Parameters Study for Three-Dimensional Flow of Scramjet

View Statistics Email Alert RSS Feed

Information

Details

Project title

Code/計畫編號

MOST107-2623-E019-002-D

Translated Name/計畫中文名

三維超燃衝壓引擎之流道設計參數研究

Project Coordinator/計畫主持人

Juan-Chen Huang

Funding Organization/主管機關

National Science and Technology Council

Department/Unit

Department of Merchant Marine

Website

https://www.grb.gov.tw/search/planDetail?id=12426404

Year

2018

Start date/計畫起

01-01-2018

Expected Completion/計畫迄

31-12-2018

Bugetid/研究經費

680千元

ResearchField/研究領域

機械工程

超燃衝壓引擎(SCRAMJET)是最適合於極音速巡航的吸氣式引擎，極音速載具具有快速反應與高穿透性之優勢，是先進國家積極投入研發的技術。本計畫規劃以燃燒化學反應流數值模擬技術，進行超燃衝壓引擎三維燃燒熱流場模擬分析，包含截面轉換進氣道、隔離段、燃燒室與尾噴管等內流道組件，以及增強燃料混合和穩定燃燒構件。依據中科院需求規格完成三維截面轉換內收縮極音速進氣道設計與複合式燃料噴注與火焰穩定器設計，並且進行燃燒室外型、複合式燃料噴注與火焰穩定器優化設計等工作。本研究複合式燃料噴注與火焰穩定器是綜合凹槽、背風臺階、斜面、噴流等構件新開發的裝置。三維超燃衝壓引擎燃燒熱流場模擬技術是採用104年學術合作計畫「雙燃燒室衝壓引擎之次音速燃燒室流場模擬分析」所發展數值模擬程式。截面轉換進氣道構型是依據105年學術合作計畫「鈍角效應下之截面轉換三維極音速進氣道設計技術研發」完成的進氣道設計技術。本計畫將開發燃燒室構型設計與增強燃料混合和穩定燃燒的設計分析技術，建構超音速燃燒衝壓引擎設計的相關能量。配合國內超燃衝壓引擎技術開發，使極音速氣動力學的研究與應用更完備，提供國內探空火箭、國防科技與產業發展相當的助益"Scramjet is an aspirated engine by far the most suitable for hypersonic vehicles. The vehicles have the advantage of high penetration and very rapid maneuvering responses. Many advanced countries actively involved in research of Scramjet techniques. In this project, the combusting flow field of the three-dimensional Scramjet is implementing by a high order accurate CFD technique with chemical reaction model. We will design the three-dimensional REST hypersonic inlet base on the requirements of CSIST, as well as a new fuel injector and flame holder which hybrid of step-jet-ramp-cavity components. With the new design combustor as initial configuration, we will performing the optimization design procedures to combustor to obtain the final configuration. The numerical simulation method used in present study was developed within the academic cooperation program of CSIST ""Flow Fields Simulation of a Dual Combustor SCRAMJET"" in 2015, and the method of REST inlet design was implemented with the CSIST program ""Three Dimensional Hypersonic Inlet with REST Under Blunt Nose Effects"" in 2016. The research topics of this project are: (1) the configuration design with geometrical parameterization of a three-dimensional scramjet, (2) combustion flow simulation of Scramjet and performance evaluation, (3) design and evaluation of hybrid mixing enhancement and flame stabilization of step-jet-ramp-cavity components, (4) develop the optimization procedures for combustor and fuel injectors. The project will implement the design techniques for combustor configuration, fuel injector, and flame holder, which enhanced fuel mixing and stable combustion, as well as to construct the relevant ability for the design of the Scramjet. With the development of Scramjet engine technology, so that more plentifully studies of hypersonic aerodynamics will performed. It provide considerable help to national defense science and technology and industry development."

Keyword(s)

超音速燃燒衝壓引擎
方轉橢圓型三維極音速進氣道
燃燒室
燃料噴注器
駐焰穩定器
WENO算則
SCRAMJET
REST
combustor
chemical reaction flow
step-jet-ramp-cavity hybrid injector
flame holder
WENO scheme

DSpace CRIS

Parameters Study for Three-Dimensional Flow of Scramjet

Details

Description