• 제목/요약/키워드: turbine blade

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CAD/CAI 통합에 기초한 박형 단면을 가지는 항공기 터빈블레이드의 정밀측정기술 개발 (Development of Precision Inspection Technique for Aircraft Parts Having Very Thin Features on CAD/CAI Integration)

  • 박희재;안우정;김왕도
    • 대한기계학회논문집A
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    • 제20권6호
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    • pp.1743-1752
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    • 1996
  • In this paper, a precision inspection technique using CAD/CAI integration is proposed for the parts having very thin and sharp 3 dimensional curve features. The technique begings with feature reconstruction of turbine blades which have 3 dimensional combined feometry, such as splines, and thin circles. The alifnment procedures consistsb of two phases-rough and fine phases : rough phase alignment is based on the conventional 6 point5s probing on the clear cut surfacef, and fine phase alignment is based on the intial measurement on the 3 dimensional curved parts using an lterative measurement feed-back least sequares technique for alignment. Forf the analysis of profile tolerance of parts, the actual measured points are obtained by finding the closet points on the CAD geometry by the developed subdivision technique and the Tschebycheff norm is applied based on iterative fashion, giving accurate profile tolerance value. The developed inspection technique is applied to practical procedures of blade manufacturing and demonstrated high performance.

회전하는 매끈한 정삼각 유로 내 열/물질전달 분포 측정 (Detailed Measurement of Heat/Mass Transfer in a Rotating Equilateral Triangular Channel with Smooth Walls)

  • 김경민;이동현;조형희
    • 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.

터빈 익렬내부의 3차원 압축성 점성유동장의 수치해석 (Numerical Analysis of Three-Dimensional Compressible Viscous Flow Field in Turbine Cascade)

  • 정희택;백제현
    • 대한기계학회논문집
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    • 제16권10호
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    • pp.1915-1927
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    • 1992
  • 본 연구에서는 3차원 압축성 내부유동해석 코드를 개발하여 터어빈 정익이나 동익 내부의 차원 익렬 유동을 수치적으로 해석하고자 한다. 여기에서 사용된 코드 는 Obyashi의 LU-ADI기법을 이용한 기존의 2차원 익렬 유동해석 코드를 3차원 유동장 으로 학장한 것이고, 난류유동해석에는, Baldwin-Lomax의 박층 대수모델을 3차원으로 확장한 알고리즘을 적용하였다.Kiock등이 실험한 선형 터어빈 익렬 내부의 천음속 유동장에 적용하여 양끝 벽면에 의한 3차원 유동장 특성을 분석하고, 3차원 익렬 유동 코드의 적합성을 검토하였다.

Part tolerancing through multicale defect analysis

  • Petitcuenot, Mathieu;Anselmetti, Bernard
    • International Journal of Aeronautical and Space Sciences
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    • 제17권1호
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    • pp.109-119
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    • 2016
  • When manufactured parts undergo large deformations during the manufacturing process, the global specifications of a part based on the concept of tolerance zone defined in the ISO 1101 standard [1] enable one to control the part's global defects. However, the extent of this tolerance zone is too large when the objective is to minimize local defects, such as hollows and bumps. Therefore, it is necessary to address local defects and global defects separately. This paper refers to the ISO 10579 standard [2] for flexible parts, which enables us to define a stressed state in order to measure the part by straightening it to simulate its position in the mechanism. The originality of this approach is that the straightening operation is performed numerically by calculating the displacement of a cloud of points. The results lead to a quantification of the global defects through various simple models and enable us to extract local defects. The outcome is an acceptable tolerance solution. The procedure is first developed for the simple example of a steel bar with a rectangular cross section, then applied to an industrial case involving a complex 3D surface of a turbine blade. The specification is described through ISO standards both in the free state and in the straightened state.

플라즈마 용사 열차폐 코팅의 열화에 따른 접착강도 평가 (Evaluation of Bond Strength of Isothermally Aged Plasma Sprayed Thermal Barrier Coating)

  • 김대진;이동훈;구재민;송성진;석창성;김문영
    • 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.

다양한 막냉각 홀 형상에 대한 막냉각 효율의 수치해석 (NUMERICAL STUDY ON FILM-COOLING EFFECTIVENESS FOR VARIOUS FILM-COOLING HOLE SCHEMES)

  • 김선민;이기돈;김광용
    • 한국전산유체공학회지
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    • 제16권4호
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    • pp.92-99
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    • 2011
  • In order to protect the turbine blade from working fluid of high temperature, many cooling techniques such as internal convection cooling, film cooling, impinging jet cooling and thermal barrier coating have been developed. With all other things, film-cooling has been widely used as the important alternative. In the present work, numerical analysis has been performed to investigate and to compare the film-cooling performance of various film-cooling hole schemes such as cylindrical, crescent, louver, and dumbbell holes. To analyze the turbulent flow and the film-cooling mechanism, three-dimensional Reynolds-averaged Navier-Stokes analysis has been performed with shear stress transport turbulence model. The validation of numerical results has been assessed in comparison with experimental data. The characteristics of fluid flow and the film-cooling performance for each shaped hole have been investigated and evaluated in terms of centerline, laterally averaged and spatially averaged film-cooling effectivenesses. Among the film cooling holes, the dumbbell shaped hole shows better film-cooling effectiveness than the other shaped holes. And the louver and cylindrical shaped hole show the worst film cooling performance, and concentrated flows on near the centerline only.

