• Title/Summary/Keyword: 추력실

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An Experimental study for the heat flux in liquid rocket thrust chamber (액체로켓 추력실에서 발생하는 Heat Flux에 관한 실험적 연구)

  • An, Won Geun;Park, Hui Ho;Hwang, Su Gwon;Kim, Yu
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.31 no.3
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    • pp.65-71
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    • 2003
  • In this research, we make the thin wall chamber to the measurement of heat flux of using a Kerosene/LOx liquid rocket engine's thrust chamber. The wall thickness is one millimeter. We measured outside wall temperature of thrust chamber by nine thermocouple. We suppose the system to the one-dimension unsteady state, and so the heat flux and heat transfer coefficient of thurst chamber are calculated using one-dimensional the transient energy equation by outside wall temperature. In this case, O/F ratio is 2.0, experimental variation is chamber pressure and we got the heat transfer coefficient of the proportion relation of 0.88 times for the chamber pressure.

Test & Evaluation for the Configuration Optimization of Thrust Chamber in 70 N-class N2H4 Thruster (Part I: Pulse-mode Performance According to the Chamber Diameter Variation) (70 N급 하이드라진 추력기의 추력실 최적설계와 시험평가 (Part I: 추력실 직경변화에 따른 펄스모드 성능특성))

  • Kim, Jong Hyun;Jung, Hun;Kim, Jeong Soo
    • Journal of the Korean Society of Propulsion Engineers
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    • v.18 no.1
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    • pp.42-49
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    • 2014
  • Performance evaluation was carried out for the 70 N-class hydrazine thruster whose design performance had been already verified. The pulse-mode firing test was conducted for the development model thrusters with various thrust chamber diameters. Evaluation was made by the performance parameters such as specific impulse, impulse bit, and characteristic velocity, etc: specific impulse and characteristic velocity were deteriorated as the thrust chamber diameter deviates from a standard model. Consequently, it is revealed that the performance characteristics of standard model is most superior among the test models.

Development of Chemical Equilibrium CFD Code for Performance Prediction and Optimum Design of LRE Thrust Chamber (액체로켓 추력실의 성능 예측 및 최적 형상 설계를 위한 해석코드 개발)

  • Kim Seong-Ku;Moon Yoon Wan;Park Tae-Seon
    • Journal of the Korean Society of Propulsion Engineers
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    • v.9 no.1
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    • pp.1-8
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    • 2005
  • An axisymmetric compressible flow solver accounting for chemical equilibrium has been developed as an analysis tool exclusively suitable for performance prediction and optimum contour design of LRE thrust chamber. By virtue of several features focusing on user-friendliness and effectiveness including automatical grid generation and iterative calculations with changes in design parameters prescribed through only one keyword-type input file, a design engineer can evaluate very fast and easily the influences of various design inputs such as geometrical parameters and operating conditions on propulsive performance. Validations have been carried out for various aspects by detailed comparisons with the result of CEA code, experimental data of JPL nozzle, actual data for two historical engines, and ReTF data for KSR-III.

A Correlation between the Pressure Oscillation of Combustion Chamber and Thrust Response in a 70 N-class Hydrazine Thruster (70 N급 하이드라진 추력기의 연소실 압력진동 강도와 추력 응답특성의 상관관계)

  • Jung, Hun;Kim, Jeong Soo
    • Journal of the Korean Society of Propulsion Engineers
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    • v.19 no.3
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    • pp.1-8
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    • 2015
  • A ground hot-firing test(HFT) was accomplished to draw a correlation between the pressure oscillation intensity of combustion chamber and thrust response characteristics in a 70 N-class hydrazine thruster which has been developed recently. Monopropellant grade hydrazine was adopted as a propellant for the HFT, and combustion-chamber characteristic length, propellant injection pressure were applied as test parameters. It was confirmed that the decrease of thrust-chamber diameter and injection pressure augmented the pressure oscillation of stagnation chamber in the test condition specified, and the oscillation hampered the pulse response performance of test models.

Effects of Characteristic Length Variation for Thrust Chamber on the Hot-fire Performance of Hydrazine Thruster (하이드라진 추력기의 추력실 특성길이 변화가 연소성능에 미치는 영향)

  • Kim, Jong Hyun;Jung, Hun;Kim, Jeong Soo
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.42 no.2
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    • pp.144-149
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    • 2014
  • A ground firing test for hot-fire performance evaluation according to the characteristic length($L^*$) variation of thrust chamber was carried out for the hydrazine thruster which may be employed in space launch vehicles. A scrutiny into the performance characteristics of each thruster is made in terms of thrust, specific impulse, response characteristics, and characteristic velocity at steady-state firing mode with propellant inlet pressure of 2.41 MPa (350 psia). Through the test results, it has been verified that performance of characteristic velocity and specific impulse degrades as the characteristic length deviates from that of the standard model. Thus, it is confirmed that the thrust chamber configuration of standard model was suitably designed for the requirement specified.

