• Tribology and Lubricants
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• 제36권2호
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• pp.105-115
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• 2020

This paper presents a numerical study on the rotordynamic analysis of a dual-spool turbofan engine in the context of blade defect events. The blades of an axial-type aeroengine are typically well aligned during the compressor and turbine stages. However, they are sometimes exposed to damage, partially or entirely, for several operational reasons, such as cracks due to foreign objects, burns from the combustion gas, and corrosion due to oxygen in the air. Herein, we designed a dual-spool rotor using the commercial 3D modeling software CATIA to simulate blade defects in the turbofan engine. We utilized the rotordynamic parameters to create two finite element Euler-Bernoulli beam models connected by means of an inter-rotor bearing. We then applied the unbalanced forces induced by the mass eccentricities of the blades to the following selected scenarios: 1) fully balanced, 2) crack in the low-pressure compressor (LPC) and high pressure compressor (HPC), 3) burn on the high-pressure turbine (HPT) and low pressure compressor, 4) corrosion of the LPC, and 5) corrosion of the HPC. Additionally, we obtained the transient and steady-state responses of the overall rotor nodes using the Runge-Kutta numerical integration method, and employed model reduction techniques such as component mode synthesis to enhance the computational efficiency of the process. The simulation results indicate that the high-vibration status of the rotor commences beyond 10,000 rpm, which is identified as the first critical speed of the lower speed rotor. Moreover, we monitored the unbalanced stages near the inter-rotor bearing, which prominently influences the overall rotordynamic status, and the corrosion of the HPC to prevent further instability. The high-speed range operation (>13,000 rpm) coupled with HPC/HPT blade defects possibly presents a rotor-case contact problem that can lead to catastrophic failure.

• 대한기계학회논문집A
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• 제39권9호
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• pp.929-936
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• 2015

풍력터빈 블레이드의 후단, 나셀 상부에 설치되는 나셀 풍속계는 블레이드 회전에 따른 후류효과 및 나셀형상 등으로 인하여 풍력터빈에 입사되는 자연풍속과는 다른 왜곡된 풍속을 측정한다. 풍력터빈 출력성능의 신뢰성 확보를 위해서는 나셀풍속을 자연풍속으로 보정하는 나셀전달함수를 유도하여 성능곡선을 보정하여야 한다. 본 연구에서는 전라남도 비금도 북부 해안에 건설된 신안풍력발전소에서 지상기반 원격탐사 장비인 라이다(LiDAR)를 설치하여 나셀 풍속계와 동일 높이에서의 자연풍속을 측정하였다. 나셀풍속을 자연풍속으로 보정하는 기존의 단순회귀분석에 의한 선형 나셀전달함수를 개선하기 위하여 다중회귀분석에 의한 비선형 나셀전달함수를 유도하였다. 나셀전달함수로 계산한 보정풍속을 풍력터빈 출력곡선에 대입하여 산출한 이론 발전량과 실제 발전량의 잔차를 비교하여 개선효과를 검증하였다. 다중회귀분석 나셀전달함수는 단순회귀분석에 비해 풍속의 표준오차는 9.4% 감소하였으며, 발전량 잔차 분포의 평균은 6.5% 감소하여 개선효과가 있음을 확인하였다.

• 한국항공우주학회지
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• 제38권9호
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• pp.890-899
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• 2010

직선형 캐스케이드 장치에서 부분분사를 받는 터빈의 작동력을 분석하기 위하여 실험 연구를 수행하였으며, 익형은 축류형으로 코드가 200mm 이다. 분사노즐은 사각형 노즐로서 $200mm{\times}200mm$ 이며, 실험은 코드기준으로 레이놀드수 $3{\times}10^5$에서 수행되었다. 익형을 회전방향으로 이동하면서 정상상태일 때 각각의 위치에 대해 익형에 형성되는 회전방향의 힘과 축방향의 힘을 측정하였다. 탈설계 성능을 측정하기 위하여 노즐의 설치각을 $58^{\circ}$, $65^{\circ}$와 $72^{\circ}$로 변경하면서, 노즐의 설치각 변화에 대한 익형의 작동력 특성을 파악하였다. 또한 현절비를 1.25, 1.38, 1.67로 변경하면서 현절비 변화에 의한 익형의 작동력 변화를 측정하였다. 실험의 결과에서 최대 회전력의 크기는 현절비의 감소에 따라 증가하였으며, 노즐의 설치각이 감소하게 될 때 회전력은 증가하였다. 축방향의 힘은 노즐 설치각이 감소하면 증가하였으며, 큰 노즐 설치각에서는 분사영역에서 역축방향의 힘이 측정되었다.

