• Title/Summary/Keyword: Rocket engine

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Improvement of the Startup Transient Analysis on the Liquid Rocket Engine Using the TP+GG Coupled Test Result (터보펌프+가스발생기 연계시험 결과를 이용한 액체로켓엔진 시동 과정에 대한 해석 방법의 개선)

  • Park, Soon-Young;Cho, Won-Kook;Moon, Yoon-Wan
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.821-826
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    • 2011
  • The turbopump+gas generator (TP+GG) coupled test for the liquid rocket engine development was performed. By comparing the results of a engine startup transient analysis with this test results, the verification of the analysis model was performed. From this, as to the analysis of the engine startup, the method calculating the pressure ratio of the turbine during the initial stage of startup was improved. And a fact that the transient heat transfer phenomenon between the working fluid and the solid parts of turbine effects to the calculation of turbine pressure ratio and consequentially to the startup analysis was revealed.

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Modeling of Liquid Rocket Engine Components Dynamics at Transient Operation (액체로켓엔진 천이작동 예측을 위한 구성품 동특성 모델링)

  • Kim, Hyung-Min;Lee, Kuk-Jin;Yoon, Woong-Sup
    • Journal of the Korean Society of Propulsion Engineers
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    • v.15 no.1
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    • pp.35-44
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    • 2011
  • Mathematical modelling for liquid rocket engine(LRE) main components were conducted to predict the dynamic characteristics when the LRE operates at the transient condition, which include engine start up, shut down, or thrust control. Propellant feeding system is composed of fuel and oxidizer feeding components except for regenerative cooling channel for the fuel circuit. Components modeling of pump, pipe, orifice, control valve, regenerative cooling channel and injector was serially made. Hydraulic tests of scale down component were made in order to validate modelling components. The mathematical models of engine components were integrated into LRE transient simulation program in concomitant with experimental validation.

Specific Impulse Variation of a Liquid Rocket Engine by Film Cooling (막냉각에 의한 액체로켓엔진의 비추력 변화)

  • Cho, Won-Kook;Park, Soon-Young;Seol, Woo-Seok
    • Aerospace Engineering and Technology
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    • v.8 no.2
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    • pp.133-139
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    • 2009
  • An analysis has been performed on the specific impulse for a liquid rocket engine of gas generator cycle. The present analysis method has been validated through the comparison of the optimal specific impulse for the 300t thrust conceptual engine against the published data. The engine specific impulse can be increased by applying film coolant decreasing the fuel pump head for regenerative cooling despite the decrease of specific impulse of the combustion chamber when the film coolant participates combustion more than the critical amount. The improved condition shows that higher combustion chamber pressure is achieved with less fuel pump head rise by additional film cooling.

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Optimal Condition of Specific Impulse for a Liquid Rocket Engine with Film Cooling (막냉각이 적용된 액체로켓엔진의 비추력 최적조건)

  • Cho, Won-Kook;Park, Soon-Young;Seol, Woo-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2007.04a
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    • pp.135-140
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    • 2007
  • An analysis has been conducted of the optimal condition to maximize the specific impulse for a liquid rocket engine with film cooling. The present engine performance has been compared with the published conceptual design to be verified satisfactorily accurate. The optimal combination of film coolant flow rate and the regenerative cooling capacity has been found for maximum specific impulse. The optimal fuel pump pressure increases and the optimal film coolant flow decreases for a larger thrust engine. Higher turbine inlet temperature increases both the fuel pump pressure and the film coolant flow rate as the optimal condition. The coking temperature has the same qualitative effect as the turbine inlet temperature.

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Evaluation of Specific Impulse for Liquid Rocket Engine Adopting Gas Generator Cycle (가스발생기 사이클 액체로켓엔진의 비추력 평가)

  • Cho, Won-Kook;Seol, Woo-Seok
    • Aerospace Engineering and Technology
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    • v.9 no.1
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    • pp.93-97
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    • 2010
  • The analysis of specific impulse of the liquid rocket engine employing gas generator cycle with LOx/kerosene as propellant has been performed. The relative error of performance of 300 ton level engine is 0.1%s for specific impulse and 12% for optimal combustion pressure comparing with the published data. The difference of the performance model and the material property models of gas generator product gas are the presumed major reason of discrepancy. The optimal condition of 30 ton level engine is combustion pressure of 68 bar and mixture ratio of 2.2 for maximum specific impulse. This optimal condition can be changed by performance models.

