• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.30 no.4
• /
• pp.99-105
• /
• 2002

The performance test of an axial-type turbine is carried out with various axial gap distances between the stator and rotor. The turbine is operated at the low pressure and speed, and the degree of reaction is 0.373 at the mean radius. The axial-type turbine consists of ons-stage and 3-dimensional blades. The chord length of rotor is 28.2mm and mean diameter of turbine is 257.56mm. The power of turbo-blower for input power is 30kW and mass flow rate is $340m^3$/min at 290mmAq static-pressure. The RPM and output power are controlled by a dynamometer connected directly to the turbine shaft. The axial gap distances are changed from a quarter to three times of stator axial chord length, and performance curves are obtained with 9 different axial gaps. The efficiency varies about 8% of its peak value due to the variation of axial gap on the same non-dimensional mass flow rate and RPM, and experimental results show that the optimum axial gap is 1.6-1.9Cx.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.22-29
• /
• 2011

Critical speed of high thrust liquid rocket engine turbopump is obtained through a rotordynamic analysis and a unloaded turbopump test is peformed for validation of the numerical model. The first critical speed predicted by the numerical analysis is correlated well with the test result for the bearing unloaded rotor condition only considering mass unbalance load. Using the previous rotordynamic model, critical speed variation is estimated as a function of varied bearing stiffness due to pump and turbine radial loads with relative angle difference. From the numerical analysis, it is found that the relative angle difference of pump and turbine radial loads greatly affects the critical speed. However, additional axial load reduces the effect derived from the relative angle difference of radial loads.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.16 no.4
• /
• pp.42-49
• /
• 2012

Critical speed of high thrust liquid rocket engine turbopump is obtained through a rotordynamic analysis and a unloaded turbopump test is peformed for validation of the numerical model. The first critical speed predicted by the numerical analysis is correlated well with the test result for the bearing unloaded rotor condition only considering mass unbalance load. Using the previous rotordynamic model, critical speed variation is estimated as a function of varied bearing stiffness due to pump and turbine radial loads with relative angle difference. From the numerical analysis, it is found that the relative angle difference of pump and turbine radial loads greatly affects the critical speed. However, additional axial load reduces the effect derived from the relative angle difference of radial loads.

• Proceedings of the Korean Fiber Society Conference
• /
• 2002.04a
• /
• pp.73-76
• /
• 2002

최근 링 정방기의 생산속도 증가로 인해 사절 및 사물성에 큰 영향을 미치는 정방장력의 중요성이 더욱 커지고 있다. 링 정방장력은 스핀들 회전수, 트래블러 중량, 링직경, 콥 직경 등과 같은 공정인자와 링 레일 상하운동에 따른 벌룬 높이, 얀 가이드에서의 실 굴절각도, 콥의 권취 반경 및 공기저항 등에 의해서도 영향을 받게 된다[1]. 이와 관련하여 링 정방장력 해석[2], 정방 공정인자가 정방장력에 미치는 영향[3] 및 정방 공정인자가 방적사 물성에 미치는 영향[4] 등의 연구가 많이 이루어져 왔다. (중략)

• Proceedings of the Korean Society of Precision Engineering Conference
• /
• 1993.10a
• /
• pp.622-626
• /
• 1993

비원형기어의 기본적인 특징을 몇 가지 소개하고자 한다. 첫째, 간소한 기구로서 소형화할 수 있고, 둘째, 임의의 부동속 회전 전달을 얻을 수 있으며, 셋째, 맞물린 치면의 미끄럼접촉이 적기 때문에 마모피로가 적고 넷째, 고부하 전달이 가능하다는 장점들이 있다. 본 연구의 목적은 링크, 캠과 같은 동일한 용도에서 사용되는 다른 여러 기구에 비해 많은 이점을 가지고 있는 적합한 타원계 비원형기어(엽형)에서 편평도의 변화에 따른 피치라인을설계하고, 각속비 및 편평도에 따른 형상과 길이의 변화, 물림압력각, 곡률반경등의 연구를 바탕으로 스퍼형과 헬리컬형의 타원계 엽형로타를 AOTOCAD의 script, 3dace를 이용하여 Computer Simulation를 통해 도형화한다.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
• /
• 1990.10a
• /
• pp.193-198
• /
• 1990

