• Transactions of the Korean Society of Mechanical Engineers A
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• v.34 no.12
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• pp.1909-1915
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• 2010

The material properties of gas turbine components change during the daily start/stop thermal cycle because of exposure to the hot combustion gas. Recently, single-crystal Ni-based superalloys have been used to manufacture many hot-gas components for gas turbines. However, the user needs to depend on the manufacturer for maintenance issues because of the lack of data required for predicting blade life and material degradation. In this study, we investigate the time-dependent degradation of first-stage blades at various operating facilities to collect the basic data for life assessment and damage analysis. The blade material is a single-crystal Ni-based superalloy, CMSX-4, and the EOH (equivalent operating hours) are 25,000 and 52,000, respectively. We prepared the test specimen directly from used blades and carried out mechanical tests and microstructural observations.

• Journal of Korea Foundry Society
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• v.42 no.3
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• pp.153-160
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• 2022

The effect of thickness on the microstructure and the mechanical properties of centrifugal cast 625 was investigated. Centrifugal cast 625 with various thickness of 10, 17 and 50mm showed partially columnar grained structure 8, 12.3 and 18.5mm respectively from the outer surface. Secondary dendrite arm spacing in the columnar grains slightly increased with increasing casting thickness. Tensile strength of the columnar region was similar regardless of casting thickness. Solidification behavior of the columnar grained region is similar to that of directional solidification, thus solidification rate in the centrifugal cast tube was extrapolated from the secondary dendrite arm spacing data of the directionally solidified material. The equiax grained region formed interior of the thick castings. The tensile strength of the equiaxed region showed the average value of the columnar region which is presumably originated from the grain structure rather than secondary dendrite arm spacing.

• Proceedings of the Korean Institute of Surface Engineering Conference
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• 2013.05a
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• pp.100-101
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• 2013

가스 터빈, 석유 화학 공장 등에 널리 사용되고 있는 합금들은 IGCC 분위기에서 심각한 부식이 야기된다. 특히 고온에서 가스터빈 재료로 사용되는 초내열 합금 등도 열악한 고온 황화분위기에서는 열악한 내부식성을 보였다. 따라서 이러한 조건에서 견딜 수 있는 재료의 개발이 필요하다. 일반적으로 알려진 내부식성 증가 방법은 내부식성 합금원소 첨가와 재료 표면에 직접 코팅을 하는 방법이 있으며, 본 연구에서는 고온의 $H_2S$ 가스 분위기에서 Pack cementation으로 Al과 Cr 확산코팅 시킨 시편을 이용하여 부식실험을 실시하여 부식 특성을 살펴보았다.

• Korean Journal of Materials Research
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• v.11 no.6
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• pp.502-507
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• 2001

The effect of solidification rate on the microstructure of directionally solidified IN792+ Hf superalloy has been studied. Solidification sequence and precipitation behavior of the alloy have been analysed by microstructural observation. The script carbide transformed to faceted carbide with decreasing solidification rates. The incorporation of ${\gamma}$ phase into the faceted carbide was due to dendritic growth of carbides. Some elongated carbide bars formed along the grain boundaries at a solidification rate of 0.5$\mu\textrm{m}$/s. Two zones, ${\gamma}$' forming elements enriched zone and depleted zone, were found in the residual liquid area. Eutectic ${\gamma}$/${\gamma}$' nucleated in the f forming elements enriched zone. Formation of eutectic ${\gamma}$/${\gamma}$' increased the ratio of (Ti+Hf+Ta+W)/Al and induced η phase precipitation. The ratio of (Ti+Hf+Ta+W)/Al decreased at lower solidification rates due to sufficient back diffusion in the residual liquid area. Hence, the Precipitation of the η Phase efficiently suppressed at the lower solidification rate.

