• Title/Summary/Keyword: 액체 N2O

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A Study on Optimization of Alumina and Catalysts Coating on Tube Reactor for Endothermic Reaction of n-Dodecane Under Supercritical Conditions (고온, 고압 조건에서 n-dodecane 액체연료의 흡열분해를 위한 관벽 내 알루미나 및 촉매 코팅 최적화 연구)

  • Kim, Sung Su;Lee, Sang Moon;Lee, Ye Hwan;Lee, Dong Yoon;Gwak, Ji-Yeong
    • Journal of the Korean Society of Propulsion Engineers
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    • v.25 no.3
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    • pp.56-61
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    • 2021
  • In this study, Al2O3 and H-ZSM-5 were coated on the inner wall of the stainless steel tube for the stable use of liquid hydrocarbon fuel and an endothermic catalyst used as coolant for hypersonic flying vehicles. Coke production is inevitable by the endothermic decomposition reaction of the liquid hydrocarbon fuel, and Fe, Ni metals induce the production of the filamentous coke by using a stainless steel tube reactor as a cooling channel. By coating the stainless steel with H-ZSM-5, Fe and Ni metals are prevented from being directly exposed to the liquid hydrocarbon fuel, and the formation of the filamentous coke is inhibited. In addition, Al2O3 is coated between the stainless steel and H-ZSM-5 to enhance adhesion bond strength.

The Hybrid Rocket Internal Ballistics with Two-phase Fluid Modeling for Self-pressurizing $N_2O$ I (자발가압 성질을 가진 아산화질소의 2상유체 모델링을 통한 하이브리드 로켓 내탄도 해석 I)

  • Lee, Jung-Pyo;Rhee, Sun-Jae;Woo, Kyoung-Jin;Oh, Ji-Sung;Jung, Sik-Hang;Moon, Hee-Jang;Sung, Hong-Gye;Kim, Jin-Kon
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.45-49
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    • 2011
  • The blow-down oxidizer feed system with self-pressurizing $N_2O$ has more advantages than the regulated system. However, it is difficult to predict the exhaust flow rate because there exist two phases in the $N_2O$ tank - liquid phase and gas phase, and the properties of $N_2O$ in storage tank are varied continuously during blow-down. In this paper, a method that can analyse simply the blow-down oxidizer feed system is studied. The properties of saturated $N_2O$ are found from the NIST data base, and mass flow through the orifice is modeled as NHNE. Cold flow test with hybrid rocket combustor is performed for the comparison where the results should found from the good agreement.

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A Study of Combustion Test Facility for LRE Using Hydrogen peroxide and Kerosene as Propellant (과산화수소/케로신 액체로켓엔진의 연소시험 설비 개발에 관한 연구)

  • Choi, Yu-Ri;Jeon, Jun-Su;Kim, Young-Mun;Ko, Young-Sung;Kim, Yoo;Kim, Sun-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.05a
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    • pp.29-32
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    • 2009
  • This study is for development combustion test facility of liquid rocket engine system using hydrogen peroxide/kerosene as propellent. For this new facility, we construct thrust measure system, propellent supply system, control and data acquisition system. To perform 200N liquid rocket engine combustion test, operation scenario and sequence were designed. Result of combustion test propellents were supplied to engine stably and confirm of development combustion test facility very well.

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Comparison between GOx/Kerosene and GN2O/Ethanol Reactive Spray in a Subscale Liquid Rocket Engine (축소형 액체로켓엔진에서 기체산소/케로신 및 기체아산화질소/에탄올 연소 분무의 비교)

  • Choi, Songyi;Shin, Bongchul;Lee, Keonwoong;Kim, Dohun;Koo, Jaye;Park, Dong-Kun
    • Journal of the Korean Society of Propulsion Engineers
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    • v.19 no.4
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    • pp.61-68
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    • 2015
  • Reactive sprays of two propellant combinations(GOx/kerosene and $GN_2O$/ethanol) were observed and compared with each other as a basic research of visualizing supercritical combustion. A shadowgraph imaging method was used to visualize the reactive sprays, and shadowgraph images were converted to density gradient magnitude images to analyse the structure of reactive sprays. The gas-liquid interface of GOx/kerosene spray showed rougher boundary and steeper density gradient near the injector face than the $N_2O$/ethanol at similar combustion chamber pressure. Spray core length was calculated from averaged density gradient magnitude images and it was revealed that spray core length of GOx/kerosene was shorter than that of $GN_2O$/ethanol, although momentum flux ratio of GOx/kerosene propellant combination was lower.

