• Journal of the Korean Society of Propulsion Engineers
• /
• v.14 no.3
• /
• pp.16-22
• /
• 2010

The gas turbine engine performance relies greatly on its component performance characteristics. Generally, engine manufacturers do not provide engine purchasers the component performance characteristics which can be obtained by lots of experimental tests at various operating conditions and big amount of expenses. In previous works the component maps have mostly been generated by scaling from a similar component map. However this scaling method has large error at off design points, specially in high altitude operation. Therefore this work proposes an inverse modeling method that can generate components maps of PT6A-67A turboprop engine using performance data provided by the engine manufacturer. In addition, evaluation can be made through comparison between performance analysis results using the performance simulation program including the generated compressor map and performance data.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 1995.11a
• /
• pp.107-114
• /
• 1995

최근 개발 중이거나 개발 예정인 항공기용 가스터빈의 종류, 현황 및 적용 기술 등을 설명하였다. 가스터빈은 군용. 민간용으로 임무 또는 목적에 따라 특성화된 엔진으로 발전되고 있으며 이러한 추세에 따라 복합사이클 엔진, 고속터보프롭엔진, 프롭팬엔진, 덕트 없는 팬엔진(UDF). 초고바이패스(VHPR)엔진, 열재생엔진 및 V/STOL용엔진 등에 대한 개발현황 및 각 주요구성품의 최신요소기술들이 설명되었다. 또한 우리나라 항공용 가스 터빈 엔진 개발 기술의 현황과 발전방향에 대해 간략히 제시하였다.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.5 no.2
• /
• pp.44-50
• /
• 2001

After modeling an aircraft turboprop engine using SIMULINK$\circledR$, performance simulation of PT6A-62 engine, which is main power plant of KT-1, was performed. For validation, performance parameters of the SIMULIINK model were compared with the simulated results by GASTURB program. It was confirm that the results by the SIMULINK model were well agreed with those by GASTURB within 1.07%, It was assumed that installation losses were bleed-air exteraction with a range from 0% to 5%, and power for accessories with a range from 0 to 20hp. In this investigation, it was found that the shafthorsepower was decreased by maxium 0.68%, but specific fuel consumption ratio was not effected nearly by these losses.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2001.11a
• /
• pp.35-36
• /
• 2001

• Journal of the Korean Society of Propulsion Engineers
• /
• v.15 no.2
• /
• pp.1-7
• /
• 2011

The UAV(Unmanned Aerial Vehicle) which is remotely operating with long endurance in high altitude must have a very reliable propulsion system. The precise fault diagnostic system of the turboprop engine as a propulsion system of this type UAV can promote reliability and availability. This work proposes a diagnostic method which can identify the faulted components from engine measuring parameter changes using Fuzzy Logic and quantify its faults from the identified fault pattern using Neural Network Algorithms. It is found by evaluation examples that the proposed diagnostic method can detect well not only single type faults but also multiple type faults.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2010.11a
• /
• pp.499-505
• /
• 2010

The UAV(Unmanned Aerial Vehicle) which is remotely operating with long endurance in high altitude must have a very reliable propulsion system. The precise fault diagnostic system of the turboprop engine as a propulsion system of this type UAV can promote reliability and availability. This work proposes a diagnostic method which can identify the faulted components from engine measuring parameter changes using Fuzzy Logic and quantify its faults from the identified fault pattern using Neural Network Algorithms. It is found by evaluation examples that the proposed diagnostic method can detect well not only single type faults but also multiple type faults.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2010.05a
• /
• pp.295-299
• /
• 2010

Recently, development and application of the condition monitoring and diagnostic system for improvement of durability and reliability and reduction of operating cost is generalized in the aircraft propulsion system. Especially, for reliable operation of the UAV which is flying in high altitude more than 40,000 ft for a long time an condition monitoring system to identify faults and degradations of its propulsion system should be needed. Therefore, this work proposes an on-line condition monitoring program using MATLAB/SIMULINK. In the development phase of the program, a engine signal generation module is used to simulate real engine measuring parameters instead of the real engine. The proposed on-line condition monitoring program was applied to a real turboprop engine to validate its application capability.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2009.11a
• /
• pp.371-377
• /
• 2009

The propulsion system of turboprop has been rarely used in the large aircraft due to the limitation of the maximum velocity of the propeller, the power limitation by the reduction gear, etc. Recently, the demand on turboprop aircraft continues to increase because of economical efficiency and environmental factors. In this paper, turboprop propulsion system which is composed of a Pratt & Whitney 127F turboprop engine and a Hamilton Standard 568F propeller was modeled by using the Gasturb11 software. The result of the performance analysis on this propulsion system model showed that the propulsion system model was evaluated to have been successfully builded.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2009.11a
• /
• pp.533-536
• /
• 2009

The power control system of Smart UAV is similar to the propeller pitch governing concept of turboprop aircraft. The pilot inputs the engine power directly and the pitch governor controls the rotational speed of proprotor. In this paper, the engine status data from ground test of Smart UAV, such as the relationship of PLA vs. Gas generator speed and power are compared with the result of engine performance calculation program.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 1999.10a
• /
• pp.24-24
• /
• 1999

소·중형 상업용 항공기나 초등 훈련기용으로 많이 이용되고 있는 터보프롭엔진의 정상상태 성능해석을 위한 프로그램을 개발하였다. 프로그램의 검증을 위하여 지상정지조건에서의 성능 및 비행마하수에 따른 출력 등을 상용 정상상태 해석 프로그램인 TURBOMARCH 해석결과와 비교하였다. 비교결과 각 구성품의 입 ·출구 온도 및 압력, 출력 등에서는 약 3%이하의 오차율을 보였으며, 마하수 변화에 따른 출력 비교에서도 최대오차율이 2.4%로 프로그램의 신뢰성을 확인하였다. 개발된 프로그램을 이용하여 비행마하수 0.2, 80% 동력터빈 회전수에서 가스발생기 회전수를 5% 간격으로 나누어 부분부하 성능해석을 수행하였으며, 동력터빈 회전수에 따른 성능해석도 수행하였다.