining two hemispherical domes by welding. Hemispherical domes can be produced by closed die hammer forging or press forging. In the present study, closed die hammer forging was employed due to nonavailability of large press. Even though published work is available on development of large forgings, it is mostly confined to processing using press [35]. There are no reports on production of IN-718 hemispherical domes by closed die hammer forging or press forging in open literature. Nevertheless, the forging temperature for IN-718 processed by different technique is well documented in the literature [69]. To a larger extent, IN-718 is being hot worked in the temperature range of 980–1120°C [8, 9]. In the present study a forging temperature of 1050°C, which is above solvus of delta phase, was chosen. Through this work, effort has been made to produce IN-718 hemispherical domes by closed die hammer forging.

2. Material and Method

The material used in the present work was   200 mm × 40 mm (height) disc of Inconel 718 produced by VIM + VAR process. The chemical composition of the alloy in wt.% is 53.1Ni-18Cr-5.15(Nb+Ta)-3.02Mo-0.5Al-0.92Ti-0.08Co-0.05C-0.2Mn-0.004B-0.04Cu-Bal(Fe). Different operations employed in deformation processing of hemispherical domes include preforging, final forging, controlled cooling, and air cooling. Both of the forging operations were performed by soaking the job at 1050°C and finish temperature was maintained above 980°C. Finish forging temperature was monitored using an optical pyrometer. Preforging was an upsetting operation involving a reduction in the height of the disc from 40 to 23 mm between flat dies using a 6 T hammer. Final forging involved realization of a hemispherical dome of 15 mm thickness by closed die hammer forging using a 10 T hammer. The process parameters, lubricants, and equipment used for preforging and final forging are given in Table 1. Prior to forging, the work piece was heated in an electric furnace with an accuracy of ±5°C. The dies for forging were heated to 350°C using a gas-fired flame. Different types of combinations employed in the study are given in Figure 1. Controlled cooling involved loading of the forged dome into a furnace set at 600°C and cooling it to 200°C by switching off the furnace. Effect of solution treatment temperature on the tensile properties and microstructure was studied in the temperature range of 900–1050°C to select the optimum cycle for post-heat treatment of the forged dome.

tab1
Table 1: Process parameters and equipment used for forging.
972917.fig.001
Figure 1: Different processing sequence employed in the study.

All the samples were conventionally polished and electrolytically etched with 10% oxalic acid to reveal the grain structure. The microstructure of the alloy was examined with an optical light microscope (make: OLYMPUS GX-71) and scanning electron microscope (make: CARL ZIESS Evo-50) equipped with OXFORD makes energy dispersive X-ray spectroscopy (EDS). The conditions used for EDS analysis are EHT voltage, 20 kV, and probe current, 600 pA. The grain size was determined by a linear intercept method using IMAGEJ image analysis software. Tensile test was conducted on the round subscale specimen (25 mm GL) using an INSTRON 5500R UTM at a nominal strain rate of 0.001 s−1 in both solution treated (ST) and solution treated and aged (STA) condition. Specimens were solution treated at 980°C for 0.5 h followed by air cooling and aged at 720°C for 8 h followed by furnace cooling to 620°C and soaking for 8 h followed by air cooling.

3. Results and Discussion

3.1. Forging

The process employed for realization of the hemispherical domes is shown in Figure 1. The first process was designed based on our previous experience with closed die hammer forging of Ti-5Al-2.5Sn alloy [10]. In process-1 (P1), the input material of 200 mm diameter and 40 mm height (disc) was upset to a height of 23 mm with a diameter of 263 mm. This preform was forged in shaped die to produce a 15 mm thick hemispherical dome as shown in Figure 1. The as-forged dome was transferred from the die and cooled in air. Upon visual inspection, the forging showed free surface cracks. These cracks could be removed by machining the surface. Such forgings will not be rejected because of free surface cracks, but often machining is required to achieve good surface finish. Hence, defect-matrix developed by Arentoft and Wanheim [11] for forging was employed to understand the reason for formation of defects and ways to eliminate them. Table 2 gives defect-matrix for the present process with possible reasons for free surface cracks, with defects in the column and causes in the row. However, the defects and the causes given are limited to this method and will be studied. The symbol “X” in the table indicates the relation between cause and defect. The possible reasons for formation of free surface cracks may be too high friction, fast cooling, low/high temperature, and improper height ()/diameter () ratio. In the present study, friction was reduced by providing sufficient lubrication between die and job by using colloidal graphite. Hence, too high friction is of no concern.

tab2
Table 2: Defect-matrix for the forging process [10].

