• 한국재료학회지
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• 제15권1호
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• pp.19-24
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• 2005

For the good combination of high-temperature strength, toughness and creep property, $9-12\%$ chromium steels are often used for gas turbine compressors, steam turbine rotors, blade and casing. In this study, the correlation of microstructural evolution and mechanical properties was investigated fur the specimens heat-treated at 600, 650 and $700^{\circ}C$ for 1000, 3000 and 5000 hrs. The microstructure of as-received specimen was tempered martensite with a high dislocation density, small sub-grains and fine secondary phase such as $M_23C_6$. Aging for long-time at high temperature caused the growth of martensite lath and the decrease of dislocation density resulting in the decrease in strength. However, the evolution of secondary phases had influence on hardness, yield strength and impact property. In the group A specimen aged at $600^{\circ}C\;and\;650^{\circ}C$, Laves phase was observed. The Laves phase caused the increase of the hardness and the decrease of the impact property. In addition, the abrupt growth of secondary phases caused decrease of the impact property in both A and B group specimens.

• 대한기계학회논문집B
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• 제31권7호
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• pp.628-634
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• 2007

The present study investigated the heat/mass transfer characteristics in an equilateral triangular channel simulating the leading edge cooling passage in gas turbine blade. Using naphthalene sublimation method and pressure measurement experiments, local mass (heat) transfer and pressure coefficients were obtained. The experiments were conducted with three rotating numbers between 0.0 and 0.1; two channel orientations of $0^{\circ}$ (model A) and $30^{\circ}$ (model B); the fixed Reynolds number of 10,000. The results showed that the channel rotation caused the heat transfer discrepancy between suction and pressure sides. Due to the secondary flow induced by Coriolis force, the high heat transfer appeared on the pressure side. When the channel orientation was $30^{\circ}$ (model B), the secondary flow caused the more uniform heat transfer distribution among leading edge and inner wall on pressure side than that of the model A.

• 대한기계학회논문집A
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• 제32권7호
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• pp.569-575
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• 2008

In this study, disk type of thermal barrier coating system for gas turbine blade was isothermally aged in the furnace changing exposure time and temperature. For each aging condition, bond tests for three samples were conducted for evaluating degradation of adhesive or cohesive strength of thermal barrier coating system. For as-sprayed condition, the location of fracture in the bond test was in the middle of epoxy which have bond strength of 57 MPa. As specimens are degraded by thermal aging, bond strength gradually decreased and the location of failure was also changed from within top coat at the earlier stage of thermal aging to the interface between top coat and TGO at the later stage due to the delamination in the coating.

• 한국유체기계학회 논문집
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• 제17권3호
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• pp.59-64
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• 2014

The kidney vortex is the important factor adversely influencing film cooling effectiveness. In general, double jet film-cooling hole is designed to overcome the kidney vortex by generating anti-kidney vortices. In this study, the film cooling characteristics and the effectiveness of the double jet film cooling hole were numerically investigated with various area ratios of the first($A_1$) and second($A_2$) cooling hole($A_1/A_2$=0.8, 1.0, 1.25) and lateral ejection angle(${\alpha}$ = $30^{\circ}$, $45^{\circ}$, $60^{\circ}$) as the design parameters. The effects of lateral distance between the first and second row holes are investigated. Numerical study was performed by using ANSYS CFX with the shear stress transport(SST) turbulence model. The film cooling effectiveness and temperature distribution were graphically depicted with various flow and geometrical conditions.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2003년도 춘계학술대회
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• pp.1453-1460
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• 2003

The present study investigates the effects of rib arrangements and aspect ratios of a rectangular duct simulating the cooling passage of a gas turbine blade. Two different V-shaped rib configurations are tested with the aspect ratios (W/H) of 3 to 6.82. One is the continuous V-shaped rib configuration with $60^{\circ}$ attack angle, and the other is the discrete V-shaped rib configuration with $45^{\circ}$ attack angle. The square ribs with the pitch to height ratio of 10.0 are installed on the test section in a parallel arrangement for both rib configurations. Reynolds numbers based on the hydraulic diameter are changed from 10,000 to 30,000. A naphthalene sublimation method is used to measure local heat/mass transfer coefficients. For the continuous V-shaped rib configuration, two pairs of counter-rotating vortices are generated in a duct, and high transfer region is formed at the center of the ribbed walls of the duct. However, for the discrete V-shaped rib configuration with $45^{\circ}$ attack angle, complex secondary flow patterns are generated in the duct due to its geometric feature, and more uniform heat/mass transfer distributions are obtained for all tested cases

• 한국항공우주학회지
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• 제50권7호
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• pp.465-470
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• 2022

본 논문은 알루미늄 6061의 고속 충격 해석과 고속 충격 시험 결과를 비교 검증하여 금속 재료의 고속 충격에 의한 거동 특성을 연구하였다. 고속 충격 해석을 위해 만능재료시험기를 이용한 준정적 시험과 Hopkinson bar를 이용한 동적 시험을 통해 Huh-Kang 모델과 Johnson-Cook 파손 모델의 계수를 구했다. LS-DYNA 프로그램 해석을 이용하여 관통 속도와 형상을 결과로 예측했고 고속 충격 시험기를 이용한 시험 결과와 비교하였다. 이를 바탕으로 항공기 가스터빈 엔진 블레이드 컨테인먼트 평가 연구에 적용하고자 한다.

