• Title/Summary/Keyword: 램제트엔진

Search Result 86, Processing Time 0.032 seconds

TBCC Engine Performance Design Technique of Reusable Launch Vehicle (재사용 우주 발사체의 TBCC 엔진 성능 설계 기법)

  • Kim, Sung-Jin;Sung, Hong-Gye
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2008.11a
    • /
    • pp.167-170
    • /
    • 2008
  • A TBCC(Turbine Based Combined Cycle) engine performance design method for reusable launch vehicles flying both in subsonic and supersonic regime was proposed. The TBCC consists of turbo jet engines and ramjet engines, operating individually or together according to operation schedule. The performance scheme of turbojet and ramjet was validated and the combined engine performance of the TBCC at a typical flight condition was analyzed.

  • PDF

Two Color PIV를 이용한 램제트엔진 연소기 특성에 대한 연구

  • 안규복;심재현;윤영빈
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2000.11a
    • /
    • pp.13-13
    • /
    • 2000
  • 램제트 엔진에 대한 기초 연구로서 양쪽 대칭의 공기 흡입구를 갖는 2차원 형태의 램제트엔진 연소기를 제작하여 그 특성을 분석하였다. 실험은 흡입공기의 연소실내 유입각도와 연소실내의 도움 위치에 따른 연소실 형상을 바꾸어가며 연소기내의 유동특성을 살펴보았다. 이를 위하여 고속 유동장의 2차원 평면 속도 분포를 측정할 수 있는 two color PIV 기법을 개발하였다. 이 기법은 다른 색의 두 레이저빔을 사용하여 방향성의 문제를 해결하며, 이미지의 색 분리에 따른 거의 완벽한 cross-correlation이 가능하며 높은 single-to-noise 비를 얻게 됨으로써 dynamic range의 증가가 가능해지며, 조사 영역 안에 존재해야 하는 입자 쌍의 수가 줄어들게 된다.(중략)

  • PDF

Performance Design of a Dual Mode Ramjet Engine (초음속에서 극초음속까지 비행을 위한 이중모드 램제트엔진의 성능 설계)

  • Choe, Se-Young;Yeom, Hyo-Won;Kim, Sun-Kyoung;Sung, Hong-Gye;Byun, Jong-Ryul;Yoon, Hyun-Gull
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2007.11a
    • /
    • pp.289-292
    • /
    • 2007
  • Performance of a dual mode ramjet engine based on the sensitivity analysis of design parameters (the gap between cowl and inlet spike and combustor length) was analyzed from the view points of aerodynamics and thermodynamics. A dual mode engine performing from supersonic to hypersonic (Mach no. 2 to 6) was designed in a proposed flight envelop. The design method and result were comparable to the results of the previous study, Hyperion RLV, and the CFD calculation.

  • PDF

Preliminary Performance Analysis of a Dual Combustion Ramjet Engine (이중연소 램제트 엔진의 예비 성능해석)

  • Byun, Jong-Ryul;Ahn, Joong-Ki;Yoon, Hyun-Gull;Lim, Jin-Shik
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.15 no.5
    • /
    • pp.72-81
    • /
    • 2011
  • In order to understand the operation characteristics and major design parameters of a dual combustion ramjet engine, a fundamental analysis model based on gasdynamics and thermodynamic theories was established. The preliminary performance analysis was accomplished and the results clearly describe the intimate relationship between air inlets, gas generator, and supersonic combustor. The methodology presented provides a means for quantitatively determining the geometries of the gas generator and supersonic combustor and assessing the effects on performance of each of the engine components. Also the design results for a basic configuration were provided.

Preliminary Performance Analysis of a Dual Combustion Ramjet Engine (이중연소 램제트 엔진의 예비 성능해석)

  • Byun, Jong-Ryul;Ahn, Joong-Ki;Yoon, Hyun-Gull;Lim, Jin-Shik
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2011.04a
    • /
    • pp.318-325
    • /
    • 2011
  • In order to understand the operation characteristics and major design parameters of a dual combustion ramjet engine, a fundamental analysis model based on gasdynamics and thermodynamic theories was established. The preliminary performance analysis was accomplished and the results clearly describe the intimate relationship between air inlets, gas generator, and supersonic combustor. The methodology presented provides a means for quantitatively determining the geometries of the gas generator and supersonic combustor and assessing the effects on performance of each of the engine components. Also the design results for a basic configuration were provided.

