• Title/Summary/Keyword: 로터 블레이드 형상

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차세대 로터 블레이드 형상정의 및 공력소음 해석

  • Yee, Kwan-Jung;Hwang, Chang-Jeon;Joo, Gene
    • Aerospace Engineering and Technology
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    • v.2 no.1
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    • pp.35-43
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    • 2003
  • In this study, a rotor planform shape with high performance and low noise has been designed and its aerodynamic and aeroacoustic characteristics are analysed. First of all, rotor blade planform with low noise characteristics, has been designed based on the paddle-shape blade by applying vane-tip concept. Finally, noise characteristics of the designed next-generation rotor blade have been investigated and the results are compared with those of BERP blade.

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Shape design and flow analysis on a 200W-class gyromill type vertical axis wind turbine rotor blade (200 W급 자이로밀형 수직축 풍력터빈 로터 블레이드 형상설계 및 유동해석)

  • Cho, Woo-Seok;Kim, Hyun-Su;Choi, Young-Do
    • Journal of Advanced Marine Engineering and Technology
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    • v.37 no.2
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    • pp.170-177
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    • 2013
  • This study is focused on the shape design and flow analysis on a 200 W-class Gyromill type vertical axis wind turbine rotor blade. Single tube theory is adopted for the shape design of the turbine blade. 2-dimensional CFD analysis is conducted to examine the turbine performance with basic shape, and then 3-dimensional shape is determined from the examination of the performance. By the CFD analysis on the 3-dimensional shape of the wind turbine, performance of the turbine is examined and also, shape of the wind turbine rotor blade is determined accordingly. From the results of this study, a 200 W-class Gyromill type vertical axis wind turbine rotor blade is designed and the reliability of the design method is confirmed by CFD analysis.

Effect of Geometric Variation on Aerodynamic Characteristics of a Shrouded Tail Rotor (덮개꼬리로부터의 형상변화에 따른 공력 특성에 관한 연구)

  • Lee, H.-D.;Kang, H.-J.;Kwon, O.-J.
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.33 no.5
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    • pp.9-17
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    • 2005
  • In the early stage of helicopter design, an optimal configuration is usually determined after a numerous parametric study about the aerodynamic performance due to geometric variation. In order to improve the aerodynamic performance of a shrouded tail rotor, optimization of the tip clearance gap between blade and shroud, the blade planform shape, and the arrangement of blade spacing is required. In the present study, the aerodynamic performance characteristics of a shrouded tail rotor due to geometric variation was investigated by using an inviscid compressible unstructured mesh flow solver for rotary wings.

Design Optimization of QTP-UAV Prop-Rotor Blade Using ModelCenter (ModelCenter를 이용한 QTP-UAV 프롭로터 블레이드 형상 최적설계)

  • Kang, Hee Jung
    • Journal of Aerospace System Engineering
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    • v.11 no.4
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    • pp.36-43
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    • 2017
  • Blade design optimization of QTP-UAV prop-rotor was conducted using ModelCenter(R). Performance efficiency of the blade in hover and forward flight were adopted as the multi-objective function. Required power and pitch link force applied to constraint in each flight mode and limited lower than the value of the baseline blade. Design variables of root chord length of the blade, taper ratio, twist slope, twist angle at 0.5R of the blade, anhedral angle, parabolic coefficient of a tip shape and location of airfoil were used to generate the blade planform. CAMRAD-II, the comprehensive analysis program of rotorcraft, was used for performance analysis of prop-rotor blade in design process. Performance of the optimized blade improved 1.6% of figure of merit in hover and 13.6% of propulsive efficiency in forward flight. Pitch link force also reduced approximately 30% less than that of the baseline blade.

Detailed Flow Analysis of Helicopter Shrouded Tail Rotor in Hover Using an Unstructured Mesh Flow Solver (비정렬격자계를 이용한 헬리콥터 덮개 꼬리 로터의 제자리 비행 유동 해석)

  • Lee, Hui Dong;Gwon, O Jun;Gang, Hui Jeong;Ju, Jin
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.31 no.5
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    • pp.1-9
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    • 2003
  • Detailed flow of a shrouded tail rotor in hover is studied by using a compressible inviscid flow solver on unstructured meshes. The numerical method is based on a cell-centered finite-volume discretization and an implicit Gauss-Seidel time integration. Numerical simulation is made for a single blade attached to the center body and guide by the duct by imposing a periodic boundary condition between adjacent rotor blades. The results show that the performance of an isolated rotor without shroud compares well with experiment. In case of a shrouded rotor, correction of the collective pitch angle is made such that the overall performance matches with experiment to account for the uncertainties of the experimental model configuration. Details of the flow field compare well with the experiment confirming the validity of the present method.

