• Title/Summary/Keyword: 이젝터 제트

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A Study On the Ejector Design Technique And Flow Characteristics (초음속 지상추진시험설비의 이젝터 설계 기법 및 유동 특성 연구)

  • Lee Yang-Ji;Cha Bong-Jun;Yang Soo-Seok
    • Journal of the Korean Society of Propulsion Engineers
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    • v.10 no.1
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    • pp.54-63
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    • 2006
  • Ejector system are used to transport a low momentum flow to the higher pressure flow by the momentum change between high and low momentum flows. This system is used to simulate the high altitude and Mach number condition over altitude 20 km and Mach 4 of the supersonic test facility. We applied the design and the performance analysis technique(EISIMP code) of the Ramjet Test Facility(RJTF) air system in JAXA to the ejector system of the ramjet test facility in KARI. After preliminary design of the ejector system, we performed a computational study using FLUENT and investigated shock structures and flow characteristics of the ejector system.

An Experimental Study of Subsonic/Supersonic Ejector Flows (아음속/초음속 공기 이젝터에 관한 실험적 연구)

  • 권오식;이준희;최보규;김희동
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2000.11a
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    • pp.33-33
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    • 2000
  • 고압의 공기를 노즐을 통하여 가속시켜. 노즐 출구로부터 방출하는 경우 제트 경계부근에서 발생하는 강한 전단작용과 제트 내부에서 발생하는 압력강하로 인하여 주변의 기체가 제트유동으로 유입하게 된다. 이러한 원리를 응용한 대표적 유체기계로 이젝터를 들 수 있다. 최근 이젝터 시스템은 각종 플랜트 시설, 냉공조 시설, 고도시뮬레이션 장치뿐만 아니라 건설장비 등에까지 다양하게 응용되고 있다.(중략)

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Freejet 타입 램제트 엔진 성능시험기 기본설계

  • Lee, Yang-Ji;Cha, Bong-Jun;Yang, Soo-Seok
    • Aerospace Engineering and Technology
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    • v.3 no.1
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    • pp.65-78
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    • 2004
  • This research was conducted for an acquisition of the ramjet engine test facility design technique which are concerned about freejet type test facility. In this research, we concentrated on the design technique and the construction technique of the vitiation air heater(VAH), test section, diffuser and ejector. Based on the operating modes of the basic test facility, ten operating modes in coordinates "Altitude-Mach number" was regenerated from Mach 2, Altitude 0km to Mach 5, Altitude 15km. In this operating modes, we calculated a design parameter of the supersonic nozzle, VAH, diffuser and ejector and acquired a technique for the ramjet test facility operating and repairing.

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Conceptual Design of Rocket Based Combined Cycle Engine (Rocket Based Combined Cycle Engine의 개념설계 연구)

  • Lee, Yang-Ji;Kang, Sang-Hun;Yang, Soo-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.11a
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    • pp.581-585
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    • 2009
  • In this study, conceptual design of the RBCC (Rocket Based Combined Cycle) engine was performed for the hypersonic propulsion system development. For the flight mission, RBCC engine takes off at sea level and accelerates up to Mach 8 at the altitude of 30km. By the flight speed characteristics, operating pattern of the engine is categorized into 3 modes : Ejector jet (~Mach 3), Ramjet (Mach 3~6), Scramjet (Mach 6~8). According to the engine mode characteristics, RBCC engine design and analysis was performed.

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A NUMERICAL STUDIES ON THE FLOW PROPERTIES OF AXI-SYMMETRIC ANNULAR BELL TYPE EJECTOR-JETS (축대칭 환형 분사식 이젝터 제트 유동 특성의 수치적 연구)

  • Park, G.H.;Kwon, S.J.
    • 한국전산유체공학회:학술대회논문집
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    • 2006.10a
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    • pp.185-188
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    • 2006
  • An investigation of the ejector-jets focusing on its flow properties was carried out by varying the geometric parameters. The area ratio of the primary nozzle, AR that was tested in the present measurement was 2.17 and 3.18, while the ratio of the length to the diameter of the duct downstream the primary nozzle inlet, L/D had values of 3.41, 6.82, and 10.23. For the frame work of flow characteristics, the wall pressures distribution of ejector-jet was investigated by experiment for basic study of ejector-jet performance. In result, terminal shock location and existence of series of oblique shocks are recognized. In this study, CFD analysis was conducted at the same time. And as a result of comparison experiment data with CFD analysis, the physical phenomena of ejector-jets were estimated.

