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.

超声速燃烧RAMJET发动机是航天飞机的重要技术之一。为了研究这种燃烧现象，激波通道是一种有用的实验设备。本研究为超声速燃烧实验搭建了新的激波通道装置。此外，为了将粒子图像测速技术应用于激波风洞，对高性能风力机进行了PIV测量。得到如下结果：激波隧道·新的激波隧道与拉瓦尔喷嘴-马赫数2.0已建成。高压管长1.2m，低压管长6.0m。在0.9Mpa、低压10.5kPa的氦气驱动条件下，实现了1009.4m/s的冲击速度。当试验段马赫数为2.0时，估计压力为104.8kPa，温度为995.1K。PIV·用粒子图像测速法测量带边缘扩散器的风力涡轮机的瞬时流速。PIV用于表示模型内部流场和下游流场在雷诺数0.9×10^5（涡轮叶片旋转，3620 rpm）下的速度矢量。·通过数据分析螺旋结构。动画显示了随时间变化的速度场。·时间平均流速矢量是在瞬时流速数据的平均值上得到的。在风力机的下游有两个涡旋。一种是缘后附近的非定常涡，另一种是风力机下游场的大阻塞涡。大阻塞涡在瞬时流矢量动画中不明显，但在时间平均流场中明显存在。

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

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 Measurement of Flow Field around a Wind Turbine with Compact-type Brimmed Diffuser

采用紧凑型边缘扩散器的风力发电机周围流场的 PIV 测量

• 发表时间: 2006
• 期刊: Proceedings of the 44^<th> Meeting of the Chugoku and Shikoku Branch of the JSME
• 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
• 通讯作者: Kazuhiko Toshimitsu