An Analysis on Plume Behaviour of Rocket Engine with Ground Condition at High Altitude Engine Test Facility (고공시험설비에서 로켓엔진의 지상시험 플룸 거동 해석)

  • Kim, Seong-Lyong;Lee, SeungJae;Han, YoungMin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.112-115
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    • 2017
  • We analyzed the rocket engine flow to check whether the possibility of the ground test and the equipment safety problems in the high altitude engine test facility. The test condition is that the vacuum chamber is open and the coolant water is injected into the supersonic diffuser. The analysis uses two-dimensional axisymmetry with a mixture of plume, air, and cooling water. As a result, the ground test was possible up to the cooling water flow rate of 200 kg/sec. However, due to the back flow of the initial plume, the vacuum chamber is exposed to high temperature, and at the same time, the inside of the vacuum chamber is contaminated due to the reverse flow of the cooling water. Therefore, sufficient insulation measures and work for pollution avoidance should be preceded.

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Ground Firing Test of a 75 Ton Class Engine System for KSLV II and its Structural Vibration Responses (75톤급 액체로켓엔진 지상연소시험 및 진동응답 분석)

  • Kim, Jin-Hyuk;Jeon, Seong Min;Park, Jongyoun;Yoo, Jaehan;Jeong, Eunhwan
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.928-929
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    • 2017
  • A 75 ton class liquid rocket engine has been developed for KSLV II. Ground firing tests of the rocket engine were conducted to characterize and quantify its structural vibration under combustion testing environments. In this study, evaluation of dynamic response characteristics of the engine system was presented to verify its structural integrity and structural design during ground firing tests.

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Numerical Study and Firing Test of a Liquid Rocket Engine Head with a Coolant Manifold (로켓엔진 헤드용 냉각 매니폴드의 해석 및 시험)

  • Park, Jinsoo;Choi, Jiseon;Yu, Isang;Ko, Youngsung;Kim, Sunjin;Shin, Dongsun
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.1021-1025
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    • 2017
  • Numerical heat/flow analysis was performed on a liquid rocket engine head with the cooling water manifold to ensure the durability of a ground test facility for heat exchanger. Through these studies, the shapes of the injector and the flow path were determined and applied to the head of the engine under development. Firing tests were conducted to verify the designed coolant manifold and no thermal damage was found on the engine-head-face. Comparing the combustion test results with the numerical analysis, the outlet temperature of coolant showed a difference of about $15^{\circ}C$. This trend is reasonable considering existence of LOX manifold, thermal barrier coating, and the actual location of flame.

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Numerical Analyses of Performance and Combustion in KSR-III Liquid Propellant Rocket Engine with Combustion Stabilization Device (연소 안정성 기구를 장착한 KSR-III 액체로켓 엔진의 성능 및 연소 해석)

  • Moon, Yoon-Wan
    • 한국연소학회:학술대회논문집
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    • 2003.05a
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    • pp.41-50
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    • 2003
  • Numerical analysis was carried out to investigate performance and combustion characteristics of KSR-III liquid rocket engine with several types of baffle. To evaluate the change of performance and combustion characteristics with several types of baffle, the first numerical calculations were performed about baffle tab, radial blade baffle, and hub-and-spoke baffle. Then radial blade and hub-and-spoke baffle were determined to design two types of the KSR-III engine with baffles. Also to investigate the effect of injector arrangements and baffle positions, two types of radial blade baffle were calculated then numerical calculations were carried out with changing axial length of radial blade I, II and hub-and-spoke baffle. While axial length of baffle effected to performance very small, injector arrangement effected to performance largely through calculations of radial blade I, II. From the viewpoint of combustion instability, hub-and-spoke baffle controlled combustion instability effectively and there was the performance of hub-and-spoke baffle between radial blade I and II.

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Thermal Analysis of Exhaust Diffuser Cooling Channels for High Altitude Test of Rocket Engine (로켓엔진 고공환경 모사용 디퓨져의 냉각 채널 열 해석)

  • Cho, Kie-Joo;Kim, Yong-Wook;Kan, Sun-Il;Oh, Seung-Hyub
    • Aerospace Engineering and Technology
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    • v.9 no.2
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    • pp.193-197
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    • 2010
  • Water cooling ducts are installed in the exhaust diffuser for high altitude tests of rocket engine to protect diffuser from high-temperature combustion gas. The mass flow rate and pressure of cooling water is designed to prevent boiling of cooling water in the ducts. Therefore, the estimation of maximum temperature of duct wall is important parameter in design of cooling system, especially pressure of cooling water. The method for predicting maximum temperatures of duct walls with variation of coolant flow rates was derived theoretically.