• Tribology and Lubricants
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• 제22권4호
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• pp.211-217
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• 2006

Ring and groove wear may not be a problem in most current automotive engines. However, a small change in ring face and groove geometry can significantly affect the lubrication characteristics and ring axial motion. This in turn can cause to change inter-ring pressure, blow-by and oil consumption in an engine. Therefore, by predicting the wear of piston ring face, ring groove and cylinder bore altogether, the changed ring end gap and the changed volume of gas reservoir can be calculated. Then the excessive oil consumption can be predicted. Being based on the calculation of gas flow amount by the theory of piston ring dynamics and gas flow, and the calculation of oil film thickness and friction force by the analysis of piston ring lubrication, the calculation theory of oil amount through top ring gap into combustion chamber will be set. This is estimated as engine oil consumption. Furthermore, the wear theories of ring, groove and cylinder bore are included. Then the each amount of wear is to be obtained. The changed oil consumption caused by the new end gap and the new volume of oil reservoir around second land, can be calculated at some engine running interval. Meanwhile, the wear amount and oil consumption occurred during engine durability cycle are compared with the calculated values. Next, the calculated amount of oil consumption and wear are compared with the guideline of each part's wear and oil consumption. So, the timing of part repair and engine life cycle can be predicted in advance without performing engine durability test. The wear data of rings and grooves are obtained from three engines before and after engine durability test. The calculated wear data of each part are turn out to be at the lower bound of aver-aged test values or a little below.

• 항공우주시스템공학회지
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• 제14권1호
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• pp.62-67
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• 2020

유럽항공안전청에서는 항공기 엔진의 형식증명을 위한 감항기준으로 CS-E (Certification Specification-Engine)를 적용하고 있다. 본 감항기준에 따라 형식증명을 받기 위한 입증 항목 중에 하나는 엔진제작사(형식증명소지자)가 창정비 주기 내에 엔진의 감항성을 유지할 수 있음을 입증하는 것이다. 이에 대한 입증방법으로 엔진의 창정비 주기에서 엔진 임무 거동을 가속하여 시험할 수 있는 가속임무시험이 가장 많이 사용된다. 국내 소형민수헬기 프로그램의 일환으로 개발되는 엔진은 유럽항공안전청의 형식증명 획득을 목표로 국제 공동 개발 중에 있다. 본 연구에서는 이 엔진의 형식증명을 위해 국외 원제작사와 협력 하에 수행되는 가속임무시험에 대한 시험절차를 수립하고, 감항기준 CS-E의 해당 요건과 개발 대상 엔진의 설계 및 운용 특성을 고려한 가속임무시험 사이클을 정립하였다.

• 한국항공우주학회지
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• 제34권7호
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• pp.105-111
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• 2006

항공기 엔진은 항공기가 각종 기동을 수행하도록 추력을 발생하는 것 외에 기동 수행을 위해 작동되는 조종면에 공급될 유압계통의 동력과 각종 항전장비 작동을 위한 전기계통의 동력을 공급한다. 엔진으로부터 제공되는 동력은 엔진의 고압압축기로부터 추출되기 때문에 축마력(Horsepower Extraction, HPX)이라하며, 추출되어 제공되는 엔진 축마력이 유압계통과 전기계통에서 요구하는 요구 축마력보다 작게 되면 엔진에 과도한 부하가 걸려 엔진회전수 감소(Rollback) 및 심한 경우 실속(stall)등이 발생할 수 있다. T/A-50체계개발 동안 요구 축마력과 엔진의 공급 축마력에 대한 비교 해석을 수행하였고, 해석 결과 엔진 축마력이 요구 축마력보다 작은 것을 확인하였다. 엔진 축마력 증가를 위한 엔진 제어 스케쥴 변경이 수행되었으며, 변경된 제어 스케쥴이 장착된 엔진을 이용하여 T/A-50비행시험을 수행하였다. 비행시험 결과를 통해 해석 결과 및 변경된 제어 스케쥴의 타당성을 검증하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2017년도 제48회 춘계학술대회논문집
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• pp.79-87
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• 2017

한국형발사체(KSLV-II) 개발과 함께 지구정지궤도 발사를 위해 비추력이 높은 다단연소사이클 로켓 엔진 개발이 한국항공우주연구원에서 진행되고 있다. 다단연소사이클 로켓엔진은 한국형발사체 엔진과 달리 가스발생기를 사용하는 개방형 엔진이 아니며, 크게 예연소기, 터보펌프, 주연소기로 구성되어 있 폐쇄형 엔진이다. 기술검증시제 개발용 모델(TDM0)을 조립하여 나로우주센터의 7톤급 엔진 연소시험 설비에서 연소시험이 진행되고 있으며, 기술검증시제 모델의 연소시험은 성공적으로 수행되었다. 현재 엔진 형상의 TDM1 모델 조립과 연소시험을 위한 준비과정이 진행 중이다.

