• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2009년도 제33회 추계학술대회논문집
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• pp.149-152
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• 2009

파이로스타터는 일종의 가스발생기로써, 내부에 충전되는 저온 고체 추진제의 연소가스를 통해 시동에 필요한 에너지를 터빈에 공급한다. 파이로스타터의 연소관에 충전된 저온 고체추진제를 연소시키기 위한 초기 에너지를 공급해 주기 위해서는 파이로스타터 및 고체추진제의 특성과 형상에 맞는 점화기 설계가 필요하다. 이에 C.B.T 시험을 수행하여 초기 연소실 내부의 충분한 압력 증가를 확보할 수 있는 점화기의 주요 설계 인자를 결정하였다. 파이로스타터의 연계연소시험을 통해 신뢰성 있는 점화 특성을 확인하였고, 점화장약 충전량에 대한 간단한 해석을 수행하였다.

• 항공우주시스템공학회지
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• 제7권1호
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• pp.8-18
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• 2013

Recently, the advanced condition monitoring methods such as the model-based method and the artificial intelligent method have been applied to maximize the availability as well as to minimize the maintenance cost of the aircraft gas turbines. Among them the non-linear GPA(Gas Path Analysis) method and the GA(Genetic Algorithms) have lots of advantages to diagnose the engines compared to other advanced condition monitoring methods such as the linear GPA, fuzzy logic and neural networks. Therefore this work applies both the non-linear GPA and the GA to diagnose AE3007 turbofan engine for an aircraft, and in case of having sensor noise and bias it is confirmed that the GA is better than the GPA through the comparison of two methods.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2002년도 춘계 학술대회논문집
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• pp.71-78
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• 2002

All modem, aerospace gas turbines must operate with hot stage gas temperature several hundreds of degrees hotter than the melting temperatures of the materials used in their construction. Complicated cooling schemes need to be employed in the combustor walls and In the high pressure turbine stages. Internal passages are cast or machined into the hot sections of aero-gas turbine engines and air from the compressor is used for cooling. In many cases, the cooling system is engineered to utilize jets of high velocity air, which impinge on the internal surfaces of the components. They are divided by Impinging cooling method and Vortex cooling method. Specially, Research of new cooling system(Vortex cooling method) that overcome inefficiency of film cooling and limitation of space. The focus of new cooling system that improve greatly cooling efficiency using quantity's cooling air which is less is set in surface heat transfer elevation. Therefore, In this study, the numerical analysis have been performed for characteristic of flow and thermal in the swirl chamber and compared with the flow field measurement by LDV. especially, for understanding of high heat transfer efficiency in vicinity of wall. we considered flow structure and mechanism of vortex and heat transfer characteristic in variation of Reynolds number.

• 한국기계가공학회지
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• 제13권6호
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• pp.1-7
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• 2014

Gas turbines for generation are operated under high temperatures, high pressures and in corrosive environments for long periods of time. This environment causes serious damage to these parts. Therefore, the material, coating, and cooling technology used with a gas turbine are important factors with regard to turbine blade development. One method that can be used to protect a product from harsh conditions is the coating technology. A turbine blade undergoes very aggressive thermal stress and experiences high-temperature fatigue. In order to reduce the surface temperature of the components and protect the blade from high-temperature flames, a thermal barrier coating (TBC) is applied to its substrate. This study confirms the applicability of an inspection system for the turbine blade coating layer using an artificial heat source.

• Advances in aircraft and spacecraft science
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• 제5권3호
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• pp.349-362
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• 2018

A non-linear numerical simulation technique for predicting the unsteady performances of an airbreathing engine is developed. The study focuses on the simulation of integrated propulsion systems, where a closer coupling is needed between the airframe and the engine dynamics. In fact, the solution of the fully unsteady flow governing equations, rather than a lumped volume gas dynamics discretization, is essential for modeling the coupling between aero-servoelastic modes and engine dynamics in highly integrated propulsion systems. This consideration holds for any propulsion system when a full separation between the fluid dynamic time-scale and engine transient cannot be appreciated, as in the case of flow instabilities (e.g., rotating stall, surge, inlet unstart), or in case of sudden external perturbations (e.g., gas ingestion). Simulations of the coupling between external and internal flow are performed. The flow around the nacelle and inside the engine ducts (i.e., air intakes, nozzles) is solved by CFD computations, whereas the flow evolution through compressor and turbine bladings is simulated by actuator disks. Shaft work balance and rotor dynamics are deduced from the estimated torque on each turbine/compressor blade row.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.84-88
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• 2008

The UAV propulsion system that will be operated for long time at more than 40,000ft altitude should have not only fuel flow minimization but also high reliability and durability. If this UAV propulsion system may have faults, it is not easy to recover the system from the abnormal, and hence an accurate diagnostic technology must be needed to keep the operational reliability. For this purpose, the development of the health monitoring system which can monitor remotely the engine condition should be required. In this study, a fuzzy trend monitoring method for detecting the engine faults including mechanical faults was proposed through analyzing performance trends of measurement data. The trend monitoring is an engine conditioning method which can find engine faults by monitoring important measuring parameters such as fuel flow, exhaust gas temperatures, rotational speeds, vibration and etc. Using engine condition database as an input to be generated by linear regression analysis of real engine instrument data, an application of the fuzzy logic in diagnostics estimated the cause of fault in each component. According to study results, it was confirmed that the proposed trend monitoring method can improve reliability and durability of the propulsion system for a long endurance UAV to be operated at medium altitude.

