• Title/Summary/Keyword: turbo shaft

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The Development of the Turbo Generator System with Direct Driving High Speed Generator (고속 발전기 직접 구동 방식의 터보 제너레이터 시스템 개발)

  • 노민식;박승엽
    • Journal of the Institute of Electronics Engineers of Korea SC
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    • v.40 no.6
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    • pp.87-94
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    • 2003
  • This paper presents results of the development of the turbo generator system with structure which is HSG(High Speed Generator) installed directly to gas-turbine engine. Turbo generator with a high speed motor-generator directly has many advantages aspects of weight, size, lubrication system and complexity of the system compared of conventional turbo generator system with a gear box. But because of direct high speed operation of the high speed generator, we have to need stable high speed motor driving algorithm for perfect engine ignition when engine start. Also we have to need the design of the Power conditioning unit(PCU) for converting high speed AC output power to conventional AC power or needed DC power.

A Study on Power loading Experiment & Performance Analysis for Dynamic Transient Effect of a Turbo-shaft Engine with Free Power Turbine (분리 축 가스 터빈 엔진의 동역학적 천이 효과를 고려한 성능 해석 및 부하 인가 시험에 관한 연구)

  • Kim Gyoung-du;Yang Soo-seok
    • Journal of the Korean Society of Propulsion Engineers
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    • v.8 no.3
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    • pp.17-26
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    • 2004
  • In this paper, power transmission systems converts the shaft power of a Turbo-shaft Engine with Free Power Turbine into the generator power and be composed of a method being supplied in the thrust motor driving a propellers. Being used this, Gas turbine engine works to flat rating about 110 kw (147 shp) that the thrust motor be extremely supplied from the engine of 317shp. In this test equipment, the engine is installed with the flywheel being able to the damping function when happen to the varying load between gas turbine engine output-shaft and generator. Then if the flywheel of inertial moment be not considered, the generator and motor not get the required power from the engine for raising the load. Also it is certified that the engine works the abnormal operation. Hence the flywheel of inertial moment is determined the required range to do the performance analysis with the dynamic transient from the given and tested engine data. This system is able to get the required power after a mounting test with the redesigned flywheel.

Design of Robust Feedback Controller for Turbo let Engine : Time Domain Approach (터보 젯 엔진을 위한 강인성 궤환 제어기의 설계 : 시간영역 해석)

  • 손영창;김승우;지원호
    • Journal of the Korean Society of Propulsion Engineers
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    • v.2 no.2
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    • pp.38-46
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    • 1998
  • A theoretical and an empirical application of the speed control of a single-shaft turbo-jet engine was done using an observer for Linear Quadratic Gausian(LQG) that is one of the robust control fields. Based on a general controller design with state feedback, a controller with output feedback was designed to find out a sufficient condition in finding an Asymptotic Stability After defining of the total system through the modeling of a real turbo-jet engine, a Tracking Control was carried out. Furthermore, a saturation of the control input was theoretically considered in the output feedback controller to simulate more similar real condition.

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Study of Performance Diagnostics of Turbo-Shaft Engine for SUAV Using Thermodynamic Sensitivity (열역학적 민감도를 이용한 스마트 무인기용 터보축 엔진의 성능진단 연구)

  • Lee Daewon;Roh Taeseong;Choi Dongwhan
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • v.y2005m4
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    • pp.252-255
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    • 2005
  • The operation of a gas-turbine engine gradually deteriorates the performance of its main components and often generates the defects of its components. The GPA method has been usually used for the diagnosis of the deterioration. In this study, the diagnostic code of the engine performance using the thermodynamic sensitivity between the sensed parameters and the health parameters has been developed without an application of the commercial program. The single performance deterioration of the turbo-shaft engine for SUAV has been estimated with this code.

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Performance Diagnostics with Altitude Variation of Turbo-Shaft Engine using Gas Path Analysis (GPA 기법을 적용한 터보축 엔진의 고도 변화에 따른 성능진단)

  • Lee Eun-Young;Roh Tae-Seong;Choi Dong-Whan
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2006.05a
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    • pp.218-221
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    • 2006
  • High reliability and minimization of operating cost are important problems for both engine-manufacturer and user in operation of gas-turbine engine, for which various performance diagnostics including a fault identification have been a major issue nowadays. Performance estimation in the off-design conditions, however, encounters problems of large errors and of poor convergence because of much required data to be evaluated. In this study, a diagnostics code of engine performance has been developed by using GPA(Gas Path Analysis). Quantitative performance deterioration of the turbo-shaft engine for SUAV has been estimated with altitude variation and is compared with that obtained by GSP code.

