• Title/Summary/Keyword: Aerodynamic Performance Loss

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PREDICTION OF AERODYNAMIC PERFORMANCE LOSS OF A WIND TURBINE BLADE SECTION DUE TO CONTAMINANT ACCUMULATION (외부 오염물 증착에 의한 풍력 터빈 날개 단면의 공력 성능 저하 예측)

  • Yang, T.H.;Choi, J.H.;Yu, D.O.;Kwon, O.J.
    • Journal of computational fluids engineering
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    • v.18 no.1
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    • pp.91-97
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    • 2013
  • In the present study, the effects of contaminant accumulation and surface roughness on the aerodynamic performance of wind turbine blade sections were numerically investigated by using a flow solver based on unstructured meshes. The turbulent flow over the rough surface was modeled by a modified ${\kappa}-{\omega}$ SST turbulence model. The calculations were made for the NREL S809 airfoil with varying contaminant sizes and positions at several angles of attack. It was found that as the contaminant size increases, the degradation of the airfoil performance becomes more significant, and this trend is further amplified near the stall condition. When the contaminant is located at the upper surface near the leading edge, the loss in the aerodynamic performance of the blade section becomes more critical. It was also found that the surface roughness leads to a significant reduction of lift, in addition to increased drag.

Aerodynamic Performance Prediction of Multistage Axial-Flow Compressors with Its Applications (다단축류압축기의 공력성능 예측기법 개발 및 적용연구)

  • Chung, H.T.;Park, C.H.
    • Journal of Power System Engineering
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    • v.3 no.3
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    • pp.54-59
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    • 1999
  • The purpose of the present study was to develop the numerical method for predicting the on-design and off-design performance of multistage axial-flow compressors. The aerodynamic properties in blade rows were analyzed by incorporating the streamline curvature method as a quasi 3D analysis with the imperical modeling of exit flow angle and loss coefficients. The present calculation procedure has been tested by applying to 5-stage compressors and good agreement with experiments has been found. The detail analysis of aerodynamic performances has been done on the compression part of the bench-scaled gas turbine engines. The predicted performance map at the variable speedline and flow rates could be used as a guide of the engine operation.

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A Computerized Design System of the Axial Fan Considering Performance and Noise Characteristics (성능 및 소음특성을 고려한 축류 팬 설계의 전산 체계)

  • Lee, Chan;Kil, Hyun-Gwon
    • The KSFM Journal of Fluid Machinery
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    • v.13 no.2
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    • pp.48-53
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    • 2010
  • A computerized design system of axial fan is developed for constructing 3-D blade geometry and predicting both aerodynamic performance and noise. The aerodynamic blading design of fan is conducted by blade angle distribution, camber line determination, airfoil thickness distribution and blade element stacking along spanwise distance. The internal flow and the aerodynamic performance of designed fan are predicted by the through-flow modeling technique with flow deviation and pressure loss correlations. Based on the predicted internal flow field and performance data, fan noise is predicted by two models for discrete frequency and broadband noise sources. The present predictions of the flow distribution, the performance and the noise level of actual fans are well agreed with measurement results.

Design Method of the Sirocco Fan Considering Aeroacoustic Performance Characteristics (공력음향학적 특성을 고려한 시로코 팬의 설계 방법)

  • Lee, Chan
    • The KSFM Journal of Fluid Machinery
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    • v.13 no.2
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    • pp.59-64
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    • 2010
  • A design method of Sirocco fan is developed for constructing 3-D impeller and scroll geometries, and for predicting both the aerodynamic performance and the noise characteristics of the designed fan. The aerodynamic blading design of fan is conducted by blade angle, camber line determinations and airfoil thickness distribution, and then the scroll geometry of fan is designed by using logarithmic spiral. The aerodynamic performance of designed fan is predicted by the meanline analysis with flow blockage, slip and pressure loss correlations. Based on the predicted performance data, fan noise is predicted by two models for cutoff frequency and broadband noise sources. The present predictions for the performance and the noise level of actual fans are well agreed with measurement results.

Measurement and Prediction of Aerodynamic Noise from Sirocco Fans (시로코 홴 성능 및 공력 소음 예측에 관한 연구)

  • Kim, Kyoung-Ho;Park, Kye-Chan;Lee, Seungbae
    • The KSFM Journal of Fluid Machinery
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    • v.2 no.4 s.5
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    • pp.57-64
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    • 1999
  • The prediction method of the performance and aerodynamic noise from a sirocco fan was developed and compared with measured data. To predict the performance of the sirocco fan, the well-known slip coefficients and various loss models were tested and applied to forward curved sirocco impellers. Using loss models proposed for both impeller and casing, the predicted performance characteristics were in good agreement with measured ones by an ANSI test plenum. Various scaling models for aerodynamic noise from the sirocco fan were evaluated and tested against measured power levels in terms of flow coefficient. It was shown that the turbulent broadband sound power from the sirocco fan can be modeled successfully by trailing edge noise.

