• Journal of Advanced Marine Engineering and Technology
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• 제29권6호
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• pp.671-677
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• 2005

In internal combustion engines the usual material for the cylinder liner is because of its good wear resistance Apparently this wear resistance arises from the at iron to form a hard glazed surface when under sliding friction. When the cylinder liner wear limits, it shall be replace with new one according to the classification soci manufacturer's standards. However, adoption of alternative repairing method such a metalizing, thermo plastic deformation process became inevitable taking enormous cost renewal into consideration. In this paper. the material properties of cylinder liner of grey discussed on the basis of the results of experimental work of the thermo plastic deformation the worn out cylinder liner made of grey cast iron.

• 한국자동차공학회논문집
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• 제14권1호
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• pp.31-38
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• 2006

Cylinder liner rotation is a new concept for reducing piston assembly friction in the internal combustion engine. The purpose of cylinder liner rotation is to reduce the occurrence of boundary and mixed lubrication friction in the piston assembly. This paper reports the results of experiments to quantify the potential of the rotating liner engine. A GM Quad-4 SI engine was converted to single cylinder operation and modified for cylinder liner rotation. The hot motoring method was used to compare the friction loss between the baseline engine and the rotating liner engine. Additionally, tear-down tests were used to measure the contribution of each engine component to the total friction torque. The cycle-averaged motoring torque of the RLE represents a $23\~31\%$ friction reduction compared to the baseline engine for hot motoring tests. Through tear down tests, it was found that the piston assembly friction of the baseline engine is reduced from $90\%$ at 1200 rpm to $71\%$ at 2000 rpm through liner rotation.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2000년도 추계학술대회논문집B
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• pp.142-149
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• 2000

The results of stand and field testing of a combustion chamber for a heavy-duty 150 MW gas turbine are discussed. The model represented one of 14 identical segments of a tubular multican combustor constructed in the scale 1:1. The model experiments were executed at a pressure smaller than in the real gas turbine. The combustion efficiency, pressure loss factor, pattern factor, liner wall temperature, flame radiation, fluctuating pressure, and NOx emission were measured at partial and full load for both model and on-site testing. The comparison of these items of information, received on similar modes in the stand and field tests, has allowed the development of a method of calculation and the improvement of gas turbine combustors.

• 한국추진공학회지
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• 제6권2호
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• pp.19-27
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• 2002

가스 발생기 추진기관 시스템에서는 연소 시 굵은 입자가 토출되면 치명적인 문제가 된다. 이러한 문제를 해결하기 위해서는 추진제에 발생하는 연소가스 입자와 더불어 라이너에서 발생되는 연소가스 입자를 최소로 하는 방안이 필요하다. 이러한 라이너 조성을 개발하기 위하여 충전제로 옥사마이드(Oxamide)를 사용하고, HTPB계 바인더를 사용한 무연 라이너 조성을 개발하였다. 라이너의 연기특성을 정량적으로 측정하기 위하여 자체 제작한 연기측정장치(Smoke Chamber)를 사용하였다. 충전제로 옥사마이드를 50%적용하였을 때가 실리카(Silica)를 50%적용 시에 비하여 연기 정도가 1/10정도로 감소하였으며 그 결과는 가스 발생기 추진기관의 연소 시험 시에도 확실하게 관찰되었다.

• Advances in materials Research
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• 제8권2호
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• pp.117-135
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• 2019

The lifetime of a gas turbine combustor is typically limited by the durability of its liner, the structure that encloses the high-temperature combustion products. The primary objective of the combustor thermal design process is to ensure that the liner temperatures do not exceed a maximum value set by material limits. Liner temperatures exceeding these limits hasten the onset of cracking which increase the frequency of unscheduled engine removals and cause the maintenance and repair costs of the engine to increase. Hot gas temperature prediction can be considered a preliminary step for combustor liner temperature prediction which can make a suitable view of combustion chamber conditions. In this study, the temperature distribution of ceramic panels for a V94.2 gas turbine combustor subjected to realistic operation conditions is presented using three-dimensional finite difference method. A simplified model of alumina ceramic is used to obtain the temperature distribution. The external thermal loads consist of convection and radiation heat transfers are considered that these loads are applied to flat segmented panel on hot side and forced convection cooling on the other side. First the temperatures of hot and cold sides of ceramic are calculated. Then, the thermal boundary conditions of all other ceramic sides are estimated by the field observations. Finally, the temperature distributions of ceramic panels for a V94.2 gas turbine combustor are computed by MATLAB software. The results show that the gas emissivity for diffusion mode is more than premix therefore the radiation heat flux and temperature will be more. The results of this work are validated by ANSYS and ABAQUS softwares. It is showed that there is a good agreement between all results.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2017년도 제48회 춘계학술대회논문집
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• pp.254-257
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• 2017