• 한국산학기술학회논문지
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• 제18권12호
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• pp.9-16
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• 2017

본 논문에서는 풍력 발전기 블레이드 공력 설계 프로세스를 정립하고, 최적화 설계 전략을 제시 하였으며, 공력 설계 진행시에 반드시 검토 필요한 제약 조건들에 대해서 정리 하였다. 이를 토대로 하여 연구 목적뿐 아니라, 블레이드 설계자가 실제 업무에 쉽게 적용 가능하고, 초기 개념설계 단계부터 최종 3차원 형상 상세 설계 단계까지 통합적으로 수행이 가능한 BEMT 기반의 공력 설계 프로그램을 개발하였다. 개발된 프로그램 AeroDA는 개념 설계 모듈, 기본 설계 모듈, 최적 TSR 도출 모듈, 국부 형상 최적화 모듈, 성능 해석 모듈, 설계 검증 모듈 및 3차원 형상생성 모듈로 구성이 된다. 개발된 프로그램을 활용하여 NREL에서 공개 배포한 5MW 블레이드를 기반으로하여 하중저감을 위한 개선 설계를 진행하여 본 프로그램이 최적화 설계에 유용하게 사용 가능함을 확인 하였다. 또한 10kW 블레이드 공력 설계 및 터빈 상세 성능 해석을 진행하고, 이를 상용 전문 프로그램 DNV GL Bladed 결과와 비교하여 정확도를 검증하였다.

• 한국유체기계학회 논문집
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• 제18권6호
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• pp.63-70
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• 2015

This paper proposes a novel airfoil named "KA2" for the blade of the wind turbine systems. Dynamic loads characteristics are analyzed and compared using aerodynamic data of ten airfoils including the proposed airfoil. The blade is divided into the sixteen elements in the longitudinal direction of the blade for applying the Blade Element Method Theory (BEMT) method, and in each element, torque, thrust, and pitching moment are calculated using turbulent time varying wind speed and aerodynamic data of each wing. Additionally, each force and torque is accumulated in the whole region of the blade for the estimation of representative values. The magnitude of such forces is comparatively analyzed for different airfoils. The angle of attack is constant below the rated wind speed due to the fact that the tip speed ratio is kept at the constant value, and it increases in the region of over rated wind speed as the tip speed ratio decreasing with constant rated rpm and increasing wind speed. Such increase in the angle of attack causes the changes of the force acting on the airfoil with different characteristics of lift and drag in the stall region of each different airfoil. Even though the mean wind speed is in the rated speed in a given time, because of the turbulence, it has either the over rated or under rated speed most of the time. Furthermore, the dynamic properties of each force are analyzed in this rated wind speed in order to objectively understand the dynamic properties of the blades which are designed based on the different airfoils. These dynamic properties are also compared by the standard deviation of time varying characteristics. Moreover, the output characteristics of the wind turbine are investigated with different airfoils and wind speeds. Based on these investigations, it was revealed that the proposed airfoil (KA2) is well applicable to the blade with passive pitch control system.

• Composites Research
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• 제27권4호
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• pp.123-129
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• 2014

세라믹 기지 복합재료는 세라믹 기지에 고 용융 온도, 낮은 밀도, 고 탄성과 강도를 가진 탄화물, 질화물, 보론화물, 산화물 등의 강화재료를 끼워 넣어 파괴 인성을 높인 것이다. 이들 소재는 우주 비행체의 열 차폐 시스템, 또 고온의 가스 터빈의 연소실, 터빈 블레이드, 고정자(Stator) 베인 등의 부품에 사용되며, 버너와 화염 유지기(Flame holder), 고온 가스 덕트에는 산화 CMC가 사용되고 있고, 극심한 열 충격이 일어나는 브레이크 디스크나 시스템의 부품, 그리고 슬라이드 베어링 부품에도 활용되고 있다. 이러한 CMC에 대한 연구 개발은 미국의 우주 비행체 활용 목적을 비롯하여, 미국, 일본, 유럽에서의 초고속항공기와 가스 터빈용, 그리고 핵 융합용 등의 목적으로 국방과 에너지 산업과 같은 전략적 분야의 활용을 목표로 개발되고 있다.

• 한국유체기계학회 논문집
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• 제4권3호
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• pp.7-13
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• 2001

