• Journal of Biosystems Engineering
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• 제26권5호
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• pp.423-430
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• 2001

The purpose of this study is to develop high-speed rotary tillage system for a power tiller by improving the rotary blade and the power train of transmission. Mechanical structure of gear train of rotary drive of conventional power tiller was simplified so that power can be transmitted directly from second shaft to tilling speed change shaft by rotating freely the transfer gear which changes the direction of rotation of shafts using needle bearing installed into middle shaft. A new gear train suitable for the single-edged rotary blade and high-speed rotary drive was developed with the rotational speed of rotary shaft faster than 7.5% at 1st-speed and 1.4% at 2nd-speed the one of conventional system by changing the numbers of teeth of gears of middle shaft, tilling speed change shaft and PTO shaft. Using the developed gear train for high-speed rotary drive, field tests were performed to compare tillage performances by the developed single-edged blade and by the conventional double-edged blade. The results showed that the performances by the single-edged blade compared with the one by the double-edged blade was improved about 18% in field capacity, about 34% in fuel consumption, and 9.4% in soil crushing ratio. Therefore, it may be concluded that tillage performance by the single-edged blade was improved compared to the one by the conventional blade. Evaluation of the developed system consisting of single-edged blade and gear train for high-speed rotary drive in field revealed that tillage performance of the developed system was similar to the one of field test conducted using the system consisting of single-edged blade and gear train for rotary drive of conventional power tiller However, considering the higher cone index of the upland field where evaluation was carried out compare to the one of the ordinary paddy field, it may be concluded that tillage performance of the developed rotary tilling system better than the one of conventional system.

• 한국소음진동공학회논문집
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• 제22권10호
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• pp.974-984
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• 2012

플랫 블레이드 와이퍼의 블레이드의 누름압 분포를 조정하여 역전과정에서 발생되는 진동을 저감하는 방법을 제시하였다. 블레이드와 유리면 사이에 길이방향으로 불균일한 누름압 분포를 도입, 고무스트립에 점진적인 역전을 유도함으로써 역전과정에서 발생하는 충격력을 저감하였다. 블레이드 내의 바디스프링 형상을 이전 연구에서 제시된 방법을 통해 구해진 형태를 적용함으로써 누름압 분포를 조정하였다. 이 방법을 적용하여 전체 길이에 균일한 누름압과 불균일한 누름압을 발생시키는 두 종류의 블레이드를 개발한 다음 누름압을 측정하여 확인하였다. 두 블레이드에서 발생하는 수직방향 및 횡방향 진동을 측정 비교한 결과, 불균일한 누름압을 가진 블레이드가 균일한 누름압의 블레이드에 비해 훨씬 작은 수직방향 진동을 나타냄을 확인하였다.

• 항공우주시스템공학회지
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• 제11권4호
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• pp.36-43
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• 2017

쿼드틸트 무인기에 적용되는 프롭로터 블레이드 형상 최적설계를 수행하였다. 형상 최적설계 프로세스 통합은 ModelCenter(R) 프로그램을 이용하였으며, 최적설계 과정에서 성능해석은 CAMRAD-II를 사용하였다. 목적함수는 제자리비행 및 전진비행 모드에서 성능효율 최대화로 설정하였으며, 제한조건은 소요 동력 및 피치로드 하중 값이 기본 형상 값보다 작게 되도록 설정하였다. 설계변수로는 블레이드 루트 코드길이, 테이퍼비, 비틀림 각의 기울기 및 각도, 하반각, 끝단 형상 생성을 위한 파라볼릭 계수, 하반각과 끝단형상이 적용되는 블레이드 스팬위치, 블레이드 단면을 구성하는 익형의 위치로 구성하였다. 최적 설계 결과 기준 형상 대비 제자리비행 효율은 1.6%, 전진 비행 효율은 13.6% 향상된 프롭로터 블레이드 형상을 도출할 수 있었으며, 피치로드 하중은 약 30% 감소하였다.

• 한국소음진동공학회논문집
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• 제23권10호
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• pp.895-901
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• 2013

Last blades of LP turbine in nuclear power plant are the highly damaged part and suffered from nozzle steam impulses during the turbine operation. Nozzle impulse is known as a common cause of damage or failure in the turbine blade and results from steam flow distortions due to uneven steam flow patterns between the stationary blade vanes. If impulse force was continuously acting on the blade for a long time, crack or wear will occur in weak parts such as root. So, it is important to know variation of nozzle impulse during the blade moving. But there is no way to measure and estimate the magnitude and direction of nozzle impulse. Therefore, this study was performed to know the variation of nozzle impulse force according to the positions of the blade and to obtain blade equivalent force and torque. This results can be used for blade stress estimation.

• 동력기계공학회지
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• 제21권1호
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• pp.70-79
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• 2017

The output power of turbine is greatly affected by the losses generated within the passage. In order to develop a better turbine or loss models, an experimental study was conducted using a linear cascade experimental apparatus. The total pressure loss and flow structures were measured at two cross-sectional planes located downstream of blade row. Measurement was conducted in a steady state for the several different locations of the blade row along the rotational direction. The blade row moved by 20 % of the pitch, and tip clearance was varied from 2% to 8%. Axial-type blades were used and its blade chord was 200mm. A square nozzle was applied and its size was $200mm{\times}200mm$. The experiment was conducted at a Reynolds number of $3{\times}10^5$ based on the chord. Nozzle flow angle sets to $65^{\circ}$ based on the axial direction and the solidity of blade row was 1.38. From the experimental results, the total pressure loss was greatly varied in the receding region than in the entering region. The flow properties within the blade passage were strongly changed according to the location of blade row.

