• Title, Summary, Keyword: Turbojet Engine

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Turbojet Engine Control Using Artificial Neural Network PID Controller With High Gain Observer (고이득 관측기가 적용된 터보제트엔진의 인공신경망 PID 제어기 설계)

  • Kim, Dae-Gi;Jie, Min-Seok
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.22 no.1
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    • pp.1-6
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    • 2014
  • In this paper, controller propose to prevent compressor surge and improve the transient response of the fuel flow control system of turbojet engine. Turbojet engine controller is designed by applying Artificial Neural Network PID control algorithm and make an inference by applying Levenberg-Marquartdt Error Back Propagation Algorithm. Artificial Neural Network inference results are used as the fuel flow control inputs to prevent compressor surge and flame-out for turbojet engine for UAV. High Gain Observer is used to estimate to compressor rotation speed of turbojet engine. Using MATLAB to perform computer simulations verified the performance of the proposed controller. Response characteristics pursuant to the gain were analyzed by simulation.

Surge Control of Small Turbojet Engines with Fuzzy Inference Method (소형 터보제트 엔진의 서지 제어를 위한 퍼지추론 기법)

  • Jie, Min-Seok;Hong, Seung-Beom
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.17 no.4
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    • pp.1-7
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    • 2009
  • The surge control system in unmanned turbojet engine must be capable of accounting uncertainties from engine transient conditions, random fluctuations of key parameters such as air pressure and fuel flow and engine modeling errors. In this paper, taking into consideration of its effectiveness as well as system stability, a fuzzy PI controller is proposed. The role of the fuzzy PI controller is to stabilize the unmanned aircraft upon occurring unexpected engine surge. The proposed control scheme is proved by computer simulation using a linear engine model. The simulation results on the state space model of a small turbojet engine illustrate the proposed control system achieves the desired performance.

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Firing Test of Core Engine for Pre-cooled Turbojet Engine

  • Taguchi, Hideyuki;Sato, Tetsuya;Kobayashi, Hiroaiki;Kojima, Takayuki;Fukiba, Katsuyoshi;Masaki, Daisaku;Okai, Keiichi;Fujita, Kazuhisa;Hongoh, Motoyuki;Sawai, Shujiro
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.115-121
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    • 2008
  • A core engine for pre-cooled turbojet engines is designed and its component performances are examined both by CFD analyses and experiments. The engine is designed for a flight demonstration of precooled turbojet engine cycle. The engine uses gas hydrogen as fuel. The external boundary including measurement devices is set within $23cm{\times}23cm$ of rectangular cross section, in order to install the engine downstream of the air intake. The rotation speed is 80000 rpm at design point. Mixed flow compressor is selected to attain high pressure ratio and small diameter by single stage. Reverse type main combustor is selected to reduce the engine diameter and the rotating shaft length. The temperature at main combustor is determined by the temperature limit of non-cooled turbine. High loading turbine is designed to attain high pressure ratio by single stage. The firing test of the core engine is conducted using components of small pre-cooled turbojet engine. Gas hydrogen is injected into the main burner and hot gas is generated to drive the turbine. Air flow rate of the compressor can be modulated by a variable geometry exhaust nozzle, which is connected downstream of the core engine. As a result, 75% rotation speed is attained without hazardous vibration and heat damage. Aerodynamic performances of both compressor and turbine are obtained and evaluated independently.

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Design of PID Type Fuzzy Logic Acceleration Controller for Turbojet Engine Using High-gain Observer (고이득 관측기를 이용한 터보제트 엔진의 PID 퍼지 추론 가속도 제어기 설계)

  • Jie, Min-Seok;Kim, Dae-Gi;Hong, Gyo-Young;Ahn, Dong-Man;Hong, Seung-Beom
    • Journal of Advanced Navigation Technology
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    • v.17 no.1
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    • pp.107-114
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    • 2013
  • In this paper, we propose controller to control the acceleration of unmanned aircraft turbojet engine. The high-gain observer to estimate the rotational speed of compressor is used, and the turbojet engine controller applying fuzzy heuristic techniques and PID control algorithm are designed. fuzzy PID controller produces the flow control input to prevent the surge and flame-out phenomena at the acceleration and deceleration of the turbojet engine. The standard acceleration is set and the fuel flow control is defined by the fuzzy heuristic. Computer simulations are performed using MATLAB in order to verify the performance of the proposed controller.

Performance Evaluation of Hypersonic Turbojet Experimental Aircraft Using Integrated Numerical Simulation with Pre-cooled Turbojet Engine

  • Miyamoto, Hidemasa;Matsuo, Akiko;Kojima, Takayuki;Taguchi, Hideyuki
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.671-679
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    • 2008
  • The effect of Pre-cooled Turbojet Engine installation and nozzle exhaust jet on Hypersonic Turbojet EXperimental aircraft(HYTEX aircraft) were investigated by three-dimensional numerical analyses to obtain aerodynamic characteristics of the aircraft during its in-flight condition. First, simulations of wind tunnel experiment using small scale model of the aircraft with and without the rectangular duct reproducing engine was performed at M=5.1 condition in order to validate the calculation code. Here, good agreements with experimental data were obtained regarding centerline wall pressures on the aircraft and aerodynamic coefficients of forces and moments acting on the aircraft. Next, full scale integrated analysis of the aircraft and the engine were conducted for flight Mach numbers of M=5.0, 4.0, 3.5, 3.0, and 2.0. Increasing the angle of attack $\alpha$ of the aircraft in M=5.0 flight increased the mass flow rate of the air captured at the intake due to pre-compression effect of the nose shockwave, also increasing the thrust obtained at the engine plug nozzle. Sufficient thrust for acceleration were obtained at $\alpha=3$ and 5 degrees. Increase of flight Mach number at $\alpha=0$ degrees resulted in decrease of mass flow rate captured at the engine intake, and thus decrease in thrust at the nozzle. The thrust was sufficient for acceleration at M=3.5 and lower cases. Lift force on the aircraft was increased by the integration of engine on the aircraft for all varying angles of attack or flight Mach numbers. However, the slope of lift increase when increasing flight Mach number showed decrease as flight Mach number reach to M=5.0, due to the separation shockwave at the upper surface of the aircraft. Pitch moment of the aircraft was not affected by the installation of the engines for all angles of attack at M=5.0 condition. In low Mach number cases at $\alpha=0$ degrees, installation of the engines increased the pitch moment compared to no engine configuration. Installation of the engines increased the frictional drag on the aircraft, and its percentage to the total drag ranged between 30-50% for varying angle of attack in M=5.0 flight.

