• Title/Summary/Keyword: Propulsion Test Facility

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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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A Layout Plan of a Pressure-fed Hot-firing Test Facility for the Performance Evaluation of a Combustion Chamber (연소기 성능평가를 위한 가압식 연소시험설비의 배치 계획)

  • Lee, Kwang-Jin;Cho, Nam-Kyung;Han, Young-Min
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2012.05a
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    • pp.465-467
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    • 2012
  • A layout plan of a pressure-fed test facility to carry out hot-firing test of liquid rocket engine combustion chamber and purpose of rooms located in the test building were proposed. The layout plan of suggested infrastructure in this paper was determined depending on the design of a vertical test facility to use the natural lay of the land and simulate the initial position of flight model.

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Operation and Maintenance Techniques for Liquid Rocket Combustor Ground Firing Test Facility (액체로켓 연소기 지상연소시험설비 운영 및 관리 기술)

  • Kang, Dong-Hyuk;Lim, Byoung-Jik;Moon, Il-Yoon;Seo, Seong-Hyeon;Han, Yeoung-Min;Choi, Hwan-Seok
    • Journal of the Korean Society of Propulsion Engineers
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    • v.11 no.3
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    • pp.43-49
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    • 2007
  • A ground firing test facility for Liquid Rocket Engine(LRE) combustor was built in Korea Aerospace Research Institute(KARI) in 2001 to support the development of the first Korean LRE for the KSR-III. About 170 tests were conducted up to date since its establishment and in the meantime a considerable improvements were made in the facility capability. This paper describes the outline, conducted tests and operation techniques which have been acquired through the operation of the test facility.

Introduction to Construction of a Turbopump Real-Propellant Test Facility (터보펌프 실매질 시험설비 구축에 대한 소개)

  • Kim, Jin-Sun;Ko, Young-Sung
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.835-840
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    • 2011
  • The development of a turbopump is fundamental to have an independent LRE(liquid rocket engine) for KSLV-II. Recently, the detail design of a turbopump real-propellant test facility based on liquid oxygen and kerosene has been performed to structure the test facility for the experimental validation of the turbopump. In this paper, the design requirements of the turbopump and the specifications of the test facility was presented and the representative sub-facilities were explained on the basis of the design results. Also, the uncertainty of the sub-facilities which could be appeared during the operation was removed in advance through the simulation method and the experimental verification.

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Sub-System Requirements of a Pressure-fed Hot-firing Test Facility for the Performance Assessment of a LRE Thrust Chamber (액체로켓엔진 연소기의 성능평가를 위한 가압식 연소시험설비의 구성 요구조건)

  • Lee, Kwang-Jin;Lim, Byoung-Jik;Seo, Seong-Hyeon;Han, Yeoung-Min;Choi, Hwan-Seok
    • Journal of the Korean Society of Propulsion Engineers
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    • v.15 no.4
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    • pp.94-102
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    • 2011
  • Sub-system requirements of a pressure-fed hot-firing test facility for performance assessment of a Liquid Rocket Engine(LRE) thrust chamber using Liquid oxygen and kerosene were described. These requirements were based on the experience of construction and operation of the ground hot-firing test facility which was used for the development of the KSR-III and a 30 tonf-class LRE thrust chamber. So it is expected that this paper is used as a basic material and an itemized previous review statement for the design and construction of a large hot-firing test facility.

Sub-System Requirements of a Pressure-fed Hot-firing Test Facility for the Performance Assessment of a LRE Thrust Chamber (액체로켓엔진 연소기의 성능평가를 위한 가압식 연소시험설비의 구성 요구조건)

  • Lee, Kwang-Jin;Lim, Byoung-Jik;Seo, Seong-Hyeon;Han, Yeoung-Min;Choi, Hwan-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2010.11a
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    • pp.63-71
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    • 2010
  • Sub-system requirements of a pressure-fed hot-firing test facility for performance assessment of a Liquid Rocket Engine(LRE) thrust chamber using Liquid oxygen and kerosene were described. These requirements were based on the experience of construction and operation of the ground hot-firing test facility which was used for the development of the KSR-III and a 30 $ton_f$-class LRE thrust chamber. So it is expected that this paper is used as a basic material and an itemized previous review statement for the design and construction of a large hot-firing test facility.

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Design of an Altitude Test Facility for Turbo Shaft Engine

  • Choi, Young-Hwan;Park, Sang-Joon;Lee, Joon-Won;Kim, Chun-Taek;Cha, Bong-Jun;Ahn, Iee-Ki
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.03a
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    • pp.173-181
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    • 2008
  • Gas turbine engine for aircraft are usually operated at the altitude condition which is quite different from the ground condition. In order to measure the precise performance data at the altitude condition, the engine should be tested at the altitude condition by a real flight test or an altitude simulation test with an altitude test facility. In this paper describes the design of altitude test facility for turbo shaft engine. This facility will be located in test cell #2 at the Korea Aerospace Research Institute. Test Cell #2 will be used for altitude testing engines with mass flow rate up to 40kg/s and inlet temperatures in the range from $-65^{\circ}C$ to $200^{\circ}C$. The existing compressor/exhauster station with heater & cooler system will be used to simulate altitude conditions in Test Cell #2.

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Development Test of Alcohol Burner for Turbopump Real-propellant Test Facility (터보펌프 실매질 시험설비를 위한 알코올버너 개발시험)

  • Kim, Jin-Sun;Han, Yeoung-Min;Ko, Youngsung
    • Journal of the Korean Society of Propulsion Engineers
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    • v.18 no.5
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    • pp.79-86
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    • 2014
  • A turbopump real-propellant test facility(TPTF) is to verify the performance of a turbopump unit(TPU) based on liquid oxygen and kerosene. One of the most important sub-facilities is a hot-gas generation system which makes the driving force of the TPU with an alcohol burner. The alcohol burner generates the required flow rates and temperature at the facility using high pressure air and ethanol. In the study, the verification tests of the alcohol burner which was manufactured entirely with domestic technology were performed and fabrication technique and operation skill for the burner could be obtained ahead of the construction of the facility. Two burners will be operated simultaneously for the real-propellant test of 75tf class turbopump and satisfy the power requirement from the turbine of the TPU.

Rocket Engine Test Facility Improvement for Hot Firing Test of 75 ton-f Class Gas Generator and Cold Flow Test (75톤급 가스발생기 연소시험을 위한 시험장 개선 및 수류시험)

  • Kang, Dong-Hyuk;Lim, Byoung-Jik;Ahn, Kyu-Bok;Seo, Seong-Hyeon;Han, Yeoung-Min;Choi, Hwan-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.11a
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    • pp.29-33
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    • 2009
  • On the basis of the development experience of a gas generator for the 30 ton-f thrust liquid rocket engine combustor a Subscale Ground Firing Test Facility was designed and fabricated for a gas generator for the 75 ton-f thrust liquid rocket engine combustor. The Subscale Ground Firing Test Facility developed is going to be used to develop 75 ton-f class gas generator. Acquired data and test technique from this facility will be used to develope the high performance liquid rocket engine combustor and the Ground Firing Test Facility. This report describes the improved Subscale Ground Firing Test Facility for 75 ton-f class gas generator and results of the cold flow test.

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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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