• Title, Summary, Keyword: 터보제트 엔진

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Performance Characteristics of a TBCC Engine with Turbo-Ramjet Engine Transition Mode (터보제트-램제트 엔진의 천이모드를 고려한 TBCC 엔진의 성능 특성)

  • Moon, Kyoo-Hwan;Sung, Hong-Gye
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.44 no.2
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    • pp.116-122
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    • 2016
  • The performance characteristics of a TBCC engine considering the transition mode from a turbojet to a ramjet engine has been investigated. The performance of each engine was proposed and a transition mode of the TBCC engine has been evaluated by adjusting the operating rate of the ramjet engine and turbojet engine performance changes continuously. Based on the transition model, it was confirmed that the performance is continuously changed at various flight Mach numbers and altitudes. The performance characteristics including thrust and specific impulse considering various flight conditions and transition mode were analyzed, which testifies characteristics of the engine itself, as well as transition of the combined cycle.

항공기용 원동기의 연구개발 동향

  • 임달연
    • Journal of the KSME
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    • v.29 no.6
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    • pp.594-600
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    • 1989
  • 항공기용 원동기는 항공기를 추진시키기 위한 동력장치이다. 항공기가 추진력을 얻기 위해서는 프로펠러를 회전시켜 대량의 공기를 뒤로 가속시켜 그 반작용을 이용하는 방법과, 단순히 배기 가스를 뒤로 고속분사시켜 그 반작용을 이용하는 방법이 있다. 피스톤 엔진은 전자를, 터보 제트 엔진은 후자를 대표하고 있는데 두 가지 방법을 절충하여 터빈으로 프로펠러를 회전시키는 터보 프롭엔진과, 헬리콥터의 로우터를 회전시키는 터보 샤프트 엔진도 있다. 또 터보 제트 엔진과 터보 프롭 엔진의 증간성능을 꾀한 터보 팬 엔진이 있는데 효율이 아주 좋기 때문에 급속히 발 전되어 항공기용 원동기의 대명사격으로 현재 군용이나 민간기용으로 널리 사용되고 있다. 최 근에는 터보팬 엔진과 터보 프롭 엔진을 절충한 새로운 터보 프롭 APT (advanced turbo prop) 엔진의 실용화가 추진되고 있다. 이상과 같은 종류의 엔진 이외에도 항공기용 원동기에는 극히 제한된 용도에 쓰이는 램 제트와 펄스 제트 엔진 그리고 로켓 엔진 등이 있다. 원동기는 그 용 도에 따라 개발, 활용되는 것이기 때문에 오랜 역사를 지닌 피스톤 엔진은 아직까지도 경항공 기용 원동기의 주류를 이루고 있고, 앞으로도 터보 프롭 엔진과 더불어 나름대로 계속 활용될 것으로 전망된다.

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TBCC Engine Performance Design Technique of Reusable Launch Vehicle (재사용 우주 발사체의 TBCC 엔진 성능 설계 기법)

  • Kim, Sung-Jin;Sung, Hong-Gye
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.167-170
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    • 2008
  • A TBCC(Turbine Based Combined Cycle) engine performance design method for reusable launch vehicles flying both in subsonic and supersonic regime was proposed. The TBCC consists of turbo jet engines and ramjet engines, operating individually or together according to operation schedule. The performance scheme of turbojet and ramjet was validated and the combined engine performance of the TBCC at a typical flight condition was analyzed.

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Development of a 65hp, Twin-Spool, Mini-Turboshaft Engine Core for UAV (UAV용 65마력급 초소형 분리축 터보샤프트 엔진 코어 개발)

  • 이시우;김경수;이기호;김승우
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.253-256
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    • 2003
  • The engine core of a 65hp-turboshaft engine for UAV is developed and modified into a 55lbf-turbojet engine. Since the core engine is installed with a propelling nozzle, which has the same mass flow characteristics as the power generator of the turboshaft engine its mechanical and aerodynamic characteristics are basically the same as those of the complete engine. Engine output is not shaft power but thrust force that is easier to measure. The core engine is very useful for core test purpose. Besides, the core engine itself can be directly used for propulsion of small air vehicles.

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읽을거리 - 미래를 주도하는 첨단 항공우주기술(17) - 개방형 회전날개 엔진(Open Rotor engine)

  • 한국항공우주산업진흥협회
    • Aerospace Industry
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    • pp.70-71
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    • 2010
  • 항공기술의 급격한 발전과 함께 터보제트 엔진의 상용화는 회전날개가 외부로 돌출된 터보프롭 엔진을 과거의 것으로 만들었다 그러나 지구온난화와 같은 환경문제와 유가 상승과 같은 여러 문제가 복합적으로 작용하면서 터보제트 엔진과 터보프롭 엔진의 장점을 접목시킨 개방형 회전날개 엔진이 21세기 첨단 항공우주 기술로 새롭게 주목받고 있다. 향후 상용화될 경우 항공분야 전반에 엄청난 영향을 미칠 것으로 예상되는 개방형 회전날개 엔진에 대해 알아본다.

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An Experimental Study of the Infrared Signal for Exhaust Plume with Bypass Ratio (바이패스비에 따른 배기가스의 적외선 신호측정 실험연구)

  • Joo, Milee;Jo, Sungpil;Choi, Seongman;Jo, Hana
    • Journal of the Korean Society of Propulsion Engineers
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    • v.23 no.5
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    • pp.1-9
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    • 2019
  • Infrared signal and exhaust gas temperature distribution with bypass ratio were measured using a micro turbojet engine. Micro turbojet engine was modified to simulate the turbofan engine behaviour. Core flow was simulated using the jet flow of the micro turbojet engine, and high-pressure air was supplied to its external duct to simulate bypass flow. The effects of bypass ratios (0.5, 1.0, and 1.4) were examined. The experimental results indicate that the infrared signal decreases as the bypass ratio increases. And also gas temperature decreases with bypass ratios. Additionally, Schlieren visualization of the exhaust gas plume was conducted. From the exhaust gas temperature distribution and Schlieren images, the structure of jet plume with various bypass ratios was understood.

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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Fuel Flow Control of Turbojet Engine Using the Fuzzy PI+D Controller (퍼지 PI+D 제어기를 이용한 터보제트 엔진의 연료유량 제어)

  • Jung, Byeong-In;Jie, Min-Seok
    • Journal of Advanced Navigation Technology
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    • v.15 no.3
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    • pp.449-455
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    • 2011
  • In this paper, Proposed controller prevent compressor surge and reduce the acceleration time of the fuel flow control system for turbo-jet engine. Turbo-jet engine controller is designed by applying fuzzy PI+D control algorithm and make an inference by applying Mamdani's inference method and the defuzzification using the center of gravity method. Fuzzy inference 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 MATLAB to perform computer simulations verified the performance of the proposed controller.

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.