• 한국자동차공학회논문집
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• 제22권4호
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• pp.145-151
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• 2014

Modern vehicle has a lot of ECU(Electronic Control Unit) products to control many parts such as engine, transmission, brake, body and so on. ECU quality is one of important factors related to vehicle quality and driver's safety. Based on Bath-tub curve which presents failure rate during product lifetime, we designed and applied Accelerated Run-in Test into manufacturing line by simulating stress amount to ECU and developing the required software and efficient test equipment for mass production. This test makes ECU products stressed through electrical and thermal stresses under excessive driving condition, which induce potential initial failure of components in the ECU during production. The outcome until these days proved that Acceleration Run-in Test have reduced initial failure rates and increased quality of ECU products in the field outstandingly.

• 항공우주시스템공학회지
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• 제7권4호
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• pp.49-54
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• 2013

A turbopump for a 75 ton class liquid rocket engine was tested at full speed for 20 seconds using model fluid. Liquid nitrogen is used for the oxidizer pump, water for the fuel pump, and hot gas for the turbine. The non-cavitating head of pump from the turbopump assembly test showed a good agreement with that from the pump component test. The relative difference of turbine efficiency between the turbopump assembly test and the turbine component test was 0.3% only. Suction performance from the turbopump assembly test was higher than that of pump component test, which resulted from the thermodynamic effect of cavitation.

• 한국윤활학회:학술대회논문집
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• 한국윤활학회 1997년도 제26회 추계학술대회
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• pp.152-160
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• 1997

A diesel engine oil which was formulated and a commercial diesel engine oil (API CG4) made from same base oil were tested by car and analyzed of their physical, chemical and mechanical properties. The tested oil to be analyzed were sampled from engine every 1000 km until 8000 km and determined the kinematic viscosity, TAN, TBN, metal content in oil, additive depletion, antiwear property and IR analysis. From the study, both the tested oils were almost same properties for the change of TAN and TBN, but the change of kinematic viscosity of formulated oil was slightly higher than that of commercial oil. But the concentration of metal in the formulated oil, especially iron, were increased much less during test. The iron content of the commercial oil was increase rapidly from 7000 km while the formulated oil was still low. These results were conformed by the antiwear test by 4-ball wear test machine for the samples. Also for the commercial oil, the depletion factor of the Zn-DTP which was added as an antiwear property was not change any more after 7000 km. But the formulated oil was change continuously until 8000 km, which mean that the ability of wear protection of the sliding parts exists for the formulated oil. With the results which were analyzed of the properties of oils by field test, it was found that the commercial oil could be used only within 7000 km, but the formulated oil can use more than 8000 km without severe wear of the sliding parts in the diesel engine.

• 항공우주기술
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• 제9권2호
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• pp.98-104
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• 2010

대기 중의 수증기는 가스터빈엔진의 주요성능에 많은 영향을 끼친다. 습공기의 영향은 기온 및 기압이 높은 여름철 해면 고도, 높은 비행 마하수 그리고 낮은 엔진 회전수에서 이 더욱 두드러진다. 이러한 습공기 유입에 따른 가스터빈 엔진의 성능변화의 정도를 살펴보고자 가스터빈 시뮬레이션 프로그램(GSP)과 200lbf 급 초소형 터보제트 엔진의 고공환경 성능시험을 통해 습도가 엔진성능에 미치는 영향에 대하여 알아보았다. 고공환경 엔진시험을 통해, 건공기 유입에 비해 습공기 유입 시 순추력에서 2.826% 낮게, 비연료소모율에서 1.325% 높게 측정되었다.

• 대한기계학회논문집A
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• 제24권2호
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• pp.370-377
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• 2000

This paper presents a mixed-mode type ER(electro-rheological) engine mount, and its vibration control performance for a passenger vehicle is presented. The field-dependent yield stress of a transfo rmer oil-based ER fluid is empirically distilled in both shear and flow modes. This is then incorporated with the governing equation of motion of the proposed mixed-mode(shear mode plus flow mode) type engine mount. The damping force is analyzed with respect to the intensity of the electric field and design parameters such as electrode gap. Subsequently, the ER engine mount which is equivalent to the conventional hydraulic engine mount in terms of the damping level is designed and manufactured. Both computer simulation and experimental test are undertaken in order to evaluate vibration isolation performance. In addition, this performance is compared with that of the conventional hydraulic engine mount.

• 한국자동차공학회논문집
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• 제17권5호
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• pp.16-25
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• 2009

Testing engine performance using an engine dynamometer requires high technical researchers and many facilities. Nowadays, different variables of CAE program are used for identifying the engine performance instead of engine dynamometer test. This is more convenience, as it does not necessitate an abundance of engine dynamometer experiments and, in addition, produces better results. However, CAE programs also contain various variables which can affect engine performance. Those are coupled with each other, thus making it difficult to determine the effectiveness of different variables on engines. DoE (Design of Experiments) methodology is an efficient way to verify the magnitude of effectiveness on engine performance as well as making responses to be optimized at once without trial & error. This study used data from WAVE simulations, which modeled the DOHC SI engine with in-line 4 cylinders at 1500, 3000 and 4500rpm. DoE methodology is designed properly to determine the effectiveness of five variables on power, BSFC, and volumetric efficiency, as well as to find the optimal response conditions at each rpm through a minimized number of experiments. After finishing DoE process, all the results are examined concerning the reliability of test through a verification experiment.