• Title/Summary/Keyword: engine facility

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Hypersonic Engine Test Facility Operation Test : Ejector System Performance Analysis (고속추진기관 시험설비 시운전 : 이젝터시스템 성능분석)

  • Kang, Sang-Hun;Lee, Yang-Ji;Oh, Joong-Hwan;Yang, Soo-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2010.05a
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    • pp.268-271
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    • 2010
  • Hypersonic engine test facility with ejector system was tested. Ejector system was designed by revised EJSIMP code. The performance of the ejector system was predicted by numerical analysis. As a result, ejector system satisfied the facility design requirement. Based on the pressure level, the facility was successfully started at Mach 3.5 and 20km altitude condition.

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Test Facility Improvement for Hot Firing Test of a 7-tonf Combustor (7톤급 연소기 시험을 위한 시험 설비 변경)

  • Kim, Hyeon-Jun;Lim, Byoung-Jik;Kang, Dong-Hyuk;Jae, Won-Ju;Choi, Hwan-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2012.05a
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    • pp.493-497
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    • 2012
  • The rocket engine test facility(ReTF) was improved for hot firing tests of 7 ton-class liquid rocket engine combustion chamber, which will be used for the third stage of the Korea Space Launch Vehicle II(KSLV-II), considering convenience of operation and maintenance, flexibility and safety. In this paper, main modifications and functions of improved ReTF were described. 초 록

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Preliminary Design of Test Facility for 75-tonf-Class Liquid Rocket Engine Combustor (75톤급 액체로켓엔진 연소기 시험설비 기본설계)

  • Lim, Byoung-Jik;Seo, Seong-Hyeon;Kim, Mun-Ki;Kang, Dong-Hyuk;Han, Yeong-Min;Choi, Hwan-Seok
    • Journal of the Korean Society of Propulsion Engineers
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    • v.14 no.5
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    • pp.84-91
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    • 2010
  • For the successful development of 75-tonf-class liquid rocket engine, a plenty of tests on each engine component have to be performed and this is equally true for a combustor. However the test facility which is in operation at Korea Aerospace Research Institute lacks its capacity to perform fire tests of a 75 tonf class combustor at its nominal thrust. Since the test facility has to be ready prior to the start of development tests, it is very urgent to establish the test facility. The preliminary design of a test facility for a 75 tonf class combustor which was performed according to such a necessity is described in the paper.

Management of Test Facility for Tests of Liquid Rocket Engine on Off-Design Condition (액체로켓엔진 탈설계 조건 시험을 위한 시험설비 운용)

  • Yu, Byungil;Kim, Hongjip;Han, Yeongmin
    • Journal of Aerospace System Engineering
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    • v.14 no.5
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    • pp.91-99
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    • 2020
  • A liquid rocket engine goes through many tests to prove its performance before liftoff. It means the tests for setting ignition and start-up conditions or a test on design condition, which verifies the design performance. However, the development process requires verification of performance under off-design conditions through tests involving different operating conditions, which affects the duration of engine development. The off-design performance test is performed by altering the conditions of the propellant supplied to the engine in conjunction with the engine performance test that varies the opening of the control valves in the engine. This paper is based on the results of the engine tests performed at the KSLV-II engine test facilities in the Naro Space Center and describes the operations of the test facility for off-design condition test that changes the inlet conditions of the turbo-pump due to changes in the pressure and temperature of the propellant supplied to the test engines.

A Study on the Hypersonic Air-breathing Engine Ground Test Facility Composition and Characteristics (극초음속 공기흡입식 추진기관 지상 시험설비의 구성 및 특성에 관한 연구)

  • Lee, Yang-Ji;Kang, Sang-Hun;Yang, Soo-Seok
    • Journal of the Korean Society of Propulsion Engineers
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    • v.19 no.6
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    • pp.81-90
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    • 2015
  • In order to know the characteristics of the hypersonic air-breahting engine, high altitude and Mach number ground test is necessary. Therefore, high pressure and high temperature condition should be simulated to do ground test of the hypersonic air-breathing engine. In this paper, the hypersonic air-breathing engine ground test facility of the Korea Aerospace Research Institute was introduced and the composition and characteristics were described.

