• Title/Summary/Keyword: Afterburner

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Modeling and Simulation of O2/CH4 Gas Supply System of Afterburner for Fuel-rich Gas of Gas Generator (가스발생기의 연료과잉가스 후연소용 O2/CH4 가스 공급시스템 설계)

  • Wang, Seungwon;Lee, Kwangjin;Chung, Yonggahp;Han, Yeoungmin
    • Journal of the Korean Society of Propulsion Engineers
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    • v.18 no.2
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    • pp.86-92
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    • 2014
  • Combustion Chamber Test Facility (CCTF) to be constructed in Naro Space Center for re-burning the fuel-rich gas of gas generator have afterburner system. The afterburner system is supplied the Oxygon ($O_2$) gas and Methane ($CH_4$) gas to reduced the harmful exhaust gas. The detailed design for the planned CCTF afterburner system is simulated and analysed by AMESim program through the all of gas supply system components. Afterburner system is performed to verify the pipe size, orifice diameter, and gas supply conditions according to the total gas consumption from analysis of gas supply system.

Cause of Fuel Leakage from the Inner Piston Packing of Afterburner Fuel Pump in an Aircraft J85-GE-21 Turbojet Engine (전투기 J85-GE-21 터보제트 엔진 후기 연소기 연료펌프의 내부 피스톤 패킹 연료 누출 원인)

  • Kim, Ik-Sik;Hwang, Young-Ha;Sohn, Kyung-Suk;Lee, Jung-Hun;Kim, Sung-Uk
    • Elastomers and Composites
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    • v.49 no.4
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    • pp.305-312
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    • 2014
  • Most of military supersonic aircraft use an afterburner. It plays an important role in performing unusual duties for supersonic flight, takeoff, and combat situations. Recently, repetitive fuel leakage from the inner piston packing rubber of afterburner fuel pump in an aircraft J85-GE-21 turbojet engine has happened. These failures have only happened in one manufacturer's parts of two manufacturers. Thus, the cause of these failures was investigated through the comparative analysis for both the failed and the unfailed with two different manufacturers using various analysis methods. The failure analysis was performed using analysis methods such as swelling or swelling ratio, total sulfur content, polymer identification, loading and surface area of carbon black, and hardness. Consequently, the main cause of this failure was identified to be insufficient loading of carbon black as a reinforcing agent, together with small surface area of carbon black and somewhat low sulfur content.

Equivalence of Binary Perturbation and Afterburner LDPC Decoder (이진 섭동과 에프터버너 LDPC 복호기의 동등성)

  • Lee, Hyunjae;Baek, Eun Chong;Kim, Sang-Hyo
    • The Journal of Korean Institute of Communications and Information Sciences
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    • v.41 no.12
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    • pp.1742-1744
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    • 2016
  • In this letter, we prove equivalence of the Binary perturbation and Afterburner LDPC decoder that are proposed for improving the decoding performance in short length LDPC codes.

A GENERAL FORMULATION OF COMBUSTION INSTABILITY FOR RAMJETS AND AFTERBURNERS

  • Hyun-Gull Yoon
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 1996.11a
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    • pp.119-133
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    • 1996
  • A wave equation and a comprehensive linear combustion model are developed for ramjet and afterburner combustion instability predictions. Modal analysis is used to develop general results for frequencies and damping factors and examples of their applications are given.

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Development of High Efficiency and Low Pollutant Cogeneration Hybrid System (고효율 저공해 열병합발전 하이브리드 시스템 개발)

  • Choi, Jae-Joon;Kim, Hyouck-Ju;Chung, Dae-Hun;Park, Hwa-Choon
    • Proceedings of the SAREK Conference
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    • 2008.06a
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    • pp.1031-1035
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    • 2008
  • The importance of the more efficient cogeneration system is emphasized. Also the more clean energy is needed at recent energy system. The cogeneration system using Lean burn engine is more preferred to the system using Rich burn engine because of the electrical efficiency. Although the cogeneration system using Lean burn engine is economically preferred, because of the NOx emission level, the system using Rich burn engine with 3-way catalyst can only be used in Korea. The NOx regulation level is 50ppm at oxygen level 13%. The cogeneration hybrid system is consist of Lean burn gas engine, afterburner, boiler, economizer, DeNOx catalyst, combustion catalyst, absorption chiller, cooling tower and grid connection system. The system was accurately evaluated and the result is following ; 90% total efficiency, below 10ppm NOx, 50ppm CO, 25ppm UHC. The cogeneration hybrid system can meet the NOx level and exhaust gas regulation. It can achieve the clean combustion gas and efficient cogeneration system.