• 대한기계학회논문집B
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• 제36권4호
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• pp.439-447
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• 2012

출력 규모가 다른 세가지 상용 가스터빈들을 바탕으로 고체산화물 연료전지/가스터빈 하이브리드 시스템을 구성하고 성능을 비교하였다. 각 가스터빈을 사용할 때 연료전지와 가스터빈의 출력 비중 및 효율을 비교, 분석하였고 연료전지 설계온도를 변화시키면서 출력 비중의 변화와 시스템 효율 변화를 분석하였다. 수십 kW 급 소형 가스터빈을 사용한 하이브리드 시스템에서는 연료전지 온도가 변하여도 효율은 거의 변화가 없었지만 MW 급 및 수백 MW 급 등 중,대형 가스터빈을 사용하는 경우에는 연료 전지 작동온도가 높아질수록 시스템 효율이 높아짐을 확인하였다. 또한 연료전지로 공급되는 공기량을 조절하여 연료전지 출력 비중을 변화시키는 것에 대해서도 해석하였다.

• 대한기계학회논문집A
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• 제34권12호
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• pp.1909-1915
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• 2010

고온의 연소가스에서 운전되는 국내 가스터빈 부품들은 매일 기동정지를 반복함으로써 열사이클에 의해 재료특성에 변화가 발생한다. 최근 많은 가스터빈 고온부품들이 단결정 초내열 합금으로 제작되어 지지만 재료열화 예측을 통한 부품 교체와 정비에 대한 기준이 없어서 대부분 제작사에 의존하고 있는 실정이다. 본 연구에서는 향후 수명평가와 손상분석의 기초자료로 활용하기 위해 실제 운전된 가스터빈 1 단 블레이드의 열화상태를 조사하였다. 사용한 블레이드는 25,000 및 52,000 의 등가운전시간(EOH : Equivalent Operating Hour)을 가졌으며, 재질은 단결정 초내열합금인 CMSX-4 이다. 사용된 블레이드에서 직접 시험편을 채취하여 기계적특성 시험 및 미세조직을 관찰하였다.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 2005년도 추계학술대회 논문집
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• pp.192-196
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• 2005

Key part of main equipment in a gas turbine may be likely to be damaged due to operation under high temperature, high pressure, high-speed rotation, etc. Accordingly, the cost for maintenance increases and the damaged parts may cause generation to stop. The number of parts for maintenance also increases, but diagnostics technology fur the maintenance actually does not catch up with the demand. Blades are made of precipitation hardening Ni superalloy IN738 and the like for keeping hot strength. The surface of a blade is thermal-sprayed, using powder with main compositions such as Ni, Cr, Al, etc. in order to inhibit hot oxidation. Conventional regular maintenance of the coating layer of a blade is made by FPI (Fluorescent Penetrant Inspection) and MTP (Magnetic Particle Testing). Such methods, however, are complicated and take long time and also require much cost. In this study, defect diagnostics were tested for the coating layer of an industrial gas turbine blade, using an infraredthermography camera. Since the infrared thermography method can check a temperature distribution on a wide range of area by means of non-contact, it can advantageously save expenses and time as compared to conventional test methods. For the infrared thermography method, however, thermo-load must be applied onto a tested specimen and it is difficult to quantify the measured data. To solve the problems, this essay includes description about producing a specimen of a gas turbine blade (bucket), applying thermo-load onto the produced specimen, photographing thermography images by an infrared thermography camera, analyzing the thermography images, and pre-testing for analyzing defects on the coating layer of the gas turbine blade.

• 한국추진공학회지
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• 제25권4호
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• pp.71-77
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• 2021

가스터빈 블레이드를 고온의 주유동으로부터 보호하기 위해 다양한 냉각 기법이 연구되었고, 팬 형상 홀을 포함한 다양한 막냉각 홀 형상에 대해서도 연구가 수행되어왔다. 하지만, 소형 가스터빈에 대한 수요가 증가함에 따라 얇은 벽에 적용할 수 있는 막냉각 홀에 대한 연구가 필요하다. 이에 따라 본 연구에서는 수치해석을 통하여 분사율 1과 2에서 팬 형상 홀의 형상 변수의 영향을 연구하였다. 또한, 원형부 길이와 전방향 및 횡방향 확장각, 세 가지 변수에 대하여 최적화를 수행하였다. 각 분사율에서 최적화된 두 형상은 유사한 형상 변수와 냉각 성능을 갖는 것으로 나타났다.