• Title/Summary/Keyword: Full-scale Combustor

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The Design and Hot-firing Tests of a regenerative-cooled Sub-scale Combustor (재생냉각 축소형 연소기의 설계 및 연소시험)

  • Lee, Kwang-Jin;Kim, Jong-Gyu;Lim, Byoung-Jik;Kim, Hong-Jip;Seo, Seong-Hyeon;Han, Yeoung-Min;Choi, Hwan-Seok
    • Aerospace Engineering and Technology
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    • v.6 no.2
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    • pp.141-149
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    • 2007
  • It was carried out hot-firing test with a regenerative-cooled sub-scale combustor which was applied regenerative-cooling, film cooling and thermal barrier coating. Test results showed that cooling methods used in the combustor play an full role in the operation of the combustor under the design condition but it is occurred high frequency combustion instability due to unsteady flow of fuel by structural support ring inserted in fuel manifold. The flow pattern of fuel was improved by excluding the ring and it will be carried out additional hot-firing test to verify the combustion stability of modified combustor.

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Thermo-Structural Survivability Evaluation of a Thrust-Measuring Nozzle Extension in a Full-scale Combustor (실물형 연소기의 추력측정용 노즐확장부에 대한 열/구조적 건전성 평가)

  • Kim, Hong-Jip;Choi, Hwan-Seok
    • Journal of the Korean Society of Propulsion Engineers
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    • v.13 no.6
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    • pp.17-23
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    • 2009
  • The survivability of the temporary nozzle extension for an accurate thrust measurement in a full-scaled combustor has been investigated through thermal analyses. The effects of nozzle extension materials and the thickness of thermal barrier coating (TBC) have been elucidated. It has been found that thermal survivability cannot be guaranteed without TBC. The maximum temperature of the nozzle extension decreased with increasing TBC thickness. For hot firing tests, the TBC is thought to be indispensable to the thermo-structural survivability of the nozzle extension made of steel.

Characteristics of Unielement Injector Combustion with Flow rates and Chamber Pressures (유량 및 연소압에 따른 액체로켓 단위분사기 연소특성 변화)

  • Moon Il-Yoon;Kim Jong-Gyu;Han Yeoung-Min;Yoo Jin;Lee Yang-Seok;Ko Young-Sung
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2005.11a
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    • pp.247-250
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    • 2005
  • In the case of appling a unielement injector developed for a full scale liquid rocket combustor, a operating condition or configuration of the injector is changed by combustion pressure, arrangement and injector quantity of a full scale liquid rocket combustor. In order to verify application, swirl coaxial injectors propelled by jet-A1 and liquid oxygen are tested at different conditions of a combustion pressure, a flowrate and an injector length. As a test result, the application of the present swirl coaxial injectors is excellent because an efficiency of a characteristic velocity is increased at the each test condition beyond that variation of dynamic pressure intensity is small.

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Large Eddy Simulation of Turbulent Combustion Flow Based on 2-scaler flamelet approach

  • Oshima, Nobuyuki;Tominaga, Takuji
    • 한국전산유체공학회:학술대회논문집
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    • 2006.10a
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    • pp.18-21
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    • 2006
  • This paper investigates LES of turbulent combustion flow based on 2-scalar flamelet approach, where a G-equation and a conserved scalar equation simulate a propagation of premixed flame and a diffusion combustion process, respectively. The turbulent SGS modeling on these flamelet combustion approach is also researched. These LES models are applied to an industrial flows in a full scale gasturbine combustor with premixed and non-premixed flames. The numerical results predict the characteristics of experiment temperature profiles. Unsteady features of complex flames in combustor are also visualized.

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Performance Test of Combustor for Aeropropulsion Gasturbine Engine (항공추진용 가스터빈엔진 연소기 성능시험)

  • Park, Poo-Min;Kim, Hyung-Mo;Choi, Young-Ho;Jeon, Byoung-Ho;Yang, Su-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.11a
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    • pp.405-406
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    • 2008
  • Combustor is one of the major component of gas turbine engine and its development is done mostly by performance test. Combustors for aviation gasturbine engines has been successfully tested at the test facility in KARI as well as for stationary gasturbine engines. Full scale combustor test requires large amount of high temperature and pressure air, so the test facility is equipped with big air compressor and heater.