저주파 및 고주파 구동 대기압 플라즈마 젯의 특성 비교

  • Gwon, Yang-Won;Baek, Eun-Jeong;Eom, In-Seop;Jo, Hye-Min;Kim, Seon-Ja;Jeong, Tae-Hun
    • Proceedings of the Korean Vacuum Society Conference
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    • 2016.02a
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    • pp.194.2-194.2
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    • 2016
  • 저주파 (수십 kHz)와 고주파 (13.56 MHz)로 구동되는 대기압 플라즈마 젯을 발생시키고, 인가전압 (혹은 인가전력)과 기체 유량에 따른 대기압 플라즈마의 특성을 비교하였다. 고주파에서 발생된 플라즈마는 저주파의 경우보다 안정적이었으며, 인가전압 (혹은 인가전력)이 증가함에 따라 플라즈마 기체온도는 상승하였고, 고주파 젯의 기체온도는 저주파 젯 보다 높았으나 330 K이하인 것을 확인하였다. Optical Emission Spectroscopy (OES)를 이용하여 저주파와 고주파의 광 방출 특성을 측정하였다. 저주파에서는 $N_2{^+}$ (391.4 nm)의 intensity 증가가 두드러지게 나타났지만 고주파 젯에서는 $N_2$, $N_2{^+}$의 intensity는 감소하였으며, OH, NO, $H_{\alpha}$, O와 같은 활성 산소 종 (Reactive Oxygen Species)이 저주파 젯 보다 높게 측정되었다. Boltzmann plot method를 이용한 분석을 통해 저주파와 고주파 영역에서의 플라즈마 전자 여기 온도를 측정하였다. 또한 자외선 흡수분광법을 이용하여 플라즈마-액체 계면에서의 OH이 입자밀도를 측정하여 OES방법으로 측정한 OH 밀도와 비교하였다. 그리고 화학적 측정법 (terephtalic acid solution)을 이용하여 액체 내의 OH의 농도를 측정하였다.

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Emulsion Liquid Membrane Transport of Heavy Metal Sons by Macrocyclic Carriers (거대고리 운반체에 의한 중금속이온의 에멀죤 액체막 수송)

  • 정오진
    • Journal of Environmental Science International
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    • v.4 no.2
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    • pp.223-232
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    • 1995
  • New two macrocyclic compounds using as carriers of liquid emulsion menbrame, have been synthesized. These reuslts provide evidance for the usefulness of the theory in designing the systems. The efficiency of selective transport for heavy metal ions have been discussed from the membrane systems that make use of $SCN^-$,<>,$I^-$,CN- and $Cl^-$ ion as co-anions in source phase and make use of $S_2O_3^{2-}$ and $P_2O_7^{4-}$ ion as receiving phase, respectively. The transport rate of M(II) was highest when a maximum amount of the M(II) in the source phase was present as$Cd(SCN)_2$$(P[SCN^-]= 0.40M)$, $Hg(SCN)_2([SCN^-]=0.40M)$ and Pd(CN)$([CN^-]= 0.40M)$. The Cd(II) and Pb(II) over each competitive cations were well transprted with 0.3M-S2032- and 0.3M-P2O74-, respectively in the receiving phase. Results of this study indicate that two criteria must be met in order to have effective macrocycle-mediated transport in these emulsion system. First one must effective extraction of the $M^{n+}$ into the toluene systems. The effectiveness of this extraction is the greatest if locK for $M^{n+}$macrocycle interaction is large and if the macrocycle is very insoluble in the aqueous phase. Second, the ratio of the locK values (or Mn+-receiving phase ($S_2O_3^{2-}$- or $P_2O_7^{4-}$) to $M^{n+}$-macrocycle (($L_1$이나 $L_2$) interaction must be large enough to ensure quantitative stripping of Mn+(($Cd^{2+}$,$Pb^{2+}$)at the toluene receiving Phase interface. $L_1$(3.5-benzo-10,13,18,21-tetraoxa-1,7,diazabicyclo(8,5,5) eicosan) forms a stable ($Cd^{2+}$ and >,$Pb^{2+}$ complexes and $L_1$ is very insoluble in water and its $Cd^{2+}$ and >,$Pb^{2+}$ complex is considerably less stable than $Cd^{2+}$-(S2O3)22- and $Pd^{2+}-P_2O_7^{4-}$ complexes. On the other hand, the stability of the $Hg^{2+}$)+-$L_1$( complex exceed that of the $Hg^{2+}$- (S2O3)22- and Hg2+-P2O74-, and the distribution coefficient of $L_2$(5,8,15,18,23,26-hexaoxa-1,12- diazabicyclo-(10,8,8) octacosane) is much smaller than that of $L_1$. Therefore, the partitioning of Lr is favored by the aqueous receiving Phase, and little heavy metal ions transport is seen despite the large logK for $Hg^{2+}$+-$L_1$ and $Mn^+$($Cd^{2+}$+, $Pb^{2+}$+ and $Hg^{2+}$)-$L_2$ interactions. Key Words : macrocycles, transport, heavy metal, co-anion, source phase, receiveing, complex separation, interaction, destribution coefficient.