본 논문에서는 항공 가스 터빈용 연소기 개발을 위한 단일 연소기 섹터 시험 결과에 대한 논의하였다. 연소기로 공급되는 전체 공기 중 주 연소 영역으로 공급되는 공기비율을 변화 시키면서 배출물 농도, 라이너 표면 온도 분포 및 연소기 출구 온도 패턴 등의 연소 성능 변화를 연구하였다. 주 연소 공기량이 증가함에 따라 CO와 NOx 배출 농도가 증가하는 경향이 있었으며, 연소기 출구 패턴은 개선되는 것으로 나타났다. 희석 공기공을 회전시켜 배치하는 경우 연소기 출구 온도 패턴의 변화가 민감하게 변하는 것을 확인하였다. 이러한 연구 결과는 연소기의 효율, 내구성 및 배출물 감소 성능을 고려한 연소기 라이너 설계 최적화 과정의 기초 자료로 활용할 예정이다.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2012년도 제45회 KOSCO SYMPOSIUM 초록집
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• pp.59-60
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• 2012

This paper describes gas turbine combustion characteristics of synthetic gas which is mainly composed of hydrogen and carbon monoxide. The combustion characteristics such as combustion instability, NOx and CO emission, temperatures at turbine inlet, liner and dump plane, and flame structure were investigated when changing when changing $H_2:CO$ ratio, dilution ratio, and $CH_4:syngas$ ratio. From the results, quantitative relationships are derived between key aspects of combustion performance, notably NOx emission. It is concluded that NOx emission of syngas is strongly influenced by the diluent heat capacity and combustion instability. Moreover, NOx control method using diluents such as $N_2$, $CO_2$, steam is verified.

• 대한기계학회논문집A
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• 제26권8호
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• pp.1608-1614
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• 2002

This Paper presents a novel piston friction force measurement system that has characteristics of relieving the Pressure force acting on the upper surface of the liner; the system uses general rubber O-rings for combustion chamber sealing, and does not need special changes to the piston top land. The lower supporter of the floating liner increases stiffness in liner axial direction, and results in the increase of natural frequency. The upper supporter has multi-layer structure designed fer low axial stiffness and high radial stiffness. With the use of the present system, the effects of variation in clearance and piston ring tension were studied.

• 한국자동차공학회논문집
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• 제8권3호
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• pp.1-11
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• 2000

Instantaneous temperature probes were manufactured by pressing method. By using these probes, the instantaneous surface temperature and unsteady heat flux in the cylinder liner of DOHC engine were measured. The main results are as follows; ⅰ) the instantaneous surface temperature of cylinder liner are affected by the contact of piston ring as well as burning gas. ⅱ) the wall temperature of the siamese portion is much higher than other parts. ⅲ) it was shown that the rising trend of heat flux by burning gas are nearly limited to the 1/2-stroke distance from the top of cylinder liner.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2007년도 제29회 추계학술대회논문집
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• pp.170-173
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• 2007

본 연구에서는 액체로켓엔진 내부에 라이너를 설치하고 기체 질소를 이용한 막냉각 방법을 사용하여, 라이너의 막냉각 특성을 살펴보았다. 고온 가스는 액체로켓 연소가스와 액체질소를 혼합하여 사용하였다. 기존의 액체로켓엔진 시험 설비에 추가적으로 라이너 냉각 기체를 공급 설비를 구축하였으며, 라이너 및 냉각 기체 공급부를 제작하였다. 10초 연소 실험을 통해 라이너 내부 고온 가스의 온도와 라이너 외부 벽면 온도를 측정하였으며, 기체 질소에 의한 라이너 냉각 특성을 확인하였다.