• Title/Summary/Keyword: Engine Test Facility

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Study on Spray Characteristics of Barbotage Injector for Scramjet Engine (스크램제트 엔진용 Barbotage injector의 분무 특성에 관한 연구)

  • Lee, Jinhee;Lee, Sanghoon;Yang, Inyoung;Lee, Kyungjae;Kim, Jaeho;Yang, Sooseok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.236-239
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    • 2017
  • A part of the development of Scramjet Engine, this study was performed about Injectors. Barbotage injectors were used for experiment. To study characteristics of injector spray, water is supplied as a main fuel and Nitrogen is supplied for water atomization. Spray test facility and PDPA equipment were used in KARI(Korea Aerospace Research Institute). It was found that gas pressure change and spray distance is important value to spray atomization.

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Step-by-step Tests for Continuous Thrust Control Hot-firing Test (연속 추력제어 연소시험을 위한 단계별 시험들)

  • Cheolwoong Kang;Shinwoo Lee;Sunwoo Han;Kangyeong Lee ;Hadong Jung;Dongwoo Choi;Kyubok Ahn
    • Journal of the Korean Society of Propulsion Engineers
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    • v.27 no.1
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    • pp.58-67
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    • 2023
  • Results of dry-run tests, cold-flow tests, and hot-firing tests performed to throttle a methane engine uni-element thrust chamber are covered in the paper. After installing flow control valves on the oxidizer and fuel supply lines of the methane engine combustion test facility, a number of dry-run tests were repeated so that the valves could reach set strokes quickly and stably. Then, cold-flow tests using liquid nitrogen and gaseous nitrogen were conducted to confirm the stable supply of the simulated propellants according to the valve control. Finally, using liquid oxygen and gaseous methane, hot-firing tests for fixed and continuous thrust control of 50% to 10% of the nominal thrust were successfully performed.

Performance Test of 5MW Gas Turbine Engine Combustor (5MW 발전용 가스터빈 엔진 연소기 성능시험)

  • Park, Poo-Min;Kim, Hyung-Mo;Choi, Young-Ho;Yang, Soo-Seok;Chon, Mu-Hwan
    • Journal of the Korean Society of Combustion
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    • v.13 no.4
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    • pp.37-46
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    • 2008
  • Performance test of 5MW class gasturbine combustor was carried out at combustor test facility of KARI(Korea Aerospace Research Institute). The combustor is dry low NOx type premixed combustor and fuel is natural gas. The characteristics of combustor were measured including emission, pressure pulsation and exit temperature distribution. Optimum operation point of combustor was found by changing parameters like fuel ratio between pilot and main burner. The test result showed that the combustor performance is sufficient to satisfy the gasturbine system requirement.

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Performance Test for a Centrifugal Air Compressor (원심형 공기압축기 성능시험)

  • 신유환;안이기;김광호;손병진
    • Transactions of the Korean Society of Mechanical Engineers
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    • v.19 no.8
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    • pp.1964-1971
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    • 1995
  • In the present study, the performance characteristics of a centrifugal air compressor were investigated experimentally. The PC controlled performance test facility for a centrifugal air compressor driven by an electric motor with a gear box to achieve higher compressor rotating speed was set up in the present study. The performance test for a turbocharger compressor of a diesel engine was conducted, and in a case of 34,800 rpm, pressure ratio 1.18, flow rate 0.09kg/s, compressor efficiency 61% were investigated. Adiabatic power for a tested compressor showed maximum value at mass flow ratio 0.8. The value of mass flow ratio of maximum efficiency was about 0.37, it was independent of compressor rotating speed.

Noise Diagram of an Automotive Turbo Charger and Its Applications (차량용 터보차져의 소음도표 작성 및 응용)

  • Lee, Hyeong-Il
    • Transactions of the Korean Society for Noise and Vibration Engineering
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    • v.20 no.5
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    • pp.502-509
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    • 2010
  • A test facility which can simultaneously measure turbocharger operating condition variables and vibro-acoustic emission in the situations that are quite similar to real internal combustion engine operating conditions has been introduced. Using this facility, a new method sweeping from full open throttle to deep surge region along constant speed curves can be utilized instead of the stationary method that has been traditionally used to obtain turbocharger compressor maps. Data covering an extensive range of the compressor performance map have been collected and analyzed. An experimental study is performed to define a noise diagram that correlates vibro-acoustic measurements to aerothermodynamic operating conditions. An instrumentation set in the facility allows the automatic definition of the operating point on the turbine and compressor map of the turbocharger. Also, radiated sound pressure and casing vibration data corresponding to the point are obtained by a microphone in the vicinity of the compressor casing and an accelerometer on the casing. The major source(s) of noise at specific operating point on the map can be easily identified with these maps. Also, acoustic characteristics of a given turbocharger at the vicinity of the surge as well as in the surge are also defined. Finally, the possibility to define mild surge region of a turbocharger using vibro-acoustic measurements is studied.

