• Title/Summary/Keyword: 기체-기체 인젝터

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Design and Spray Characteristics of Coaxial injector using GCH4/LOx (가스메탄/액체산소를 추진제로 이용한 동축인젝터 설계 및 분무 특성)

  • Kim, Bo-Yeon;Lee, Yank-Suk;Park, Jin-Ho;Ko, Young-Sung;Kim, Sun-Jin;Kim, Yoo
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2010.11a
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    • pp.577-580
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    • 2010
  • Coaxial injectors using GCH4/LOx as propellants was designed with shear(gas)/shear(liquid) type and shear(gas)/swirl(liquid) type. Spray characteristics were investigated by cold flow test. Spray patterns of the shear/shear and the shear/swirl type injectors were like a spout of water and hollow cone, respectively. Atomization efficiency of the shear/swirl type injector was better than atomization efficiency of the shear/shear type injector.

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Visualizations of Gas-centered Swirl Sprays in Sub to Super Critical Conditions (임계조건에 따른 기체중심 스월 분무의 가시화 시험)

  • Kim, Dohun;Lee, Keonwoong;Son, Min;Koo, Jaye
    • Journal of the Korean Society of Propulsion Engineers
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    • v.18 no.3
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    • pp.26-33
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    • 2014
  • The gas-centerd swirl injectors are widely used on the main combustor of large liquid propellant rocket engines. Since the gas-liquid propellants, such as kerosene and oxygen-rich gas combination, are mixed and burned in the high pressure condition over the critical pressure point, the cold-flow spray test in the atmospheric condition can not represent the actual spray pattern. To observe the near actual spray patterns of gas-centered swirl injector, the high pressure spray chamber and the control system were constructed. The operating sequence was controlled precisely to obtain clear visualization images.

Effects of Swirl/Shear-coaxial Injector on the Dynamic Behavior of Gaseous Methane-Gaseous Oxygen Diffusion Flame (스월/전단 동축형 인젝터가 기체메탄-기체산소 확산화염의 동역학적 거동에 미치는 영향)

  • Hong, Joon Yeol;Bae, Dae Seok;Kim, Jeong Soo
    • Journal of the Korean Society of Propulsion Engineers
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    • v.23 no.1
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    • pp.1-8
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    • 2019
  • To analyze the dynamic behavior and the structure of the gaseous methane-gaseous oxygen diffusion flame formed by a swirl/shear-coaxial injector, combustion experiments were carried out under different propellant injection conditions. As a result, the OH radical emission intensity of the diffusion flame visualized through chemiluminescence was observed to increase as the propellant mass flow and the momentum flux ratio increased. And flames with swirl showed a more high radical emission intensity than those without swirl.

Spray Characteristics According to the Variation of Design Parameters and Gas-liquid Momentum-flux Ratio in a Swirl-coaxial Injector Applied to Small Rocket Engine (소형로켓엔진에 적용된 스월 동축형 인젝터의 형상변수와 기체-액체 운동량 플럭스 비에 따른 분무특성)

  • Hyun Jong Ahn;Yun Hyeong Kang;Jeong Soo Kim
    • Journal of the Korean Society of Propulsion Engineers
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    • v.27 no.1
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    • pp.27-36
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    • 2023
  • To understand the atomization performance in gas-liquid swirl-coaxial injector applied to a small rocket engine, a cold-flow test was performed by varying the design parameters and supply condition of propellants. As the swirl-chamber diameter and the angle of the convergent section, which are design parameters of injector increased, the spray performance of the injector improved by increasing the swirl strength. In addition, as the gas-liquid momentum-flux ratio increased, the gas flow separated some of the droplets from the liquid film, and a gas-droplet mixture core was formed in the center of the spray sheet.

Dynamic Characteristics of Coaxial Swirl-Jet Injector with Acoustic Excitation (동축형 스월-제트 인젝터의 음향가진에 따른 동특성)

  • Bae, Jinhyun;Kim, Taesung;Jeong, Seokgyu;Jeong, Chanyeong;Choi, Jeong Yeol;Yoon, Youngbin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.691-698
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    • 2017
  • In this study, the injector transfer function (ITF) of a gas-gas coaxial jet-swirl injector is measured by applying excitation to jet or swirl flow using a loudspeaker. As a result of measuring the ITF according to the variation of feed system length, the ITF peak occurs at the resonance frequency of the space where the perturbed flow passes. When applying the excitation to the jet flow, as the jet flow increases up to 56 slpm, the magnitude of ITF decreases, and ITF increases thereafter. Therefore the larger the velocity difference between the jet and the swirl flow, the larger the ITF. In the case of the swirl excitation, the ITF decreases as the jet flow increases because of the decrease of the energy with respect to the constant flow at the downstream. This difference is caused by the location of the hot wire anemometer on the downstream of the injector center axis.