• Journal of Powder Materials
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• v.20 no.6
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• pp.487-493
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• 2013

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.248-250
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• 2017

The Mar-M-247 alloy is one of the most widely used materials for gas turbine components in aerospace filed and it shows excellent high temperature strength properties. Hot section parts, such as turbine nozzle and blade, are difficult to manufacture because of their complicated shape. So, the joining process usually applies to them. In this study, the high-temperature behavior of Mar-M-247 alloy at liquid diffusion bonding was investigated. Thus, we performed the diffusion bonding at $1,121^{\circ}C$ for 7 minutes, and observed changes in high temperature strength. As a result, the strength of the bonded specimens decreased by about 70% at $649^{\circ}C$, 60% at $825^{\circ}C$, and 45% at $1,000^{\circ}C$ compared to the base metal. As a result of observing the strength change with bonding time, the specimen bonded for 720 minutes showed a similar strength with the base metal at $649^{\circ}C$. Inferring this result, the joint is considered to be the one-body part.

• Korean Journal of Materials Research
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• v.3 no.6
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• pp.575-584
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• 1993

The effects of atmosphere on the creep rupture properties of Ni-base superalloy Ren6 80 were investigated. Creep rupture tests were performed at $760^{\circ}C$, 657MPa and 982%, 157MPa under Ar gas atmospheres. Creep rupture mode and rupture properties (rupture life and elongation) were similar in two different atmospheres under the condition of $760^{\circ}C$, 657MPa. However, the results at $982^{\circ}C$, 157MPa showed different creep rupture mode and life between air and Ar gas atmospheres. In air, it was shown that creep cracks were initiated at surface-exposed grain boundaries and propagated along grain boundaries. In Ar gas atmosphere, the cracks were initiated at inner grain boundaries and coalesced to surface cracks which cause cup-and-cone type fracture. Due to protective oxide layer formation, air test showed longer rupture life than Ar test.

• Resources Recycling
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• v.24 no.5
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• pp.56-62
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• 2015

Solvent extraction experiments for the separation and recovery of Re from hydrochloric acid leaching solution of spent super alloy by Alamine 304-1 were carried out. The effects of some variables, such as the nature and concentration of the extractants, HCl concentration, and the presence of impurities were investigated. The synthetic solutions of Re were prepared by dissolving ammonium perrhenate (APR), Alamine304-1, Cyanex272 and $D_2EHPA$ were used solvent extractants distilled in kerosene. The extraction percentage of Re by Alamine304-1 was higher than the other extractants as Cyanex272 and $D_2EHPA$ and the percentage is about 99%. Only 99% of Re was extracted in the presence of Al, Co and V in HCl solution.

• Korean Journal of Materials Research
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• v.10 no.2
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• pp.128-137
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• 2000

A study has been made to investigate the effects of hot isostatic pressing(HIPing) on the microstructure and high temperature fatigue lives of the IN738LC, Ni-base superalloy used in turbine blades, with emphasis on the elimination of casting microporosity and fatigue damage through HIP treatments. Microstructure was observed using OM, SEM and the fatigue life was investigated with rotate bending fatigue tester. The results show that the fatigue lives of properly HIP-processed specimens could be extended be extended by a factor of about sixty. In contrast, no comparable life improvement was achieved with heat treatment only. The repetitive HIP treatment was shown to be very effective as a means of rejuvenating the fatigue life of intentionally fatigue-damaged IN738LC by restoration of the initial alloy microstructure and additional removal of fine casting defects which remained in the HIP-processed material.

• Transactions of Materials Processing
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• v.22 no.5
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• pp.258-263
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• 2013

The deformation behavior of NIMONIC 80A was studied in the high temperature range of $900{\sim}1200^{\circ}C$ and for strain rates varying between 0.02 and $20s^{-1}$ via the hot compression test. Processing maps for hot working were constructed on the basis of the power dissipation efficiency using a dynamic material model. The results showed that the strength during hot compression increased with increasing strain rate and decreasing temperature. At low strains, the processing map of NIMONIC 80A did not reveal any instability domain regardless of the strain rate and temperature. However, at high strains, the processing map exhibited an instability domain at a low strain rate of $0.2s^{-1}$ and within a temperature range of $900{\sim}960^{\circ}C$. In the instability domain, the deformed microstructure exhibited shear bands and carbide precipitation while, in the safe domain, full recrystallization occurred.