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Electronic Effects of the Iron Porphyrin on $O_2/N_2$ Selectivity (Iron(II) Porphyrin 화합물을 이용한 산소 촉진 수송)

  • 임성욱;홍석인;유병수
    • Proceedings of the Membrane Society of Korea Conference
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    • 1992.10a
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    • pp.39-40
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    • 1992
  • 분리막법이 기체 분리에 응용된후 에너지 소비의 절감, 열안전성 등과 같은 장점들로 인해 수소회수 및 $H_2/CO_2$의 비율조정, $CH_4/CO_2$ 분리, $O_2/N_2$의 분리 등에 이용되고 있다. 이러한 분리막의 특성은 투과도와 선택투과도에 의해 결정되어지는데, 이들은 서로 상반된 경향을 나타낸다. 즉 투과도가 높으면 선택투과도는 낮아지고, 선택투과도가 높으면 투과도는 감소하게 된다. 그러나 이러한 두가지 특성 모두를 높이기 위한 연구가 활발히 진행되고 있는데, 그 연구방향은 새로운 고분자의 합성 및 고분자의 개질, 복합재료의 개발, 액정, 촉진수송법 등으로 나눠질 수 있다. 이중 촉진수송이란 특정한 기체와 가역적 친화력 또는 흡착력을 갖는 운반체를 액체나 고체막에 분산시켜 원하는 특정 기체만을 선택택으로 수송하는 것을 말한다.

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Vaporization Characteristics of Liquid Oxygen at High-Pressure Environment (고압 상태에서의 액체 산소의 증발 특성 해석)

  • 유용욱;김용모;손정락
    • Journal of the Korean Society of Propulsion Engineers
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    • v.2 no.3
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    • pp.90-98
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    • 1998
  • The vaporization process of liquid oxygen(LOX) at high pressure environment is numerically investigated. The present vaporization model can account for the high-pressure effects such as ambient gas solubility, real gas behavior and variable properties. The predicted phase-equilibrium compositions for $N_2$/$H_2$ and $O_2$/He system are well agreed with experimental data. The LOX vaporization characteristics is parametrically studied for wide range of the operating conditions encountered in the high-pressure combustion process of liquid rocket engine.

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Requirement Analysis of Propulsion System for Active Anti-Ship Missile Decoy (능동형 대함 유도탄 기만기의 추진 시스템 요구 조건 분석)

  • Moon, Yongjun;Kwon, Sejin
    • Journal of the Korean Society of Propulsion Engineers
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    • v.17 no.4
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    • pp.1-9
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    • 2013
  • An active anti-ship missile decoy system was designed conceptually to analyze propulsion system requirements and feasibility to use a liquid bi-propellant rocket engine. Overall mass, size, and shape were assumed referring to specifications of Nulka which was developed by US and Australia in 1990s. The propulsion system was assumed to be a 1,000 N-class $H_2O_2$/kerosene rocket engine with a pressurized feed system. A three-degree-of-freedom optimal trajectory was calculated based on the assumptions, and mass budget was designed from the calculation results. It was found that the requirements for the propulsion system is that it shall be operated more than 100 sec; it shall be re-ignitable; it shall have a throttle capability of a range from 35% to 100% when the maximum thrust at sea level is 1,000 N.

Development of 1-N class Thruster System based on ADN Monopropellant (ADN 단일 추진제 기반 1N 급 추력기 시스템 개발)

  • Kim, Jincheol;Choi, Woojoo;Jo, Yeongmin;Jeon, Jonggi;Kim, Taegyu
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.406-408
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    • 2017
  • Ammonium dinitramide (ADN) Low toxicity monopropellant based 1N class thruster and test equipment were developed. Compared with the hydrazine which used in existing satellite thruster, ADN is easy to handle and has excellent physical characteristics such as density and specific impulse. Due to these characteristics, ADN is attracting attention as an eco-friendly propellant. In this paper, 1N class thruster and thrust measurement system was designed for performance testing of ADN monopropellant. The composition of the propellant for the design and experiment was set at 11.2: 25.4: 63.4 for each of Methanol: $H_2O$: ADN.

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