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Design of Full-Scale Combustion Chamber of Liquid Rocket Engine for Ground Hot Firing Tests (지상연소시험용 실물형 고압 연소기의 설계)

  • Han Yeoungmin;Kim Seunghan;Seo Seonghyeon;Cho Wonkook;Choi Hwanseok;Seol Wooseok;Lee Sooyong
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • v.y2005m4
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    • pp.299-304
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    • 2005
  • The design procedures of full-scale combustion chamber with chamber pressure of 53bara, mass flow rate of 90kg/s, combustion efficiency of $94\%$ and specific impulse at ground of 253sec were described. The details of combustion performance and geometrical parameters were also given. Full-scale combustion chamber consists of the combustor head with injector/baffle and the chamber/nozzle with regenerative cooling channels. The design results of combustion chamber with ablative materials, detachable injector head with SUS baffle or baffle injector and chamber body for ground hot firing tests were given in this paper.

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A study on prediction of propellant distribution of single swirl coaxial injector in gas generator (가스발생기용 단일 스월 동축형 분사기의 추진제 분포 예측에 관한 기법 연구)

  • Kim Jong-Gyu;Kim In-Tae;Han Yeoung-Min;Seol Woo-Seok;Lee Kwang-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2004.10a
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    • pp.205-209
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    • 2004
  • The configuration and arrangement of injector in LRE gas generator and combustor have a great impact on combustion process and heat exchange because of affecting atomization, vaporization, mixing and chemical reaction. A relation between injector array and mixing distribution of propellants based on a physical approach was investigated in this study. Programming method of this relation is used to predict mixing distribution of propellants. Simplicity of physical approach and various assumptions make it reduce the accuracy and application of the results of present study. But, this method is very useful to predict the mixing distribution of full scale combustor due to difficulties in cold flow testing.

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Experimental Study on the Combustion Stability of Full Scale Rocket Combustor (실물형 액체로켓 연소기의 연소안정성에 대한 시험적인 고찰)

  • Lee Kwang-Jin;Seo Seong-Hyeon;Kang Dong-Hyeuk;Song Ju-Young;Lim Byoung-Jik;Han Yeoung-Min
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2005.11a
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    • pp.240-246
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    • 2005
  • A series of combustion tests of a 30-tonf-class full scale liquid rocket thrust chamber under development has been carried out to verify its design. The test results revealed decent performance in the aspects of efficiency. The combustion stability is one of the most important parameters of liquid rocket engine in addition to the efficiency. Assessment tests of combustion stability must be accomplished to confirm the possibility of combustion instability due to spontaneous or external disturbances. The combustion stability rating tests of the full scale thrust chamber with temporary baffles made of stainless steel were carried out utilizing pulse guns to estimate combustion stability characteristics. The tests results show highly stable combustion stability characteristics. The outcome acquired from the present experimental study will be used to design an actively cooled baffle that can survive for the life time operation of the thrust chamber.

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M4 Semi-Freejet Test with Full-scale Vehicle Model (실기체급 비행체 모델에 대한 M4 준자유류 시험)

  • Juhyun Bae;Changwon Lim;Hojin Choi;Sangwook Jin;Jeongwoo Kim
    • Journal of the Korean Society of Propulsion Engineers
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    • v.26 no.5
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    • pp.63-73
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    • 2022
  • Investigation on operation of the test apparatus for the M4 semi-freejet tests with a full-scale vehicle model was carried out utilizing domestic facilities. An integrated design of the experimental apparatus and the vehicle model was obtained through iterative computational fluid dynamics (CFD) analysis. The test results showed that the M4 nozzle of the apparatus was fully expanded to provide required test conditions. It was also found that the intake of the vehicle model successfully started, and the corresponding shadowgraph images were recorded during the test. A variable nozzle of the model was set to adjust the back pressure of the model combustor, and wall-static pressures were measured to obtain the pressure distribution at the main locations of the model. The flame of torch ignitors and pilot fuel ignition were observed in a flame-holder of the combustor.

Combustion Test of Regenerative Cooling Combustor for Liquid Rocket Engine (실물형 재생냉각 액체로켓엔진 연소기(확대비3.5) 연소시험)

  • Yang, Seung-Ho;Kim, Hee-Tea;Kang, Dong-Hyuk;Ahn, Kyu-Bok;Seo, Seong-Hyeon;Han, Yeoung-Min;Choi, Hwan-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2007.11a
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    • pp.125-130
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    • 2007
  • Firing tests have been performed for a 30 tonf-class full-scale regeneratively cooled combustion chamber. It was the first model which has welded construction of the injection head and the combustion chamber. A number of firing tests have been performed to evaluate combustion efficiency, regenerative cooling performance and durability of the combustor. This paper describes the results of firing tests performed at the design and off-design conditions which correspond to the chamber pressure of 60 bar, 68 bar respectively and the O/F ratio of 2.5 and 2.8 respectively. The data at each test condition have provided successful results in terms of combustion performance, combustion stability and durability. The tests are considered to be quite meaningful in the sense that the technologies for kerosene regeneratively cooled combustion chamber are successfully proven.

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