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Spray Breakup Characteristics of a Swirl Injector in High Pressure Environments (고압환경에서 스월 인젝터의 분무 및 분열특성)

  • 김동준;윤영빈;임지혁;길태옥;한풍규
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.34 no.7
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    • pp.97-104
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    • 2006
  • The spray and breakup characteristics of swirling liquid sheet were investigated by measuring the spray angle and breakup length as the axial Weber number Wel was increased up to 1554 and the ambient gas pressure up to 4.0MPa. As Wel and ambient gas density increased, the disturbances on the annular liquid sheet surface were amplified by the increase of the aerodynamic forces, and thus the liquid sheet disintegrated near from the injector exit. The measured spray angles according to the ambient gas density were different before and after the sheet breaks. Before the liquid sheet breaks, the spray angle was almost constant, but once the liquid sheet started to breakup, the spray angle decreased. And the breakup length decreased because of the increase of the aerodynamic force as the ambient gas density and Wel increased. Lastly, the measured breakup length according to the ambient gas density and Wel was compared with the result by the linear instability theory. We found that the corrected linear instability theory considering the attenuation of sheet thickness agrees well with our experimental results.

Flow Characteristics of Cryogenic Oxidizer in Liquid Propellant Rocket Engine (액체로켓 엔진에서의 극저온 산화제의 유동 특성)

  • 조남경;정용갑;문일윤;한영민;이수용;정상권
    • Journal of the Korean Society of Propulsion Engineers
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    • v.6 no.4
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    • pp.15-23
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    • 2002
  • In most cryogenic liquid rocket engines, liquid oxygen manifold and injector are not thermally insulated from room temperature environment fur reducing system complexity and the weight. This feature of cryogenic liquid rocket engine results in the situation that cryogenic liquid oxygen flow is easy to be vaporized especially in the vicinity of the manifold and the injector wall. The research in this paper is focused on two-phase flow phenomena of liquid oxygen in rocket engine. Vapor fraction was estimated by comparing the measured two-phase flow pressure drop in engine manifold and the injector with ideal single phase pressure drop. Heat flux into cryogenic flow is estimated by measuring the wall temperature on the engine manifold to examine boiling characteristics. Suitable correlations for cryogenic two-phase flow were also reviewed to see their applicability. In addition, the effect of vapor generation in liquid rocket engine manifold and injector on engine performance and stability was considered.

Experimental Study on Self-Pulsation Characteristics of Swirl Coaxial Injector with Various Infection Conditions (스월 동축형 인젝터의 분사조건에 따른 Self-Pulsation의 특성 연구)

  • Im Ji-Hyuk;Kim Dongjun;Yoon Youngbin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • v.y2005m4
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    • pp.322-326
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    • 2005
  • The spray and acoustic characteristics of a swirl coaxial injector are studied experimentally. The spray and acoustic characteristics of a swirl coaxial injector are investigated according to the injection conditions, such as the pressure drop of the liquid and gas phase, and injector geometries, such as recess length and gap size between the inner and outer injector.

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Design and Verification of a Injector using Gas Methane and LOx as Propellants (가스메탄/액체산소를 추진제로 하는 인젝터 설계 및 설계 검증)

  • Jang, Jee-Hun;Min, Ji-Hong;Lee, Yang-Suk;Ko, Young-Sung;Kim, Sun-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.877-880
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    • 2011
  • A coaxial swirl/shear injector using GCH4/LOx as propellants was degisned and manufactured. Flow analysis by Fluent was performed to decide the number of orifice and the rear shapes of inlet orifice etc. Flow rate of the injector was measured according to differential pressure and uniformity of injector's spray pattern was confirmed by a patternator. The results showed that the difference of flow rate was around 10% and the spray angle of oxidizer was $66^{\circ}$.

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Design and Verification of a Injector using Gas Methane and LOx as Propellants (가스메탄/액체산소를 추진제로 하는 인젝터 설계 및 설계 검증)

  • Jang, Jee-Hun;Min, Ji-Hong;Lee, Yang-Suk;Ko, Young-Sung;Kim, Sun-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.658-661
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    • 2011
  • A coaxial swirl/shear injector using GCH4/LOx as propellants was degisned and manufactured. Flow analysis by Fluent was performed to decide the number of orifice and the rear shapes of inlet orifice etc. Flow rate of the injector was measured according to differential pressure and uniformity of injector's spray pattern was confirmed by a patternator. The results showed that the difference of flow rate was around 10% and the spray angle of oxidizer was $66^{\circ}$.

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