• 한국추진공학회지
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• 제3권4호
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• pp.67-74
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• 1999

고체 물체 표면이나 지표면에 초음속 제트가 충돌할 때 발생되는 문제들은 다단 로켓의 분리, 우주공간에서의 도킹, 수직 이/착륙기, 제트 엔진의 배기가스, 가스터빈 블레이드, 지상 로켓 발사 등의 다양한 상황에서 일어나며 이러한 충돌제트의 유동은 아음속과 초음속 혼합영역, 충격파가 교차하는 영역, 팽창파, 난류 전단층 등의 매우 복잡한 구조를 이루고 있는 것으로 알려져 있다. 본 연구에서는 출구마하수 2, 축소-확대형 초음속 노즐을 통해 과소 팽창된 제트가 수직, 경사평판에 부딪힐 때 형성되는 표면압력분포 및 유동가시화 등을 초음속 유동시험장치를 이용하여 연구하였다. 평판에서의 최대압력은 수직일 경우보다 경사졌을 때 훨씬 더 컸으며, 이는 여러 충격파를 통한 압력 회복 때문이다. 또한, 평판이 자유제트의 첫 번째 충격파 셀 내에 위치할 때 과소 팽창비에 따른 표면압력분포는 서로 유사한 경향을 보여주었다.

• 대한기계학회논문집A
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• 제38권12호
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• pp.1427-1430
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• 2014

열차폐 코팅은 고온 화염의 열이 블레이드의 모재에 직접 전달되는 것을 막는 역할을 하며, 세라믹 재질의 탑코팅층과 금속 모재간 결합력을 증가시켜주는 본드코팅층으로 이루어져있다. 이러한 열차폐 코팅 기술로 인하여 블레이드 표면의 온도가 화염온도에 비해 약 $100{\sim}170^{\circ}C$정도 낮아지게 된다. 이러한 열차폐 코팅은 금속모재와 코팅층의 열팽창 계수의 차이로 인해 내부 응력이 발생하게 되며, 블레이드의 형상 및 위치에 따라 발생하는 응력이 다르다. 따라서 본 논문에서는 열차폐코팅의 내구성 시험에 보편적으로 사용되는 코인형 시험편에 대하여 모재의 곡률에 따른 유한요소해석을 수행하고 열차폐 코팅에서 발생하는 내부 응력변화를 고찰하였다. 그 결과 탑코팅에 최저응력이 발생할 때의 곡률을 도출하였고 최저응력에서의 곡률과 차이가 커질수록 발생하는 응력이 커짐을 확인하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2017년도 제48회 춘계학술대회논문집
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• pp.248-250
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• 2017

Mar-M-247 합금은 고온에서의 우수한 강도로 Ni기 초내열합금 중 항공용 가스터빈 부품에 가장 널리 사용되는 소재 중 하나이다. Mar-M-247을 이용하여 터빈 노즐, 터빈 블레이드와 같이 Hot section 용으로 제작되는 부품은 복잡한 형상 등의 이유로 접합 공정을 적용하고 있다. 본 연구에서는 Mar-M-247 합금의 액상확산접합부에 대한 고온 특성 거동을 고찰하고자 하였다. 이에, $1,121^{\circ}C$에서 7분간 확산접합을 실시하여 고온 강도 변화를 관찰하였다. 시험 결과, 접합 시편은 $649^{\circ}C$에서 모재 대비 약 70%, $825^{\circ}C$에서 약 60%, $1,000^{\circ}C$에서 약 45%의 강도치를 나타내었다. 접합시간에 따른 강도 변화를 관찰한 결과, 720분 접합한 시편은 $649^{\circ}C$에서 모재와 유사한 강도치를 나타내었으며, 이는 One-body 부품에 가까운 일체형 확산 접합이 이루어진 것으로 판단된다.

• Advances in aircraft and spacecraft science
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• 제9권5호
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• pp.415-431
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• 2022

Secondary flows have a huge impact on losses generation in modern low pressure gas turbines (LPTs). At design point, the interaction of the blade profile with the end-wall boundary layer is responsible for up to 40% of total losses. Therefore, predicting accurately the end-wall flow field in a LPT is extremely important in the industrial design phase. Since the inlet boundary layer profile is one of the factors which most affects the evolution of secondary flows, the first main objective of the present work is to investigate the impact of two different inlet conditions on the end-wall flow field of the T106A, a well known LPT cascade. The first condition, labeled in the paper as C1, is represented by uniform conditions at the inlet plane and the second, C2, by a flow characterized by a defined inlet boundary layer profile. The code used for the simulations is based on the Discontinuous Galerkin (DG) formulation and solves the Reynolds-averaged Navier-Stokes (RANS) equations coupled with the Spalart Allmaras turbulence model. Secondly, this work aims at estimating the influence of viscosity and turbulence on the T106A end-wall flow field. In order to do so, RANS results are compared with those obtained from an inviscid simulation with a prescribed inlet total pressure profile, which mimics a boundary layer. A comparison between C1 and C2 results highlights an influence of secondary flows on the flow field up to a significant distance from the end-wall. In particular, the C2 end-wall flow field appears to be characterized by greater over turning and under turning angles and higher total pressure losses. Furthermore, the C2 simulated flow field shows good agreement with experimental and numerical data available in literature. The C2 and inviscid Euler computed flow fields, although globally comparable, present evident differences. The cascade passage simulated with inviscid flow is mainly dominated by a single large and homogeneous vortex structure, less stretched in the spanwise direction and closer to the end-wall than vortical structures computed by compressible flow simulation. It is reasonable, then, asserting that for the chosen test case a great part of the secondary flows details is strongly dependent on viscous phenomena and turbulence.