Development of Numerical Framework for Design and Analysis of Liquid Rocket Thrust Chambers (액체로켓 추력실 설계 및 성능 분석을 위한 통합해석기법 개발)

  • Kim, Seong-Ku;Choi, Hwan-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.11a
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    • pp.34-37
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    • 2009
  • The present study presents a numerical methodology for early conceptual trade-off study between propulsive performance, cooling efficiency, weight and size, in which combustion and cooling precesses in regeneratively cooled rocket thrust chamber are interactively simulated. To address the capabilities and reliability of the design tool, some application results are given involving contour design, performance analysis, and wall cooling prediction as well as a systematic design evaluation.

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Test & Evaluation for the Configuration Optimization of Thrust Chamber in 70 N-class N2H4 Thruster (Part II: Pulse-mode Performance According to the Chamber Length Variation) (70 N급 하이드라진 추력기의 추력실 최적설계와 시험평가 (Part II: 추력실 길이변화에 따른 펄스모드 성능특성))

  • Jung, Hun;Kim, Jong Hyun;Kim, Jeong Soo
    • Journal of the Korean Society of Propulsion Engineers
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    • v.18 no.1
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    • pp.50-57
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    • 2014
  • A ground hot-firing test (HFT) was conducted to take out the optimal design configurations for the thrust chamber of 70 N-class liquid rocket engine under development. Monopropellant grade (purity: ${\geq}98.5%$) hydrazine was adopted as a propellant for the HFT, and three kinds of thrust chambers having characteristic lengths ($L^*$) of 2.79, 2.95, and 3.13 m were selected for their performance evaluation. It is revealed through the test and evaluation that the increase of the $L^*$ leads to a performance degradation in the test condition specified, and pulse response performance of the development model shows superior characteristics to commercialized hydrazine thrusters.

Estimation of Thermodynamic/Transport Properties of Kerosene using a 3-Species Surrogate Mixture (3-화학종 대체 혼합물을 이용한 케로신의 열역학적·전달 상태량 예측)

  • Joh, Miok;Kim, Seong-Ku;Choi, Hwan-Seok
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.41 no.11
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    • pp.874-882
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    • 2013
  • Kerosene(Jet A-1), one of the propellants for each stage's engine of the Korea Space Launch Vehicle-II(KSLV-II), functions as coolant at the same time as it flows inside the cooling jacket of the combustion chambers and is injected through the film cooling holes. A physical surrogate mixture model to reproduce the thermophysical characteristics of Jet A-1 has been selected and the thermodynamic/transport properties of the model fuel under high pressure including supercritical conditions have been estimated using SUPERTRAPP(NIST SRD4). Comparisons with the measured properties suggest that proposed database can be used to extract properties of Jet A-1 for conjugate heat transfer analysis of liquid propellant rocket engine thrust chambers. Predicted combustion/cooling performance of regeneratively cooled thrust chambers shall be validated through comparisons with upcoming firing test results.

Experimental Study of Film Cooling in Liquid Rocket Engine(III) (액체로켓엔진의 막냉각에 관한 실험적 연구(III))

  • Yu Jin;Choi Younghwan;Park Heeho;Ko Youngsung;Kim Yoo
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • v.y2005m4
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    • pp.203-207
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    • 2005
  • An experimental study was carried out to investigate the effect of film cooling in the thrust chamber of liquid rocket using LOx and Kerosene as propellant. The heat fluxes were obtained from the measured wall temperature to the axial direction of thrust chamber for different type of coolant, the various O/F ratio, mass flow rate and the location of the film cooling injector. A thin wall combustion chamber and nozzle were used to obtain the heat flux.

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Numerical Study of the effect of pintle shape on the thrust level (핀틀 형상이 추력 크기에 미치는 영향에 대한 수치해석적 연구)

  • Kim, Joung-Keun;Park, Jong-Ho
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.37 no.5
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    • pp.476-482
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    • 2009
  • The effect of pintle shape on the thrust level of pintle-nozzle Solid Rocket Motor(PNSRM) was studied numerically using the Spalart-Allmaras turbulent model of Fluent. Mass flow rate of PNSRM was always less than theoretical value and the extent of decrease in mass flow rate grew in the large pintle because of increase in the relative boundary layer thickness between pintle body and nozzle wall. The bigger pintle size was, the more thrust of pintle tip pressure was obtained. Meanwhile the more thrust of nozzle and chamber pressure decreased. Hence, total thrust of big pintle was less than a small pintle under same throat area condition. Specific impulse was relatively flat for all pintle shape.