• Title/Summary/Keyword: 토치 점화장치

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Combustion Characteristics of Orifice Size of Torch in a CVCC (토치 점화 장치의 오리피스 직경에 따른 연소특성 파악)

  • Kwon, Soon-Tae;Kim, Hyeong-Sig;Choi, Chang-Hyeon;Park, Chan-Jun;Ohm, In-Young
    • Proceedings of the Korea Society for Energy Engineering kosee Conference
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    • 2010.04a
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    • pp.59-63
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    • 2010
  • Seven different size of orifice were applied in a constant volume combustion chamber for evaluating the effects of torch-ignition on combustion. The initial flame development and flame propagation were analyzed by the mass fraction burn and combustion enhancement rate. The combustion pressures were measured to calculate the mass fraction burn and the combustion enhancement rates. In addition, the flame propagations were visualized by the shadowgraph method for the qualitative comparison. The result showed that the combustion pressure and mass burned fraction were increased when using the torch-ignition device. The combustion enhancement rates of torch-ignition cases were improved in comparison with conventional spark ignition. Finally, the visualization results showed that the torch-ignition induced faster burn than conventional spark ignition due to the earlier transition to turbulent flame and larger flame surface, during the initial stage.

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Combustion Characteristics of Volume Variation of Torch in a CVCC (토치 점화 장치의 체적에 따른 연소특성 파악)

  • Kwon, Soon-Tae;Kim, Hyeong-Sig;Choi, Chang-Hyeon;Park, Chan-Jun;Ohm, In-Young
    • Proceedings of the Korea Society for Energy Engineering kosee Conference
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    • 2010.04a
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    • pp.166-170
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    • 2010
  • Six different size of torch-ignition device were applied in a constant volume combustion chamber for evaluating the effects of torch-ignition on combustion. The torch-ignition device was designed six different volumes and same orifice size. The combustion pressures were measured to calculate the mass burn fraction and combustion enhancement rate. In addition, the flame propagations were visualized by shadowgraph method for the qualitative comparison. The result showed that the combustion pressure and mass burn fraction were increased when using the torch ignition device. And the combustion duration were decreased. The combustion enhancement rates of torch-ignition cases were improved in comparison with conventional spark ignition. Finally, the visualization results showed that the torch-ignition device the torch-ignition induced faster burn than conventional spark ignition due to the earlier transition to turbulent flame and larger flame surface, during the initial stage. And the initial flame propagation was effected torch-ignition volume.

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Forced Ignition Characteristics with a Plasma Jet Torch in Supersonic Flow (초음속 유동장 내 플라즈마 토치를 사용한 강제 점화 특성)

  • Kim, Chae-Hyoung;Jeung, In-Secuk;Choi, Byoung-Il;Kouchi, Toshinori;Masuya, Goro
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.04a
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    • pp.363-366
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    • 2011
  • Mixing and combustion experiments with a vent slot mixer were performed in Mach 2 supersonic wind tunnel. Helium and hydrogen gases each were used for the mixing and the combustion experiment with a plasma jet (PJ) torch. The vent slot mixer holds plenty of fuel in the downstream mixing region, even though the fuel is transversely injected. In case of the combustion, the injected fuel is ignited by the PJ torch, and then unburned mixture is burned by shock-induced combustion downstream. Thermal choking in the combustor leads to shock trains in the isolator, causing the unstable combustion.

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A Mixing Head Integrated, Multi-Ignition Device for Liquid Methane Engine (액체메탄엔진용 믹싱헤드 일체형 다중점화장치)

  • Lim, Byoungjik;Lee, Junseong;Lee, Keejoo;Park, Jaesung
    • Journal of the Korean Society of Propulsion Engineers
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    • v.26 no.3
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    • pp.54-65
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    • 2022
  • We are developing a compact ignition device that can provide a multi-ignition capability for an upper stage methane engine of a two staged small satellite launch vehicle. Firstly, the multi-ignition device is designed and built as an integral part of an additively manufactured mixing head. Secondly, the ignition device requires no separate high-pressure vessels to store ignition propellants as they are branched out from the main feed lines for the mixing head. We performed experiments at various levels, including igniter autonomous tests, thrust chamber ignition and combustion tests on the new compact ignition device which is integrated in the thrust chamber of one-tonf class liquid oxygen/liquid methane engine, and confirmed stable ignition performance.