• 대한기계학회논문집B
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• 제35권3호
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• pp.263-268
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• 2011

본 연구는 볼텍스 형태를 대신하는 원심형태의 비 막힘형 2엽 수중 슬러리 펌프 임펠러를 개발하기 위해 수행하였다. 이를 위해 먼저 펌프 설계에 있어 중요한 변수로 입구면 날개각(blade angle)과 날개 길이 각(blade length angle) $\alpha$를 선정하여 이들이 펌프의 효율에 미치는 영향을 살펴보기 위해 상용 코드인 ANSYS CFX and BladeGen을 사용하여 해석을 수행하였다. 그 결과 입구면 임펠러 날개 형상은 $\beta$값이 $30^{\circ}$ 로 일정한 값을 가질 때 가장 높은 효율을 가지게 됨을 알 수 있었으며, $\alpha$값은 효율에 비례하는 특징을 가짐을 관찰할 수 있었다.

• Journal of Biosystems Engineering
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• 제37권1호
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• pp.1-10
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• 2012

Purpose: The most important element of an agricultural helicopter is the rotor blade realizing lift force. In order to improve the performance of the rotor blades, two types (KA152313 and KB203611) of airfoils were designed and compared. Methods: The nose shape of the KB203611 airfoil was 'drooped' and 'sharp' compared to the leading edge of the KA152313 airfoil. The performance of the experimental airfoils was simulated using CFD-ACE program, and lifts were measured in situ using the 'AgroHeli-4G', a prototype helicopter. Results: Simulated lifts of the blade with the KA152313 airfoil showed proper values for a wide range of angles of attack between $14^{\circ}{\sim}18^{\circ}$, while the simulated lift of the KB203611 blade exhibited maximum values near $13^{\circ}{\sim}14^{\circ}$. In the lift measurements, the range of operable angles of attack was a collective pitch angle at the grip (GP) of $12^{\circ}{\sim}18^{\circ}$ for the KA152313 blade. On the other hand, the range of angles of attack for the KB203611 blade was a GP of $12^{\circ}{\sim}14^{\circ}$. Conclusions: The blade of KA152313 performed well over a wide range of AoAs and the blade of KB203611 performed better at low AoAs. In this study, a variative airfoil blade, gradually emerging from grip to tip using the two different airfoils, was suggested.

• 한국가시화정보학회지
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• 제8권2호
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• pp.23-30
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• 2010

Regarding the aircrafts with a rotor blade system, the miniaturization of them is limited due to the rotor blade length and the tail rotor system. To miniaturize an aircraft, an equipment is required that increases thrust and also shortens the length of the rotor blade. The present study will conduct the flow analysis for miniaturizing the aircraft by applying a duct to the coaxial rotor blade system without tail rotor. First, the verification on the calculated results was conducted through the computational flow analysis on the coaxial rotor blade system without a duct. Then, the flow analysis for the coaxial rotor blade systems was performed including Ka-60 duct, Single duct, Twin duct, and Double duct, respectively. From the numerical results, the thrust coefficient appeared higher with the duct than without a duct for the coaxial rotor blade system. Especially, in the case of Double duct, the thrust was improved due to the increase of incoming flow and the extension of the wake area. These results will be used as the basic concepts for miniaturizing the aircraft with the rotor blade system. The flow analysis on the coaxial rotor blade system including the fuselage remains as a future work.

• Wind and Structures
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• 제21권6호
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• pp.677-691
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• 2015

In this study, the geometrical setup of a turbine blade is tracked. A research-scale rotating turbine blade system is setup with a single 3-axes accelerometer mounted on one of the blades. The turbine system is rotated by a controlled motor. The tilt and rolling angles of the rotating blade under operating conditions are determined from the response measurement of the single accelerometer. Data acquisition is achieved using a prototype wireless sensing system. First, the Rodrigues' rotation formula and an optimization algorithm are used to track the blade rolling angle and pitching angles of the turbine blade system. In addition, the blade flapwise natural frequency is identified by removing the rotation-related response induced by gravity and centrifuge force. To verify the result of calculations, a covariance-driven stochastic subspace identification method (SSI-COV) is applied to the vibration measurements of the blades to determine the system natural frequencies. It is thus proven that by using a single sensor and through a series of coordinate transformations and the Rodrigues' rotation formula, the geometrical setup of the blade can be tracked and the blade flapwise vibration frequency can be determined successfully.

• Wind and Structures
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• 제26권1호
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• pp.25-34
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• 2018

This paper presents a beam finite element model of a vibrate wind blade in large elastic deformation subjected to the aerodynamic, centrifugal, gyroscopic and gravity loads. The gyroscopic loads applied to the blade are induced by her simultaneous vibration and rotation. The proposed beam finite element model is based on a simplex interpolation method and it is mainly intended to the numerical analysis of wind blades vibration in large elastic deformation. For this purpose, the theory of the sheared beams and the finite element method are combined to develop the algebraic equations system governing the three-dimensional motion of blade vibration. The applicability of the theoretical approach is elucidated through an original case study. Also, the static deformation of the used wind blade is assessed by appropriate software using a solid finite element model in order to show the effectiveness of the obtained results. To simulate the nonlinear dynamic response of wind blade, the predictor-corrector Newmark scheme is applied and the stability of numerical process is approved during a large time of blade functioning. Finally, the influence of the modified geometrical stiffness on the amplitudes and frequencies of the wind blade vibration induced by the sinusoidal excitation of gravity is analyzed.