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선형 연소 불안정성 해석

  • 윤현걸
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 1997.11a
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    • pp.12-12
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    • 1997
  • 여러 가지 형태의 연소 불안정성 중에서 50-500Hz 사이에서 발생되며 길이방향 모드(longitudinal mode)로 특징이 있는 저주파수 불안정성이 램제트 혹은 재연소기(Afterburner)의 연소 불안정성에서 가장 중요한 것이라고 여겨진다. 본 논문에서는 램제트 흑은 재연소기에서 일어날 수 있는 길이 방향의 연소 불안정성을 Modal 해석법을 사용하여 수학적인 모델로 만들었다. 특히 이 모델의 선형형태는 어떤 형태든지 선형 속도에 민감한 Burning rate 모델을 사용할 수가 있어서 보다 포괄적인 형태로 만들어져 있으며, 이 모델을 이용하여 여러 가지 연소 형상과 불완전 연소 응답 등을 연구할 수 있다. 본 논문에서는 실제 연소 형상과 유사한 삼각형 모양의 연소 형상을 사용하여 기존의 다른 모델들과 비교 분석하였다.

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Application of a Turbojet Engine for Fire Extinguishing

  • Slitenko, A.F.;Kim, SooYong
    • International Journal of Aeronautical and Space Sciences
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    • v.1 no.1
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    • pp.62-69
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    • 2000
  • Present study deals with performance analysis of an inert gas generator (IGG) which can be used as effective means to suppress fire. The IGG uses a turbo-jet engine to generate inert gas for fire extinguishing. It is generally known that a less degree of oxygen content in the product of combustion will increase the effectiveness of fire extinguishing. An inert gas generator system with water injection has advantages of suffocating and cooling effects that are very important factors for fire extinguishing. Some aspects of influencing parameters, such as, air excess coefficient, compressor pressure ratio, air temperature before combustion chamber, gas temperature after combustion chamber, mass flow rate of water injection etc. on the performance of IGG system are investigated.

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Manufacturing technology of Next Generation High-Speed Air-Breathing Engines (차세대 초고속 공기흡입식 추진기관 제작기술)

  • Han, Poong-Gyoo;Oh, Myung-Hwan;Kim, Young-Soo
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.11a
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    • pp.435-436
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    • 2008
  • The manufacturing technology used for next generation high-speed air-breathing engines, such as ramjet engine, scramjet engine and so on, was classified and reviewed to check up if pre-occupied manufacturing technology in Hyundai Rotem and other Korean companies in the field of liquid rocket engines, gas turbines and afterburners can be applied for fabricating next generation air-breathing engines.

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Parametric Cycle Analysis for a Turbofan Engine with Interstage Turbine Burner (중간단계 터빈 버너(ITB) 사용 터보팬 엔진의 성능 해석)

  • Lee, Seung-Hwan;Ku, Ja-Yeo
    • Journal of Aerospace System Engineering
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    • v.3 no.4
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    • pp.19-27
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    • 2009
  • ITB(Interstage Turbine Burner) is a kind of afterburner locating between HPT(High Pressure Turbine) and LPT(Low Pressure Turbine). The objective of this study is to use the engine's design parameters as input parameters to obtain engine's performance parameters, such as specific thrust and its thrust specific fuel consumption. This study analyzes the performance of Turbofan engines with ITB and compares the performance between Turbofan engines with ITB and Turbofan engines without ITB. Results of this study can verify the advantages of Turbofan engine with ITB in term of thrust, efficiency.

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Numerical simulation of combustor afterward sprayed in hot product stream (고온기류중에 재분사된 연소기 후류의 수치해석)

  • Kim, Tae-Han;Gwon, Hyeong-Jeong
    • Transactions of the Korean Society of Mechanical Engineers B
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    • v.21 no.7
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    • pp.841-848
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    • 1997
  • Combustion of gaseous fuel combustor in a high temperature vitiated air stream was studied with computer simulation. It is for application to afterburner of gas turbine engine which the exact mechanism is not yet clarified. As the jet velocity from fuel nozzle is very high and the geometry of combustor is three dimensional complex structure, many time and money are required to have good results. To consider this demerit, it is simplified to 2-dimensional and modified with the nozzle hole area to same area of annual status. As the thickness of annual is too thin, it is to divide with the many grids for reasonable results. Accordingly, new method which injected fuel mass, momentum and energy are added to source terms of each governing conservation equation as a source terms is introduced like as two phase analysis. Reaction rate is determined by taking into account the Arrhenius reaction based on a single step reaction mechanism. It is focused to temperature and product concentration distribution at each equivalence ratio of inlet hot product.