Flmae Visualization of the sector combustor (분할연소기의 화염 가시화 연구)

  • Kim, Bo-Ra-Mi;Choi, Chea-Hong;Kim, Chun-Taek;Choi, Seong-Man
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.11a
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    • pp.213-216
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    • 2009
  • In order to see the flame behavior in the gas turbine combustor, combustion test was performed by using sector combustor. Ignition test with torch ignition system was carried out at the various combustor inlet velocity and air fuel ratio. Also, flame blow out limit was measured by changing fuel flow rate with fixed air mass flow rate. In the test results, stable ignition is possible at air excess ratio of 6 and this limit is gradually increased with combustor inlet air velocity. The minimum blow out limit is about 4 at 40 m/s of combustor inlet velocity. This blow out limit is also increased up to about 10 with increasing combustor inlet velocity.

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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.

A Study of Flame Visualization of the APU Gas Turbine Engine Sector Combustor (APU용 가스터빈 엔진 분할연소기의 화염가시화 연구)

  • Kim, Bo-Ra-Mi;Choi, Chea-Hong;Choi, Seong-Man
    • Journal of the Korean Society of Propulsion Engineers
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    • v.15 no.4
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    • pp.11-17
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    • 2011
  • In order to see flame behavior in the annular reverse gas turbine combustor, sector combustion test was performed. Ignition test by using torch ignition system was carried out at various combustor inlet velocity and air fuel ratio. Also, flame blow out limit was measured by changing fuel flow rate with constant air mass flow rate. In test results, stable ignition is possible at air excess ratio of 6 and this limit is gradually increased with combustor inlet velocity. The minimum blow out limit is about 4 at 40 m/s of combustor inlet velocity. This blow out limit is also increased up to about 10 with increasing combustor inlet velocity. Test result shows that lean blow out limits are increased with air velocity. The highest blow out limit was found at the combustor inlet velocity of 65 m/s.

A Study of Flame Visualization of the APU Gas Turbine Engine Sector Combustor (APU용 가스터빈 엔진 분할연소기의 화염가시화 연구)

  • Kim, Bo-Ra-Mi;Choi, Chea-Hong;Choi, Seong-Man
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2010.11a
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    • pp.153-159
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    • 2010
  • In order to see the flame behavior in the annular reverse gas turbine combustor, sector combustion test was performed. Ignition test by using torch ignition system was carried out at the various combustor inlet velocity and air fuel ratio. Also, flame blow out limit was measured by changing fuel flow rate with constant air mass flow rate. In the test results, stable ignition is possible at air excess ratio of 6 and this limit is gradually increased with combustor inlet velocity. The minimum blow out limit is about 4 at 40 m/s of combustor inlet velocity. This blow out limit is also increased up to about 10 with increasing combustor inlet velocity. Test result shows that lean blow out limits are increased with air velocity. The highest blow out limit was found at the combustor inlet velocity of 65m/s.

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Combustion Characteristics Study using Hyper-mixer in Low-enthalpy Supersonic Flow (하이퍼 혼합기를 사용한 저엔탈피 초음속 유동장 내연소 특성 연구)

  • Kim, Chae-Hyoung;Jeung, In-Seuck
    • Journal of the Korean Society of Propulsion Engineers
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    • v.17 no.6
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    • pp.75-80
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    • 2013
  • In this study, a forced ignition method with a plasma jet torch is studied in Mach 2 laboratory scaled wind-tunnel. The hyper-mixer is used as a mixer. For two normal injection cases, the one is collided against a wedge plate of the hyper-mixer and the other is directly injected into the cold main flow. For the first case, the hyper-mixer disperses the injected fuel, leading to the mixing enhancement. Furthermore, the fuel-air mixture is provided into the plasma hot gas, which enhances the combustion performance. However, the direct injection into the main flow method spends amount of fuel without ignition in the cold supersonic flow. In the end, for the forced combustion, it is important to supply the fuel-air mixture into the heat source.

A Study on Combustion Characteristic Methane Fuel according to Torch Volume Variation in a Constant Volume Combustion Chamber (정적연소기에서 토치의 체적 변화에 따른 메탄의 연소특성 파악)

  • Kwon, Soon-Tae;Park, Chan-Jun;Ohm, In-Young
    • Journal of the Korean Society of Visualization
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    • v.9 no.1
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    • pp.42-48
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    • 2011
  • Six different size of torch-ignition device were applied in a constant volume combustion chamber for evaluating the effects of torch-ignition on combustion. The torch-ignition device was designed for six different volumes and same orifice size. The combustion pressures were measured to calculate the mass burn fraction and combustion enhancement rate. In addition, the flame propagations were visualized by shadowgraph method for the qualitative comparison. The result showed that the combustion pressure and mass burn fraction were increased when using the torch ignition device. And the combustion duration were decreased. The combustion enhancement rates of torch-ignition cases were improved in comparison with conventional spark ignition. Finally, the visualization results showed that the torch-ignition induced faster burn than conventional spark ignition due to the earlier transition to turbulent flame and larger flame surface, during the initial stage. Finally, the initial flame propagation was affected by torch-ignition volume.