In this work, material to be forged (Inconel 718) and tools to be used (die design and material) are predetermined. Therefore, efforts were directed towards modification of the preform and process. Under the process, the causes of surface cracks can be fast cooling. The cooling rate has been modified from air cooling as it is in P1 to controlled cooling in process-2 (P2). This modification has yielded a crack free forging. It is well established that residual stresses are induced during the hammer forging process and based on the preform shape and size additional localized stresses may be induced. If the stress reaches a threshold level and sufficient time is not provided for relieving the stress, it may result in free surface cracking as observed in P1. By controlled cooling in furnace sufficient time and temperature are provided for stress relieving yielding a crack free dome.

Further in process-3 (P3), the concern of an improper height/diameter () ratio has been addressed. The process adopted involved direct forging to realise a dome avoiding preforging. A defect-free dome realised through P3 was in agreement with Arentoft and Wanheim [11] that lower ratio was improper selection for the present method. The ratio for disc and preform were 0.2 and 0.08, respectively. Lower ratio (0.08) will result in severe bending of the job followed by flow of the material along the lower die to form a hemisphere. In the case of 0.2  ratio, sufficient height is available for filling the die cavity and enabling the flow of the material without any bending stresses being induced. Preform design and controlled cooling were effectively used in P3 to avoid surface cracking. However, controlled cooling is not economical and industrially feasible. Keeping this in mind, an attempt was made to design process-4 (P4) which can meet above requirements and could be scaled up. This process involved direct forging followed by air cooling. The forged dome was free of surface cracks. All the forged domes were subjected to dye-penetrant test and ultrasonic inspection after solution annealing and proof machining, and no recoverable indications were observed. From the above discussion using defect-matrix, it may be ascertained that improper selection of preform is the primary reason for free surface cracking. Nevertheless, some additional numerical simulation of the process may be necessary in order to verify the output from the defect-matrix.

3.2. Selection of Solution Annealing Temperature

The microstructure of the solution treated sample at 900°C consisted of fine equiaxed grains decorated with grain boundary delta phase and MC type primary carbides [1214]. Delta phase has composition of Ni3Nb with orthorhombic crystal structure. It forms above 700°C and has solvus around 1000°. It is reported that rate of formation of delta phase is maximum at 900°C [15, 16]. Azadian et al. [16] reported that delta phase nucleates at the grain boundaries followed by growth of needles extending into the grains. Carbides were observed at the grain boundary and occasionally within the grains as indicated by arrows in Figure 2(a). Further, increase in the solution treatment temperature (940–980°C) has resulted in the decrease in the volume fraction of the delta phase as shown in Figures 2(b) and 2(c). Complete dissolution of delta phase and grain growth was observed at 1050°C as shown in Figure 2(d). Nevertheless, primary carbides were not affected by high temperature solution treatment (1050°C). Figure 3 shows the SEM micrographs of the solution treated samples at 900 and 1050°C. The typical features in 900°C (ST) were needle shaped phase along the grain boundary and large carbides at the grain boundaries as shown in Figure 3(a). At 1050°C (ST), the grain boundaries were free of any phase, but the carbides distribution was unaltered as shown in Figure 3(b). The energy dispersive X-ray spectroscopy (EDS) spectra obtained using quantitative method from the grain boundary phase and carbide are shown in Figures 3(c) and 3(d), respectively. The EDS spectrum in Figure 3(c) shows prominent peaks of Ni and Nb along with Fe and Cr. Considering the size of the analysed phase (≈1 μm in thickness), the additional peaks of Fe and Cr may be due to contribution of the matrix. From the morphology (needle shape) and EDS spectrum of the phase, the possible phase can be Ni3Nb. The EDS spectrum from the large particle displays prominent peaks of Nb along with Ti confirming the carbides are rich in Nb and Ti. It can be presumed from the shape, size, and EDS spectrum that large particles are (Nb,Ti)C. The observations made are in agreement with the earlier works on Inconel 718 [1417].

fig2
Figure 2: Effect of temperature on the optical micrographs in solution treated condition: (a) 900°C, (b) 940°C, (c) 980°C, and (d) 1050°C.
fig3
Figure 3: SEM micrographs and corresponding EDS spectra from the solution treated samples. (a) SEM micrograph of ST-900°C sample, (b) SEM micrograph of ST-1050°C sample, (c) EDS spectrum from spot-1 in (a), and (d) EDS spectrum from spot-2 in (a).