  • PDF

Freejet 타입 램제트 엔진 성능시험기 기본설계

  • Lee, Yang-Ji;Cha, Bong-Jun;Yang, Soo-Seok
    • Aerospace Engineering and Technology
    • /
    • v.3 no.1
    • /
    • pp.65-78
    • /
    • 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.

  • PDF

Characteristics of Performance Parameters of Dual Mode(Ramjet-Scramjet Combined) Engine Based on the Analysis of The Operating limitations (작동한계 관점에서의 이중모드(램제트-스크램제트 연합 작동)엔진의 성능 인자 특성)

  • Sung, Hong-Gye;Byun, Jong-Ryul
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2006.11a
    • /
    • pp.393-396
    • /
    • 2006
  • This paper presents the characteristics of the performance parameters of dual mode(ramjet-scramjet combined) engine, inlet and combustor for wide range of flight Mach number, resulted from the analysis of its operating limitations. The transitional-critical flight Mach number from ramjet to scramjet and the performance of two types of combustors, such as constant pressure- and constant area- combustor, are conceptually evaluated.

  • PDF

Papers : A Study on the Characteristics of the Ramjet Engine Combustor using a Two Color PIV Technique (논문 : Two Color PIV 기법을 이용한 램제트엔진 연소기 특성에 대한 연구)

  • An,Gyu-Bok;Yun,Yeong-Bin;Jeong,In-Seok;Heo,Hwan-Il
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.30 no.1
    • /
    • pp.95-104
    • /
    • 2002
  • A two color PIV technique has been developed for visualization of complex and high speed flow in a ramjet combustor. Two color PIV has the advantages that velocity distribytions in high speed flowfields can be measured simply by varying the time interval between two different laser beams and a directional ambiguity problem can be solved by color separation, and then a singnal-to-noise ratio can be increased through nearly perfect cross-correlation. As a basic research of the ramjet engine, a 2-D shaped combustor with two symmetric air intakes has been manufactured and an experimental study has been conducted using a two color PIV technique. The flow characteristics such as recirculation zones and two intake air mixing have been investigated varying inlet angles and dome heights. It is found that the size and air mass ratio of reciculation zones are affected mainly by an inlet angle, but not much by a dome height.

Performance Characteristics of a TBCC Engine with Turbo-Ramjet Engine Transition Mode (터보제트-램제트 엔진의 천이모드를 고려한 TBCC 엔진의 성능 특성)

  • Moon, Kyoo-Hwan;Sung, Hong-Gye
    • Journal of the Korean Society for Aeronautical & Space Sciences
    • /
    • v.44 no.2
    • /
    • pp.116-122
    • /
    • 2016
  • The performance characteristics of a TBCC engine considering the transition mode from a turbojet to a ramjet engine has been investigated. The performance of each engine was proposed and a transition mode of the TBCC engine has been evaluated by adjusting the operating rate of the ramjet engine and turbojet engine performance changes continuously. Based on the transition model, it was confirmed that the performance is continuously changed at various flight Mach numbers and altitudes. The performance characteristics including thrust and specific impulse considering various flight conditions and transition mode were analyzed, which testifies characteristics of the engine itself, as well as transition of the combined cycle.

Performance Analysis for Various Flight Conditions with Air Disturbance (대기외란을 적용한 램제트 엔진의 비행 조건별 성능 연구)

  • Seo, Bong-Gyun;Choi, Jae-Hyung;Sung, Hong-Gye;Park, Jung-Woo;Park, Ik-Soo;Yoon, Hyun-Gull
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • 2011.11a
    • /
    • pp.588-593
    • /
    • 2011
  • In this study, the performance analysis method for ramjet engine system with atmospheric air disturbance was proposed. Flight path was determined to satisfy dynamic pressure constant at each flight altitude. The atmospheric air disturbance incoming into a engine intake was simulated by the model Tank proposed. The performance parameters was investigated at each flight condition with air disturbance. Engine operation stability was evaluated as analysis of the normal shock position.

  • PDF