효율적인 2단계 최적화를 통한 3차원 해상풍력터빈 블레이드 설계 (Three-Dimensional Offshore Wind Turbine Blade Design by using Efficient Two Step Optimization)

  • 이기학;홍상원;정지훈;김규홍;이동호;이경태
    • 한국신재생에너지학회:학술대회논문집
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    • 한국신재생에너지학회 2007년도 춘계학술대회
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    • pp.432-436
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    • 2007
  • 본 연구의 목적은 3차원 풍력터빈 블레이드 최적형상설계를 위한 실용적이고 효율적인 설계 과정을 구현하는 것이다. 국내 연안의 해상풍력에 적용하기 위해서 통계적 모델을 이용하여 풍황 자료를 분석하였다. 설계에 관련된 많은 수의 설계변수를 효과적으로 관리하기 위해서 설계과정은 운용조건 최적화와 블레이드 형상설계의 2단계로 구성하였다. 실험계획법에 의해 추출된 각 운용조건점은 형상설계를 위한 입력값으로 제공된다. 형상설계 단계에서는 최소에너지손실 조건과 결합된 BEMT를 이용하여 각 블레이드 단면에서의 시위길이와 피치각 분포를 최적화하였다. 블레이드 단면 익형은 NREL S830을 이용하였고, 익형의 공력성능은 XFOIL을 이용하여 예측하였다. 설계된 블레이드 형상의 성능해석을 수행하고 그 결과를 바탕으로 반응면을 구성하였다. 좀 더 나은 성능을 가진 블레이드 형상을 찾기 위해서 초기설계공간에서 확률적 방법을 이용하여 타당성 있는 설계공간까지 운용조건 설계변수를 이동시키고 구배최적화 기법을 통해 각각의 제약함수를 만족하면서 연평균발생에너지를 최대로 하는 최적블레이드 형상을 구현하였다. 제시된 최적설계과정은 풍력터빈블레이드 개발에 실용적이고 신뢰성 있는 설계툴로서 사용이 가능하다.

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풍력용 동기발전기의 전기자 반작용을 이용한 전기 제동방식에 관한 연구 (A study on electronic braking system using wind power synchronous generator's armature reaction)

  • 박귀열;문채주;정의헌;장영학;김의선
    • 한국태양에너지학회 논문집
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    • 제30권4호
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    • pp.1-8
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    • 2010
  • The mechanical parts of small windp ower generator less than 10kW are manufactured in the form of removing most of the accelerators. The braking system to protect blade from damages caused by high wind speed is manufactured in a manner having apparatus system(furling), manual brake or no brake. This study is on braking system in small size wind power generator, and carried out survey as following steps by applying electric braking system which uses armature reaction. We explained the principle of electric braking system and the principle of existing braking system. Also, this paper interpreted short circuit current through open circuit and short circuit, as well as checking brake system's action using armature reaction with real construction of control device.

Soot 생성을 고려한 가스발생기의 Kerosene/LOx의 비평형 화학반응 모델링 (Modeling of Non-Equilibrium Kinetics in Gas Generator including Soot Formation)

  • 유정민;이창진
    • 한국추진공학회:학술대회논문집
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    • 한국추진공학회 2006년도 제27회 추계학술대회논문집
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    • pp.150-153
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    • 2006
  • 액체 로켓 엔진의 가스발생기는 터빈 블레이드의 열적 손상을 막기 위해 온도의 제한이 있으며 이를 위해 농후 또는 희박 연소를 하게 된다. 따라서 비평형 화학 반응이 주로 발생하며 이를 해석하는 것은 매우 어렵다. 본 연구에서는 케로신과 액체산소를 추진제로 하는 가스발생기에 대하여 Dagaut이 제안한 상세 화학 반응 단계를 사용하여 완전 혼합 반응기 연소 모델의 수정을 통해 계산하였으며, Frenklach의 soot 모델을 적용하여 예측 결과의 몰 분율, 가스 물성치 등의 결과에 대한 개선 방향을 제시하였다.

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이중분사 홀의 면적비와 분사각 변화에 따른 가스터빈 막냉각 특성 연구 (A Study on the Film-cooling Characteristics of Gas Turbine Blade with Various Area Ratios and Ejection Angles of the Double Jet Holes)

  • 조문영;이종철;김윤제
    • 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.