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A Study on Performance Diagnostics of Turbo-Shaft Engine Using Thermodynamic Sensitivity (열역학적 민감도를 이용한 터보축 엔진의 성능진단 연구)

  • Lee Dae-Won;Roh Tae-Seong;Choi Doeg-Whan
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2005.11a
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    • pp.289-292
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    • 2005
  • Because of accumulation of operation time, the performance of main components(compressor, combustor, turbine, etc.) come to be deteriorated in gas-turbine engine. So, high reliability and minimun of expense are important problem for engine manufacturer and user in operation of gas-turbine engine. In this study, the diagnostic code of the engine performance using the thermodynamic sensitivity between the sensed parameters and the health parameters has been developed without an application of the commercial program. The single performance deterioration of the turbo-shaft engine has been estimated with this code.

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A Study on Fault Detection of a Turboshaft Engine Using Neural Network Method

  • Kong, Chang-Duk;Ki, Ja-Young;Lee, Chang-Ho
    • International Journal of Aeronautical and Space Sciences
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    • v.9 no.1
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    • pp.100-110
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    • 2008
  • It is not easy to monitor and identify all engine faults and conditions using conventional fault detection approaches like the GPA (Gas Path Analysis) method due to the nature and complexity of the faults. This study therefore focuses on a model based diagnostic method using Neural Network algorithms proposed for fault detection on a turbo shaft engine (PW 206C) selected as the power plant for a tilt rotor type unmanned aerial vehicle (Smart UAV). The model based diagnosis should be performed by a precise performance model. However component maps for the performance model were not provided by the engine manufacturer. Therefore they were generated by a new component map generation method, namely hybrid method using system identification and genetic algorithms that identifies inversely component characteristics from limited performance deck data provided by the engine manufacturer. Performance simulations at different operating conditions were performed on the PW206C turbo shaft engine using SIMULINK. In order to train the proposed BPNN (Back Propagation Neural Network), performance data sets obtained from performance analysis results using various implanted component degradations were used. The trained NN system could reasonably detect the faulted components including the fault pattern and quantity of the study engine at various operating conditions.

A Study on Performance Diagnostics of Turbo-Shaft Engine For SUAV Using Gas Path Analysis (GPA 기법을 적용한 스마트 무인기용 터보축 엔진의 성능진단에 관한 연구)

  • Lee, Eun-Young;Roh, Tae-Seong;Choi, Dong-Whan;Lee, Chang-Ho
    • Journal of the Korean Society of Propulsion Engineers
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    • v.10 no.3
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    • pp.82-89
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    • 2006
  • Recently operation and maintenance cost of gas turbine engines has been issued as a major parameter in terms of designing and manufacturing. Accordingly, the conception that the maintenance and repair of an engine has to be conducted in assembled condition has been spreaded out. However, it is possible only if the prediction of the engine performance is clearly identified. In this study, therefore, a diagnostic code of the engine performance has been developed by using GPA(Gas Path Analysis) and Fuzzy Logic which can analyze the engine performance and estimate the health parameters. The prediction of the quantitative performance deterioration of the established model of the turbo-shaft engine for SUAV has been achieved in a satisfied level compared to that obtained by GSP code.

Development of Test Stand for Altitude Engine Test of Reciprocating Engine (왕복동 엔진의 고도성능시험을 위한 시험장치 개발)

  • Lee, KyungJae;Yang, InYoung;Kim, ChunTaek;Kim, DongSik;Baek, Cheulwoo;Yang, GyaeByung
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.563-571
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    • 2017
  • Test stand for altitude engine test of reciprocating engine was designed, manufactured and validated by preliminary test and simple calculation. These test stand designed to interface with Altitude turbo-shaft engine test facility of Korea Aerospace Research Institute. Many limiting condition for altitude test of reciprocating engine are assumed and test stand was developed to satisfy those limits. Test stand design specially focused on a altitude, Mach number and fuel temperature control for reciprocating engine altitude test with smaller air and fuel flow than turbo-shaft engine.

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Sensor Fault Detection for Small Turboshaft Engine Considering Multiple Trim Conditions (다중 트림 상태를 고려한 소형 터보샤프트 엔진의 센서 고장 검출)

  • Seong, Sang-Man;Rhee, Ihn-Seok;Ryu, Hyeok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.11a
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    • pp.192-195
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    • 2008
  • A sensor fault detection method for small turbo shaft engine considering multiple trim conditions is proposed. This engine is used in a helicopter. Firstly, under multiple trim conditions, we derive the linearized models from a nonlinear model which includes engine, rotor and feedback control loop. As a fault detection method, we adopt the Kalman filter based method. To keep continuity of estimates between the changes of trim conditions, we reconfigure the initial values of state variables at trim changes. We detect the faults with two steps that when the first filter does not alarm the faults for some sensors, the second filter is runned for other sensor. Via some simulations we show that the proposed method works well under multiple trim conditions.

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