The present study investigates convective heat/mass transfer and flow characteristics inside a cooling passage of rotating gas-turbine blades. The rotating duct has staggered ribs with $70^{\circ}$ attack angle, which are attached on leading and trailing surfaces. Naphthalene sublimation technique is employed to determine detailed local heat transfer coefficients using the heat and mass transfer analogy. Additional numerical calculations are conducted to analyze the flow patterns in the cooling passage. The present experiments employ two-surface heating conditions in the rotating duct because the exposed surfaces to hot gas stream are pressure and suction side surfaces in the middle passages of an actual gas-turbine blade. Secondary flows are generated by Coriolis and centrifugal forces in the spanwise and streamwise directions. The ribs attached on the walls disturb the mainflow resulting in recirculation and secondary flows near the ribbed wall. The local heat transfer and flow patterns in the passage are changed significantly according to rib configurations and duct rotation speeds. Therefore, the geometry and arrangement of the ribs are important for the advantageous cooling performance. The experimental results show that the ribs enhance the heat transfer more than $70\%$ from that of the smooth duct. The duct rotation generates the heat transfer discrepancy between the leading and trailing walls due to the secondary flows induced by the Coriolis force. The overal heat transfer pattern on the leading and trailing walls for the first and second passes are depended on the rotating speed, but the local heat transfer trend is affected mainly by the rib arrangements.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2001년도 유체기계 연구개발 발표회 논문집
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• pp.325-333
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• 2001

The present study investigates convective heat/mass transfer and flow characteristics inside the cooling passage of the gas-turbine blades. It is important to increase not only the heat transfer rates but also the uniformity of heat transfer in the cooling passage. The square duct has compound-angled ribs with $60^{\circ},\;70^{\circ}$ and $90^{\circ}$ attack angles, which are installed on the test plate surfaces. a naphthalene sublimation technique is employed to determine the detailed local heat transfer coefficients using the heat and mass transfer analogy. The ribs disturb the main flow resulting in the recirculation and secondary flows near the ribbed wall and the vertices near the side-wall. The local heat transfer and the secondary flow in the duct are changed largely according to the rib orientation. Therefore, geometry and arrangement of the ribs are important fur the advantageous cooling performance. The angled ribs increase the heat transfer discrepancy between the wall and center regions because of the interaction of the secondary flows. The average heat/mass transfer coefficient and pressure drop of the ribs with the $60^{\circ}$ $-90^{\circ}$ compound-angle are higher than those with the $60^{\circ}$ attack angle. Also, the thermal efficiency of the compound-angled rib is higher than that with the $60^{\circ}$ attack angle. The uniformity of heat/mass transfer coefficient on the cross ribs may is higher than that on the parallel ribs array.

• 대한기계학회논문집A
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• 제30권8호
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• pp.965-975
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• 2006

High pressure turbine blades are one of the key components in fossil power plants operated at high temperature. The blade is usually made of 12Cr steel and its operating temperature is above $500^{\circ}C$. Long term service at this temperature causes material degradation accompanied by changes in microstructures and mechanical properties such as strength and toughness. Quantitative assessment of reduction of strength and toughness due to high temperature material degradation is required for residual life assessment of the blade components. Nondestructive technique is preferred. So far most of the research of this kind was conducted with low alloy steels such as carbon steel, 1.25Cr0.5Mo steel or 2.25Cr1Mo steel. High alloy steel was not investigated. In this study one of the high Cr steel, 12Cr steel, was selected for high temperature material degradation. Electrochemical polarization method was employed to measure degradation. Strength reduction of the 12Cr steel was represented by hardness and toughness reduction was represented by change of transition temperature, FATT. Empirical relationships between the electrochemical polarization parameter and significance of material degradation were established. These relationship can be used for assessing the strength and toughness on the aged high pressure blade components indirectly by using the electrochemical method.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 추계학술대회논문집B
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• pp.22-29
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• 2001

The present study investigates the effects of various rib arrangements and rotating on heat/mass transfer in the cooling passage of gas turbine blades. The cooling passage has very complex flow structure, because of the rib turbulator and rotating effect. Experiments and numerical calculation are conducted to investigate the complex flow structures and heat transfer characteristics; the numerical computation is performed using a commercial code, FLUENT ver.5, to calculate the flow structures and the experiments are conducted to measure heat/mass transfer coefficients using a naphthalene sublimation technique. For the rotating duct tests, the test duct, which is the cross section of is $20mm\times40mm$ (the hydraulic diameter, $D_h$, of 26.7 mm, has two-pass with $180^{\circ}$ turning and the rectangular ribs on the wall. The rib angle of attack is $70^{\circ}$ and the maximum radius of rotation is $21.63D_h$. The partition wall has 10 mm thickness, which is 0.5 times to the channel width, and the distance between the tip of the partition wall and the outer wall of the turning region is 26.7 mm $(1D_h)$. The turning effect of duct flow makes the very complex flow structure including Dean type vortex and high turbulence, so that the heat/mass transfer increases in the turning region and at the entrance of the second pass. The Coriolis effect deflects the flow to the trailing surface, resulting in enhancement of the heat/mass transfer on the trailing surface and reduction on the leading surface in the first pass. However, the opposite phenomena are observed in the second pass. The each rib arrangement makes different secondary flow patterns. The complex heat/mass transfer characteristics are observed by the combined effects of the rib arrangements, duct rotation and flow turning.