전자기 베어링은 기계적 접촉이 없고 전기적 제어가 가능하여 최근 고속 정 밀 회전기에 사용되고 있다. 본 논문에서는 능동 자기베어링을 모형화하고 제어 이득에 따른 계의 안정성 판별 및 응답특성의 변화를 고찰하였다. 이를 토대로 두개의 반경방향 베어링과 회전체를 제작하고 아날로그 제어회로를 구성하여 안정되게 회전체를 부상시킬수 있었으며 이로부터 계의 응답특성 을 구하였다.

• Journal of the Korean Society for Precision Engineering
• /
• v.11 no.4
• /
• pp.5-12
• /
• 1994

고속절삭을 통해서 가공능률과 가공정밀도의 향상을 도모할 수 있기 때문에, 최근에는 공작기계용 고속주축계가 많은 주목을 받고 있다. 본 연구에서는 주축 선단부에 무거운 척과 공작물이 위치하는 선반용 고속주축계의 동특성을 해석하기 위해서 유한요소법을 도입하였다. 특히 세장비가 비교적 작은 주축은 Timoshenko 이론으로, 폭이 유한한 베어링은 반경방향 외에도 모멘트방향의 강성 및 감쇠특성을 가지고 있는 것으로 모델화하였다. 그리고 선반용 고속주축계의 고유진동수와 감쇠비에 대한 주축회전수, 베어링의 지지특성, 베어링의 간격, 주축재료의 내부감쇠율 등의 영향을 고찰하였다.

• Journal of the Korea Institute of Military Science and Technology
• /
• v.6 no.4
• /
• pp.100-112
• /
• 2003

This paper presents the transient response analysis of a rotating blade in resonant frequency range. It is shown that the modeling is considered in elastic foundation and friction damping effect. The equations of motion are derived and transformed into a dimensionless form to investigate general phenomena. Numerical results show that the magnitude of friction damping to reduce maximum transient response in near the critical angular speed. The method can be applied to a number of examples of the practical rotating blade system to minimize transient response in resonant frequency range.

• Transactions of the Korean Society of Mechanical Engineers B
• /
• v.20 no.10
• /
• pp.3272-3281
• /
• 1996

The flow analysis method which had been developed for the numerical calculation of 3-dimensional, incompressible and turbulent flow within an axial compressor was extended to the flow field within centrifugal impeller. In this method based on the SIMPLE(Semi Implicit Method Pressure Linked Equations) algorithm, the coordinate transformation was adopted and the standard k-.epsilon. model using wall function was used for turbulent flow analysis. The calculated flow fields have agreed very well with measurement results. Especially, 3-dimensional and viscous flow characteristics including secondary flows, jet-wake flow and decreased pressure rise along impeller passage, which can't be predicted by inviscid Q3D calculation were predicted very reasonably.

• Transactions of the Korean Society of Mechanical Engineers B
• /
• v.25 no.10
• /
• pp.1293-1302
• /
• 2001

It is generally known that radial vane blowers with vaneless diffuser may generate mostly only a rotating stall but backward curved vane blowers may do both an impeller and a diffuser rotating stalls. In this study, it was found from the numerical and experimental results that the diffuser rotating stall does not appear in a radial vane because of the suppression for the diffuser stall appearance by occurring of impeller rotating stall in a large flow rate coefficient. The diffuser rotating stalls occurring when the width of diffuser is broaden fur a backward curved vane blower are classified definitely by the diffuser flow rate coefficient defined by adopting the varying diffuser width.