Optimum Shape Design of Counter-rotating Wind Turbine System (상반회전 풍력발전 시스템의 설계형상 최적화에 관한 연구)

  • Lee, Ju-Young;Jung, Sung-Nam;Song, Seung-Ho;Kim, Dong-Yong
    • Proceedings of the KIEE Conference
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    • 2003.04a
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    • pp.373-375
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    • 2003
  • 상반회전 풍력발전 시스템의 경우 전방에 위치한 로터의 후류 효과를 적절히 반영하여 설계에 이용해야 한다. 본 연구에서는 이러한 로터의 후류효과 및 블레이드의 실속후 모델을 고려하여 30kW급 상반회전시스템의 설계형상에 대한 검토연구를 수행하였다 기본공력이론은 모멘텀 이론과 2차원 준정상 공기력 이론을 통합한 형태를 사용하였다. 로터의 후류영향을 고려하기 위해 축소형 풍차 블레이드 모델에 대한 풍동시험 결과를 적절히 이용하며, 이로부터 보조로터를 지난 후류의 축속도 및 각속도 성분을 결정하였다. 최종적으로 상반회전 시스템의 로터 반경 및 상호 이격거리 등을 고려한 성능해석을 수행하고 이로부터 최적 설계형상에 대한 파라미터 연구결과를 제시하였다.

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Development of Program for Modeling of Cross Section of Composite Rotor Blade (복합재료 로터 블레이드 단면 모델링 프로그램 개발)

  • Do, Hyung-Soo;Cho, Jin-Yeon;Park, Il-Ju;Jung, Sung-Nam;Kim, Tae-Joo;Kim, Do-Hyung
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.39 no.3
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    • pp.261-268
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    • 2011
  • Generally, modeling procedure of cross section of composite rotor blade is complicated and time-consuming, because it is made up of various stiffeners and multiple layers of composite materials. For efficient modeling of cross section of composite rotor blade, a modeling program so called KSec2D, which provides a user friendly GUI, is developed by using a 2D modeling algorithm based on set operation. By the developed program KSec2D, a modeling of complicated cross section of rotor blade is carried out. Through the demonstration, the usefulness of developed program in modeling procedure of cross section of composite rotor blade is verified.

Surface Pressure Measurement on a Rotor Blade using Fast-Responding PSP (고속압력감응페인트를 이용한 로터 블레이드 표면 압력 측정)

  • Kim, Kidong;Kwon, Kijung
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.42 no.1
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    • pp.1-9
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    • 2014
  • The present study was conducted by using fast-responding PSP technique to measure the surface pressure on a small-scale rotor blade in hover. Also, the study was performed to verify the accuracy and investigate its possibility of PSP application for rotor blade pressure measurement. Pulsed laser which has 532 nm wavelength was used as a light source. Lifetime measurement technique was applied. Also, the coated paint on a rotor blade was porous PSP which has faster response time than conventional PSP. The blades had NACA0012 airfoils. The length of rotor blade was 340 mm and chord was 40 mm with rectangular shape 1 set, and 4 sets had several tip sweepback angles. The measured results qualitatively showed that the upper surface pressure decreases with increasing the collective pitch angle. Quantitative pressure coefficients of PSP results were higher approximately 0.4 to 0.7 than the pressure tap data of the NASA experiment.

An Investigation into the Three-dimensional Design of Turbine Rotor Blade for Turbopump (터보펌프용 터빈 로터 블레이드의 3차원 설계 연구)

  • Jeong, Sooin;Choi, Byoungik;Lee, Hanggi;Kim, Kuisoon
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.1038-1044
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    • 2017
  • We are working on improving the performance by applying the three-dimensional design element to the rotor blades of high pressure supersonic impulse turbine that drives turbo pump of liquid rocket engine. In this paper, based on the shape of a rotor blade of a turbopump turbine designed in the past, a three-dimensional shape is applied to a rotor blade through a stacking line change such as sweep and dihedral. After performing the flow analysis, the changes in the turbine performance characteristics for each design element were carefully examined and the results were summarized.

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A study of Main Rotor Blade Tip shape and analysis of flow around Main Rotor Blade Tip (Main Rotor Blade Tip 형상 변화에 따른 유동분석)

  • Kim, Se-Il
    • Proceeding of EDISON Challenge
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    • 2013.04a
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    • pp.382-386
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    • 2013
  • 본 연구에서는 Main Rotor Blade Tip 형상 변화에 따른 후류해석을 통해 와류 생성 및 주변 유동을 분석하여 블레이드 팁 형상의 변화가 와류 간섭을 감소시키는지의 여부를 확인하였다. EDISON CFD를 이용하여 블레이드 Blade Tip 형상에 따라 유동이 어떻게 나타나며, Blade 후류의 압력과 점성의 변화를 분석하여 와류의 양상을 해석하였다. 비교 Blade 형상은 2세대 긴 직사각형 모형, KUH 수리온의 Blade, 유로콥터사의 'Blue Edge'로 비교적 최근에 개발된 대표적인 Blade Tip 형상 3개로 정하였다. 결과를 토대로 블레이드 뒷전의 와류흐름 양상을 확인하여 블레이드 와류 간섭현상의 감소를 확인하였다.

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