Study on Liquid Rocket Engine High Altitude Simulation Test (액체로켓엔진 고공환경 모사시험 연구)

  • Kim, Seung-Han;Moon, Yoon-Wan;Seol, Woo-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2010.11a
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    • pp.733-736
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    • 2010
  • Korea Aerospace Research Institute (KARI) performed the preliminary design of liquid rocket engine high-altitude simulation firing test facility for the development and qualification of LRE for the 2nd stage of KSLV-II. The engine high-altitude simulation firing test facility, which are to be constructed at Goheung Space Center, will provide liquid oxygen and kerosene to enable the high-altitude simulation firing test of 2nd stage engine at ground test facility. The high-altitude environment is obtained using a supersonic diffuser operated by the self-ejecting jet from the liquid rocket engine.

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Combustion Test for a Supersonic Combustor Using a Direct-Connected Facility (직결형 설비를 이용한 초음속 연소기 연소 시험)

  • Yang, Inyoung;Lee, Kyung-Jae;Lee, Yang-Ji;Lee, Sanghoon;Kim, Hyungmo;Park, Poomin
    • Journal of the Korean Society of Propulsion Engineers
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    • v.22 no.3
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    • pp.1-7
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    • 2018
  • A combustion test for a supersonic combustor was conducted using a direct-connected type supersonic combustor test facility. The facility was verified for the capability of simulating required flow conditions. The test condition was maintained at Mach 2.0, $915^{\circ}C$ and 496 kPa for 15 s. Using gaseous hydrogen as the fuel, the combustor model was also tested for its ignition and flame holding capability at the fuel equivalence ratio of 0.12. Combustion efficiency was 71%, and the supersonic flow regime was obtained at this test condition.

A Starting Characteristics Study of the Scramjet Engine Test Facility with a Mach 5.0 Nozzle (마하 5.0 노즐을 장착한 스크램제트 엔진 시험설비의 시동 특성 연구)

  • Lee, Yang-Ji;Yang, In-Young;Yang, Soo-Seok
    • Journal of the Korean Society of Propulsion Engineers
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    • v.17 no.4
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    • pp.63-72
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    • 2013
  • A Mach 5 nozzle and a diffuser of the Scramjet Engine Test Facility (SETF) were made for a hydrocarbon-fueled scramjet engine. SETF, attached with a diffuser guide, started with a model of 60% blockage, though the model engine could not start by over expansion of the facility nozzle. The model was moved into the nozzle to escape the shock generated from the nozzle exit, both SETF and the engine could start. The pitot rake experiments (blockage of 2.3%) were done for measuring the core flow in the test section. From the pitot experiments, the core flow was expanded by an under expansion. It means that the core flow in the test section was related with a model blockage. SETF and the engine with a blockage of 33% work normally. From a series of experiments, SETF started with a normal shock efficiency of 58%, regardless of a blockage ratio.

Concept Design of High Altitude Simulation Test Facility (고공환경모사 시험설비 구축을 위한 개념설계)

  • Kim, Sang-Heon;Kim, Yong-Wook;Lee, Jung-Ho;Yu, Byung-Il;Cho, Sang-Yeon;Oh, Seung-Hyub
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2006.11a
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    • pp.75-81
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    • 2006
  • The propulsion system of KSLV-I second stage is engine with high expansion ratio and its starting altitude is high. To verify the performance of engine before the launch in the ground, high altitude test facility to simulate its operating condition is necessary. This material is about the concept design of high altitude simulation test facility for second stage engine. And it will be the basis for the construction of test facility and the test of engine.

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Operation Techniques of Liquid Rocket Engine Combustor Ground Firing Test Facility (액체로켓엔진 연소기 지상연소시험설비 운영관리 기술)

  • Kang, Dong-Hyuk;Lim, Byoung-Jik;Moon, Il-Yoon;Seo, Seong-Hyeon;Han, Yeoung-Min;Choi, Hwan-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2006.11a
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    • pp.157-162
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    • 2006
  • A Liquid Rocket Engine(LRE) ground firing test facility was built in Korea Aerospace Research Institute(KARI) in 2001 to develop the LRE for the first Korean liquid rocket, KSR-III. Around 170 tests were conducted since its establishment until recently by September 2006, and in the meantime, a considerable improvements were made in the capability. This paper describes the outline, conducted tests and operation techniques which have been accumulated through the operation of KARI LRE ground firing test facility.

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