权益分类	功能权益	普通用户	{{item.name}}会员
{{category.name}}	{{benefitItem.name}}

Study on Experimental Technique for Supersonic Combustion

超音速燃烧实验技术研究

基本信息

批准号：
03045021
负责人：
TSUBOI Takao
金额：
$ 3.58万
依托单位：
Yokohama National University
依托单位国家：
日本
项目类别：
Grant-in-Aid for international Scientific Research
财政年份：
1991
资助国家：
日本
起止时间：
1991 至 1993
项目状态：
已结题

来源：
https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-03045021/
关键词：
Shock wave Shock tube Supersonic flow Supersonic Combustion SCRAM Spray Combustion 噴霧燃焼 Shock wave Shock tube Supersonic flow Combustion SCRAM Spray Combustion

项目摘要

Usually one needs large facilities for the experiments of the SCRAM-JET. When studying the supersonic combustion in the laboratory of university-size, one has to develop the facilities of small size. From these points of view we planned the project to find any possibilities to develop such system under co-working with Rheinisch-Westfaelische Technische Hochschule Aachen in Germany.During the past 3 years of this project we invited three researchers from the shock wave laboratory in RWTH Aachen and sent three professors from our side to their laboratory. The results of supersonic combustion at Yokohama National University and the technique of supersonic flow measurements at RWTH Aachen were exchanged. In three years we could obtain the following results :1.(Model I)(1)In the Laboratory of Thermophysics at Yokohama National University we obtained the flow of Mach-number 2 in the incident shock wave and accelerated the flow using divergent nozzle until Mach-number 5. We propagated the detonation from the side of down stream and observed decrease of the propagating velocity of detonation. (2)Using these results we designed a larger facility to obtain the supersonic flow of Mach-number 6-7. Presently in TH Aachen this supersonic wind tunnel is being built. After this project we plan to develop an experiment to obtain the standing detonation.2.(Model II)In Yokohama we built the Laval-nozzle to obtain Mach-number 5. (1)Using this nozzle we measured the flow velocity (Mach-number) etc. : (1.1)From the stagnation and static pressures we calculated Mach-number in the nozzle. (1.2)We took the Schlieren and shadow photographs by using Nano-spark light source and measured Mach-number 5 using the angle of the oblique shock wave. (1.3)We directly measured the flow velocity by light extinction of small particles seeded in the flow, and obtained 600-700 m/s, which corresponded to the Mach-number 5.

通常，人们需要大型设备来进行SCRAM喷气试验。在大学规模的实验室中研究超音速燃烧时，必须开发小型设备。从这些角度来看，我们计划在与德国亚琛莱茵-威斯法利施技术公司合作的情况下，寻找开发这种系统的任何可能性。在这个项目的过去3年里，我们邀请了来自亚琛RWTH冲击波实验室的三名研究人员，并从我们这边派遣了三名教授到他们的实验室。交流了横滨国立大学的超音速燃烧结果和亚琛RWTH的超音速流动测量技术。在三年的时间里，我们获得了以下结果：1.(模型I)(1)在横滨国立大学热物理实验室，我们得到了入射激波中马赫数为2的流动，并用扩张喷管加速到马赫数为5。我们从下游一侧传播爆轰，观察到爆轰传播速度的降低。(2)利用这些结果，我们设计了一个较大的装置来获得马赫数为6-7的超音速流动。目前，在亚琛正在建造这个超音速风洞。2.在横滨，我们建造了拉瓦尔喷管，获得了马赫数5。(1)利用这个喷嘴，我们测量了气流的速度(马赫数)等：(1.1)根据静压和静压，我们计算了喷管中的马赫数。(1.2)利用纳米火花光源拍摄了纹影和阴影照片，并利用斜激波的角度测量了马赫数5。(1)利用小颗粒在水流中的消光直接测量流速，得到600-700m/S，与马赫数5相对应。