Tensile properties of the alloy subjected to solution treatment at different temperature and aged as per standard cycle are shown in Figure 4. The tensile properties in the temperature range of 900–980°C were in the range of 1426–1467 MPa (ultimate tensile strength), 1216–1241 MPa (yield strength), and 23.3–23.8% (elongation). At 1050°C, the ultimate tensile strength and yield strength decreased to 1252 MPa and 975 MPa, respectively, with improvement in ductility (31%). The decrease in strength is attributed to dissolution of delta phase and grain coarsening as seen in Figures 2(d) and 3(b). From the optical and SEM micrographs and tensile properties, solution treatment at 980°C was selected as appropriate temperature because of combination of strength and lower volume fraction of delta phase. The deleterious effect of delta phase on the high temperature mechanical properties and room temperature ductility is reported in literature [1519].

972917.fig.004
Figure 4: Influence of solution treatment temperature on the tensile properties of Inconel 718 after aging.
3.3. Microstructure of Solution Annealed Dome

Figure 5 shows the microstructure of the disc ( 200 mm) used in the present study. It has been observed that microstructure had fully recrystallised equiaxed grains with a mean grain size of 88 ± 10 μm. Figure 6 shows the microstructure of the dome forging at three locations after solution treatment. At the top of the dome, the microstructure appears to be recrystallised and has relatively larger grains, which have undergone recovery as shown in Figure 6(a). The grain size was measured to be 62 ± 10 μm. The extent of recrystallisation mainly depends on total strain, strain rate, and temperature [10]. Therefore, it can be assumed that “necklace” recrystallisation observed at the top of the dome may be attributed to lower deformation and die chilling. However, it was reported that such limited or partial recrystallised structure does not affect the mechanical properties (tensile and fatigue) [3]. The midportion of the dome had slightly elongated grains with the remains of some large recovered grains as shown in Figure 6(b). The elongated grains also indicate that the flow of material was along the wall of the shaped die. This is the portion of the dome, which experiences maximum deformation. Bottom of the dome had fully recrystallised structure with annealing twins, and grain size was 52 ± 12 μm as shown in Figure 6(c). This portion of the dome experiences moderate deformation and low die chilling allowing complete recovery and recrystallisation. The grain size of the dome taken at different locations was found to be finer than ASTM No. 4.

972917.fig.005
Figure 5: Optical micrograph of the Inconel 718 disc used for forging.
972917.fig.006
Figure 6: Optical micrographs of Inconel 718 of dome forging after solution treatment: (a) top of the dome, (b) mid-portion of the dome, and (c) bottom of the dome.

3.4. Mechanical Properties of Solution Treated and Aged Dome

Prior to tensile testing, specimens were solution treated and aged. Properties of the disc and dome forging are given in Table 3. The yield strength (YS) and ultimate tensile strength (UTS) of the disc were 839 MPa and 1111 MPa, respectively, in solution treated (ST) condition. They increased to 1154 MPa (YS) and 1312 MPa (UTS) after aging treatment. The dome has shown improved properties compared to the disc because of mechanical working that occurred during forging with an average value of 1210 MPa (YS) and 1362 MPa (UTS). However, better mechanical properties and fine microstructure can be achieved by lowering the forging temperature [8].

tab3
Table 3: Typical mechanical properties of the disc and forged dome.

4. Conclusions

To summarise, closed die hammer forging can be employed for production of 200 mm hemispherical domes of Inconel 718. Defect-matrix was employed to overcome the free surface cracking observed in the forged dome. Post-solution annealing temperature for the domes was selected as 980°C, considering good tensile properties, fine grains, and lower content of delta phase. Solution annealed dome showed non-uniform microstructure: partially, recrystallised grains at the top, fully, recrystallised grains with annealing twins at the bottom, and fine elongated grains at the midportion of the dome. Grain size of the hemispherical dome at all locations was finer than ASTM No. 4 and tensile properties of forged dome were better than the feedstock used for forging.

Conflict of Interests

The authors declare that there is no conflict of interests regarding the publication of this paper.

Acknowledgment

The authors would like to express sincere gratitude to Director of VSSC for his kind permission to publish this work.

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