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Evaluation of Design Program of Low-Noise Axial Fan (축류형 송풍기 저소음 설계 프로그램의 개발 및 평가)

  • 김기황;박준철;김진화;이승배
    • Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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    • 2001.05a
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    • pp.967-972
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    • 2001
  • An axial fan design code, called iDesignFan$^{TM}$, was developed. In this code, three major loss models were used to predicted the aerodynamic performance of a fan. The overall sound pressure level, predicted from steady blade loading, is also used as an input parameter from the third loop of the designing process to acquire most silent fan for the given aerodynamic performance parameters. With this kind of inverse design concept used in this code, the period of designing a fan, which has given aerodynamic performance with minimal acoustic noise, is significantly shortened. The experimental results of a prototype fan, designed by this code, showed that aerodynamic and acoustic performance of an axial fan is reasonably well predicted. Thus, one can design/develop an axial fan in a short time by using the code.e.

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Development of Centrifugal Compressors in an 1.2MW Industrial Gas Turbine(I)-Aerodynamic Design and Analysis- (1.2MW급 산업용 가스터빈 원심압축기 개발(1)- 공력설계해석 -)

  • Jo, Gyu-Sik;Lee, Heon-Seok;Son, Jeong-Rak
    • Transactions of the Korean Society of Mechanical Engineers B
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    • v.20 no.8
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    • pp.2707-2720
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    • 1996
  • The aerodynamic design of the two-stages of centrifugal compressors in an 1.2MW industrial gas turbine is completed with the application of numerical analyses. The final shape of an intake, the axial guide vanes and a return channel is determined using several interactions between design and two-dimensional turbulent flow analysis, focused on the minimum loss of internal flows. The one-dimensional turbulent flow analysis, focused on the minimum loss of internal flows. The one-dimensional design and prediction of aerodynamic performances for the compressors are performed by two different methods; one is a method with conventional loss models, and the other a method with the two-zone model. The combination methods of the Betzier curves generate three-dimensional geometric shapes of impeller blades which are to be checked with a careful change of aerodynamic blade loadings. The impeller design is finally completed by the applications of three-dimensional compressible turbulent flow solvers, and the effect of minor change of design of the second-stage channel diffuser is also studied. All the aerodynamic design results are soon to the verified by component performance tests of prototype centrifugal compressors.

Study on the Optimum Rotor Blade Design of the 5 kW HAWT by BEMT (BEMT를 이용한 5 kW급 수평축 풍력발전용 로터 블레이드 형상 최적설계에 관한 연구)

  • Kim, Mun-Oh;Lee, Min-Woo;Kim, Chang-Goo;Kim, Tae-Hyung;Lee, Young-Ho
    • 한국신재생에너지학회:학술대회논문집
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    • 2009.11a
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    • pp.444-447
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    • 2009
  • The optimum design and the performance analysis software called POSEIDON for the HAWT (Horizontal Axis Wind Turbine) was developed by use of BEMT. The Prandtl's tip loss theory was adopted to consider the blade tip loss. The aerodynamic characteristics of NACA 63415 airfoils were predicted via X-FOIL and the post stall characteristics were estimated by the Viterna's equations. All the predicted aerodynamic characteristics are fairly well agreed with the Velux wind tunnel test results. The rated power of the testing rotor is 5kW at design conditions. The power, estimated by use of predicted lift and drag coefficient via X-FOIL becomes a little higher than experimental one.

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Software Development for the Performance Analysis of the HAWT based on BEMT (BEMT를 적용한 수평축 풍력터빈 성능해석 소프트웨어의 개발)

  • Kim, Beom-Seok;Nam, Cheong-Do;Lee, Young-Ho
    • 한국신재생에너지학회:학술대회논문집
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    • 2005.11a
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    • pp.575-578
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    • 2005
  • The optimum design and the performance analysis software called POSEIDON for the HAWT (Horizontal Axis Wind Turbine) was developed by use of BEMT. The Prandtl's tip loss theory was adopted to consider the blade tip loss. The lift and the drag coefficient of S-809 airfoil were predicted via X-FOIL and also the post stall characteristics of S-809 were estimated by the Viterna's equations. All the predicted aerodynamic characteristics are fairly well agreed with the wind tunnel test results, performed by Sommers in Delft university of technology. The rated power of the testing rotor is 20kW(FIL-20) at design conditions. The experimental aerodynamic parameters and the X-FOIL data were used for the power prediction of the FIL-20 respectively. The comparison results shows good agreement in power prediction.

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Software Development for the Performance Analysis of the HAWT based on BEMT (BEMT를 적용한 수평축 풍력터빈 성능해석 소프트웨어의 개발)

  • Kim, Beom-Seok;Lee, Young-Ho
    • New & Renewable Energy
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    • v.1 no.4 s.4
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    • pp.38-42
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    • 2005
  • The optimum design and the performance analysis software called POSEIDON for the HAWT [Horizontal Axis Wind Turbine] was developed by use of BEMT. The Prandtl's tip loss theory was adopted to consider the blade tip loss. The lift and the drag coefficient of S-809 airfoil were predicted via X-FOIL and also the post stall characteristics of S-809 were estimated by the Viterna's equations. All the predicted aerodynamic characteristics are fairly well agreed with the wind tunnel test results, performed by Sommers in Delft university of technology. The rated power of the testing rotor is 20kW[FIL-20] at design conditions. The experimental aerodynamic parameters and the X-FOIL data were used for the power prediction of the FIL-20 respectively. The comparison results shows good agreement in power prediction.

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