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INTERNAL FLOW PROPERTIES AND THRUST CHARACTERISTICS OF AXI-SYMMETRIC ANNULAR BELL TYPE EJECTOR-JET (축대칭 환형 이젝터 제트의 내부 유동과 추력특성)

  • Park, G.H.;Kwon, S.J.
    • Journal of computational fluids engineering
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    • v.12 no.2
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    • pp.46-52
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    • 2007
  • An experimental and numerical investigation of the ejector-jets focusing on its geometric parameters that effect on thrust performance was carried out. The area ratio of the primary nozzle that was tested in the present study was 2.17 and 3.18, while the ratio of the length to the diameter of the duct downstream the primary nozzle inlet had values of 3.41, 6.82, and 10.23. Internal flow properties of ejector-jet were estimated by comparison experiment data and CFD analysis for basic study of ejector-jet thrust performance. For examination of thrust performance, the thrust ratios increased with increase in L/D. Especially at AR=2.17, the maximum thrust augmentation was 33 percent for the shortest L/D. It is expected that the increase of mixing duct length of ejector-jet will be helpful in a thrust performance by improving mixing efficiency.

INTERNAL FLOW PROPERTIES AND THRUST CHARACTERISTICS OF AXI-SYMMETRIC ANNULAR BELL TYPE EJECTOR-JET (축대칭 환형 이젝터 제트의 내부 유동과 추력특성)

  • Park, G.H.;Kwon, S.J.
    • 한국전산유체공학회:학술대회논문집
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    • 2007.04a
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    • pp.166-170
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    • 2007
  • An experimental and numerical investigation of the ejector-jets focusing on its geometric parameters that effect on thrust performance was carried out. The area ratio of the primary nozzle that was tested in the present studywas 2.17 and 3.18, while the ratio of the length to the diameter of the duct downstream the primary nozzle inlet had values of 3.41, 6.82, and 10.23. Internal flow properties of ejector-jet were estimated by comparison experiment data and CFD analysis for basic study of ejector-jet thrust performance. For examination of thrust performance, the thrust ratios increased with increase in L/D. Especially at AR=2.17, the maximum thrust augmentation was 34 percent for the shortest L/D. It is expected that the increase of mixing duct length of ejector-jet will be helpful in a thrust performance by improving mixing efficiency.

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Multi-Ejector Design for High Altitude Simulation (고고도 환경 모사를 위한 멀티 이젝터 설계)

  • NamKoung, Hyuck-Joon;Shim, Chang-Yol;Lee, Jae-Ho;Park, Sun-Sang
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.705-708
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    • 2011
  • Ejector system can induce the secondary flow or affect the secondary chamber pressure by both shear stress and pressure drop which are generated in the primary jet boundary. Ejectors are widely used in a range of applications such as a turbine-based combined-cycle propulsion system and a high altitude test facility for rocket engine, pressure recovery system, desalination plant and ejector ramjet etc. The primary interest of this study is to set up an design procedure on the configuration and operating condition of multi-ejector for the various high altitude simulation.

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1-D Analysis of Tandem-ejector for the Engine-bay Ventilation (엔진베이 환기용 탠덤 이젝터의 1차원 해석모델링 기법 개발)

  • Im, Ju Hyun;Kim, Myung Ho;Kim, Yeong Ryeon;Jun, Sang In
    • Journal of the Korean Society of Propulsion Engineers
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    • v.18 no.4
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    • pp.81-89
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    • 2014
  • Tandem-ejector has been devised for engine-bay cooling. In this study, 1-D model has been developed to analyze Tandem-ejector. In the model, the primary, the secondary and the tertiary flow conditions have been analyzed with isentropic process. The mixing process has been analyzed with conservation laws based on the control volume analysis. The total pressure loss of the primary flow has been analyzed under the matching condition between the static pressure of Tandem-ejector discharge flow and atmospheric pressure. Consequently, 1-D model can predict Tandem-ejector performance accurately and provide the performance map.

Conceptual Design Study on Rocket Based Combined Cycle Engine (로켓 기반 복합사이클 엔진의 개념설계)

  • Kang, Sang Hun;Lee, Yang Ji;Yang, Soo Seok
    • Aerospace Engineering and Technology
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    • v.12 no.1
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    • pp.111-119
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    • 2013
  • Conceptual design of RBCC (Rocket Based Combined Cycle) engine is performed through the thermodynamic cycle analysis. The engine is designed to take off at sea level and accelerate to Mach 8 at 30 km altitude. According to the flight speed, the engine operating modes are categorized into 3 modes : Ejectorjet (~ Mach 3), Ramjet (Mach 3~6), Scramjet (Mach 6~8). As a design result, the engine has a diameter of 1 m and a length of 6.7 m. In the prediction results, its maximum thrust is 16.5 ton. In Ramjet and Scramjet modes, design condition of the engine intake influence the engine thrust according to the flight speed.