A Study on PIV Measurement of Supersonic Combustion by a Shock Tunnel

激波风洞PIV测量超音速燃烧的研究

• 批准号: 16560692
• 负责人: TOSHIMITSU Kazuhiko
• 金额: $ 2.43万
• 依托单位: Matsue National Collage of Technology
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (C)
• 财政年份: 2004
• 资助国家: 日本
• 起止时间: 2004 至 2005
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-16560692/
• 关键词: Shock Tunnel; PIV; Supersonic Flow; SCRAMJET Engine; Combustion Flow; Fluid Measurement; Velocity Field; Spaceplane; 乱流

For the spaceplanes the supersonic combustion RAMJET engine is one of the important technologies. In order to investigate such the combustion phenomenon, a shock tunnel is useful experimental facility. In the present study new shock tunnel facility for the supersonic combustion experiment has been constructed. Furthermore to apply a particle image velocimetry on the shock tunnel, PIV measurements of high performance wind turbine are carried out. The following results are obtained.Shock Tunnel・New shock tunnel with Laval nozzle - Mach number 2.0 has been built. The high pressure tube length and low pressure tube length are 1.2m and 6.0m respectively. For the condition of Helium driver gas with 0.9Mpa and low pressure at 10.5kPa, shock speed of 1009.4m/s has been realized. If the test section Mach number is 2.0,the pressure and temperature are estimated 104.8kPa and 995.1K respectively.PIV・The instantaneous flow velocity measurements of a wind turbine with a brimmed diffuser by particle image velocimetry. The PIV is used to show the velocity vectors of the inner and downstream flow fields of the model at Reynolds number, 0.9×10^5 for turbine blades rotating, 3620 rpm.・The vortical structure is analyzed through the data. The time dependent velocity fields are shown by the animation.・The time average flow velocity vectors are made on an average of the instantaneous velocity data. There are two vortices in the downstream of the wind turbine. One is unsteady vortex near behind the brim, and another is a large blockage vortex in the downstream field of the wind turbine. The large blockage vortex is not clear in the instantaneous flow vector animation, however it exists clearly in the time average flow field.

对于太空平面图，社区的电动机是重要的技术。高压管长度和低压管的长度为1.2m，对于0.9MPA的氦气状况，如果测试部分MACH为2.0，则在10.5kpa时进行了冲击速度F 10094m/s。 ，压力和温度估计分别为104.8kPa和995.1k。piv /粒子图像图像图像图像图像图像图像图像图像图像图像图像图像图像图像图像图像图像图像图像图像图像图像图像图像图像图像图像图像图像很刺激为54。 Anner anner anner anner anner anner anner anner anner anner anner anner anner a anner anner blades旋转的涡轮叶片的平均值由动画显示了瞬时速度的平均值。风力涡轮机。

项目成果

PIVによるコンパクトタイプ風レンズ風車まわりの流れ場計測

使用 PIV 测量紧凑型风透镜风力涡轮机周围的流场

• 发表时间: 2006
• 期刊: 日本機械学会中国四国支部第44期総会・講演会講演論文集
• 作者: 米田博幸;淺野和典;Norihiro Kato;Norihiro Kato;Norihiro Kato;Norihiro Kato;Norihiro Kato;高木亮治;高木亮治;Ryoji Takaki;Ryoji Takaki;高木亮治;高木亮治;利光和彦
• 通讯作者: 利光和彦

つば付きディフューザ風車後流のPIVによる速度場の時間的変動

边缘扩散器风力涡轮机尾流中 PIV 引起的速度场随时间变化

• 发表时间: 2004
• 期刊: 日本航空宇宙学会西部支部講演会講演集
• 作者: 利光和彦;春木 渉;大屋裕二
• 通讯作者: 大屋裕二

PIVによるつば付きディフューザ風車後流の渦構造解明

使用 PIV 阐明法兰扩散器风力涡轮机后面的涡流结构

• 发表时间: 2005
• 期刊: 日本機械学会流体工学部門講演会講演論文集 (CD-ROM)
• 作者: 米田博幸;淺野和典;Norihiro Kato;Norihiro Kato;Norihiro Kato;Norihiro Kato;Norihiro Kato;高木亮治;高木亮治;Ryoji Takaki;Ryoji Takaki;高木亮治;高木亮治;利光和彦;Kazuhiko Toshimitsu;利光和彦;Kazuhiko Toshimitsu;利光和彦
• 通讯作者: 利光和彦

PIVによるつば付きディフェーザ風車後流の渦構造解明

使用 PIV 阐明法兰相移器风力涡轮机尾流中的涡流结构

• 发表时间: 2005
• 期刊: 日本機械学会流体工学部門ン講演会講演論文集 (CD-ROM)
• 作者: 米田博幸;淺野和典;Norihiro Kato;Norihiro Kato;Norihiro Kato;Norihiro Kato;Norihiro Kato;高木亮治;高木亮治;Ryoji Takaki;Ryoji Takaki;高木亮治;高木亮治;利光和彦;Kazuhiko Toshimitsu;利光和彦
• 通讯作者: 利光和彦

Experimental Investigation of Vortex Structure of a Wind Turbine with a Brimmed Diffuser by a Particle Image Velocimetry

带有边缘扩散器的风力发电机涡流结构的粒子图像测速实验研究

• 发表时间: 2005
• 期刊: Proceedings of the JSME Fluid Engineering Conference 2005 No.1818
• 作者: 米田博幸;淺野和典;Norihiro Kato;Norihiro Kato;Norihiro Kato;Norihiro Kato;Norihiro Kato;高木亮治;高木亮治;Ryoji Takaki;Ryoji Takaki;高木亮治;高木亮治;利光和彦;Kazuhiko Toshimitsu;利光和彦;Kazuhiko Toshimitsu
• 通讯作者: Kazuhiko Toshimitsu