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Full Rig Test and High Altitude Ignition Test of Micro Turbojet Engine Combustor (초소형 터보제트엔진 연소기의 리그시험 및 고고도 점화시험)

  • Lee, Dong-Hun;Kim, Hyung-Mo;Park, Poo-Min;You, Gyung-Won;Paeng, Ki-Suk
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.373-376
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    • 2009
  • A full rig combustor test and altitude ignition test were carried out for radial-annular combustor of micro turbojet engine. 11.2% total pressure loss and 99.85% of combustion efficiency were measured at design point of engine under sea level standard condition and $2{\sim}6$ of air excess ratio for ignition envelope was achieved on engine starting regime. Finally, A 30,000 ft high altitude ignition test was also performed and finally we found out that the developed radial-annular combustor is appropriate to micro turbojet engine.

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Development of High Performance Micro Turbojet Engine (고성능 초소형 터보제트엔진 개발)

  • Paeng, Ki-Seok;Ahn, Chul-Ju;Min, Seong-Ki;Kim, Yu-Il
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.548-551
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    • 2010
  • A 150 lbf-thrust class micro turbojet engine has been developed. The engine could be applied to power plant for small aviation vehicle such as UAV, decoy and anti-radar missile and was designed with concepts that has small size, low-cost and high performance. A prototype was manufactured and performed the ground static test and high altitude test. This paper outlines the features and layout of 150 lbf turbojet engine and also describes the design characteristics and test results of the engine and components.

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Design of Fuzzy-PID Controller for Turbojet Engine of UAV Using LabVIEW (LabVIEW를 이용한 무인항공기용 소형 터보제트 엔진의 Fuzzy-PID 제어기 설계)

  • Shin, Haeng-Cheol;Jie, Min-Seok
    • Journal of Advanced Navigation Technology
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    • v.20 no.3
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    • pp.190-195
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    • 2016
  • In this paper, Propose to prevent compressor surge and improve the transient response of the fuel flow control system of turbojet engine. Turbojet engine controller is designed by applying Fuzzy-PID control algorithm. To prevent any surge or a flame out event during the engine acceleration or deceleration, the Fuzzy-PID controller effectively controls the fuel flow input of the control system. Fuzzy-PID results are used as the fuel flow control inputs to prevent compressor surge and flame-out for turbo-jet engine and the controller is designed to converge to the desired speed quickly and safely. Using LabVIEW to perform computer simulations verified the performance of the proposed controller. Response characteristics pursuant to the gain were analyzed by simulation.

Design of PI-type Fuzzy Logic Controller for a Turbojet Engine of Unmanned Aircraft (무인 항공기용 터보 제트 엔진의 PI-구조 퍼지 추론 제어기 설계)

  • Jie, Min-Seok;Mo, Eun-Jong;Lee, Kang-Woong
    • Journal of Advanced Navigation Technology
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    • v.9 no.1
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    • pp.34-40
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    • 2005
  • In this paper we propose a turbojet engine controller of unmanned aircraft based on the Fuzzy-PI algorithm. To prevent any surge or a flame out event during the engine acceleration or deceleration, the PI-type fuzzy controller effectively controls the fuel flow input of the control system. The fuzzy inference rule made by the logarithm function of acceleration error improves the tracking error. Computer simulations applied to the linear model of a turbojet engine show that the proposed method has good tracking performance for the reference acceleration and deceleration commands.

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Development Study on Variable Nozzle For Hypersonic Air Breathing Engine

  • Kojima, Takayuki;Taguchi, Hideyuki;Kobayashi, Hiroaki;Fukiba, Katsuyoshi;Sato, Tetsuya;Hatta, Hiroshi;Goto, Ken;Koyanagi, Jun;Aoki, Takuya
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.492-498
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    • 2008
  • In this paper are described recent studies about variable nozzles, that are a rectangular type nozzle and an axisymmetric type nozzle, of the precooled turbojet engine(S-engine) which are developed for the demonstration of the key technologies for the propulsion system of the hypersonic airplane and the first stage propulsion of the TSTO space plane. For the rectangular nozzle, three types of C-shaped carbon/carbon composite cowls which includes subscale model of the precooled turbojet engine are fabricated and the fine attachment to the ramp is confirmed. For the firing of the S-engine, stainless steel cowl with concrete heat insulator are fabricated and tested for 20 sec. Axisymmetric variable plug nozzle which is made of C/C material is fabricated and pressurized by the cold flow test. The axisymmetric plug nozzle can be operative up to 0.57 MPa of nozzle inlet pressure.

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