Thrust Measurement in a Impulse Facility (충격파 시험장치를 이용한 추력 측정)

  • Jin, Sangwook;Hwang, Kiyoung;Park, Dongchang;Min, Seongki
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.310-319
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    • 2017
  • This paper introduces the method how to measure the thrust in impulse facility. In a Facility having such a short duration time of steady flow, there's no time to reach a steady state of the forces acting on model so that the test model vibrates until the end of the flow. The forces exerted on an engine exist with vibration so that the usual force balance can not be used. SWFB(Stress Wave Force Balance) technique is utilized in a shock tunnel to get the thrust. As an example, a model force balance has been calculated its strain against impulse force by using FEM(Finite Element Method). A transfer function between the impulse force and strain has been obtained by the way of de-convolution.

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Combustion Test of a Mach 5 Scramjet Engine Model (마하 5 스크램젯 엔진 모델의 연소 시험)

  • Yang, Inyoung;Lee, Yang-Ji;Kim, Young-Moon;Lee, Kyung-Jae
    • Journal of the Korean Society of Propulsion Engineers
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    • v.17 no.3
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    • pp.9-14
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    • 2013
  • Combustion tests were conducted for a hydrogen-fueled Mach 5 scramjet engine model using a blow-down facility. No fuel and two fuel flow rate cases were tested for two different model configurations. Time history of the wall static pressures inside the model and their time-averaged spatial distribution were used for the analysis of the flow and combustion characteristics. For shorter model, supersonic combustion was occurred for both of the fuel flow rate cases. For longer model, supersonic combustion was occurred for less fuel case, whereas thermal choking and subsonic combustion were occurred for more fuel case. Intake started even for this subsonic combustion case.

Periscope Imaging System Design and Analysis for Flame Front Visualization (화염 정면 가시화를 위한 페리스코프 영상 시스템 설계 및 해석)

  • Shin, Jaeik
    • Journal of Aerospace System Engineering
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    • v.13 no.5
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    • pp.16-23
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    • 2019
  • This paper describes the design and analysis of a periscope imaging system installed at the engine test facility in the Agency for Defense Development. The periscope system is a cylinder-shaped image observation system installed at the rear of the engine and at the top of the diffuser. The periscope system has high risk of breaking because it is directly affected by high temperature (2300 K) and products of combustion. Thus, we used 1D heat transfer calculation, and 2D and 3D CFD analysis to confirm the heat flux and temperature distribution. Also, the cooling performance was verified. In the current design, using the periscope system, we can see flame shapes, control of the nozzle, and stability of the exhaust flow visually.

Technology Demonstration Plan and Status of a 75-$Ton_f$ LRE Thrust Chamber (75톤급 액체로켓엔진 연소기 기술검증 계획 및 현황)

  • Choi, Hwan-Seok;Han, Young-Min;Kim, Young-Mog
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.11a
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    • pp.15-18
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    • 2009
  • Technology demonstration for the development of a 75-tonf liquid rocket engine(LRE) thrust chamber for a space launch vehicle has been started on the basis of the previously acquired 30-tonf LRE technologies. For this purpose, a technology demonstration plan was established upon considering the currently available firing test facility in Korea and performance evaluation firing tests were performed on technology demonstration model thrust chambers under a restricted test condition. This paper describes the plan and current status of technology demonstration for a 75-tonf LRE thrust chamber.

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A Study on the Risk Reduction Method for Liquid Rocket Test Facility (액체로켓 시험설비에서의 위험감소 방법)

  • Lee Jung-Ho;Kim Yong-Wook;Bershadskiy V. A.;Kang Sun-Il;Cho Sang-Yeon;Oh Seung-Hyub
    • Journal of the Korean Society of Propulsion Engineers
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    • v.9 no.3
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    • pp.120-126
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    • 2005
  • The method of decreasing the ecological risk for the LRE(Liquid Rocket Engine) test is developed, working on the cryogenic oxidizer and the high-boiling fuel(Kerosene). This Method is based on the study that contains a technical solution method and an accident occurrence range for decreasing of accident probability and damage. This paper contains schematic on the all risk circumstance bring to accident, block-diagram for an accident growth process in case of the propellant leakage, technical solution method and risk reduction evaluation method. It will be used to alternative method for the risk reduction of complex technical systems.