Velocity, Pressure and Temperature Measurement in Low-Pressure Supersonic Flow

低压超音速流中的速度、压力和温度测量

• 批准号: 06805023
• 负责人: TSUBOI Takao
• 金额: $ 1.15万
• 依托单位: Yokahama National University
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for General Scientific Research (C)
• 财政年份: 1994
• 资助国家: 日本
• 起止时间: 1994 至 1995
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-06805023/
• 关键词: Supersonic fiow; Tube window tunnei; Spray combustion; Shadow photograph; Temperature measurement; ルトビ-ク管

The large scale supersonic window tunnels are usually applied for the study of SCRAM jet engine. However, one cannot use the large window tunnel in a small laboratory, such as in a university, if one consider the running cost, the safety and the scale of facility. Therefore, we developed the small scale window tunnel and tried to measure the flow velocity, the Mach unmber, the density and temperature, as well as the pressure of unsteady flow within submilliseconds in two steel rectangular tube window tunnels. To know the above-mentioned variables we measured the static pressures, obtained the shadow photographs and the light absorption of infrared He-Ne laser at 3.39 mum, and measured the velocity of the small particles seeded in the gas in the cold model, where the room temperature air and nitrogen in the high pressure section are expanded through the throat into the low pressure section.The one throat of tunnel is 38 mm wide and 10 mm high and the other is 20 x 5 mm^2. Using these wi … More ndow tunnels we could obtain the Mach number 4-4.5, the temperature 30-50 K,0.5-2kPa.Since we confirmed that the temperature, the velosity, and the Mach number agreed with those calculated from the static pressure, we used the static pressure measurement for the experiment of hot model, where the burned gas of wxygen rich mixture in the high pressure section expanded into the low pressure section. The hot model experimet was performed in a 6 meter long steel tube of 100 mm diameter with 150 liter dump tand. In the low pressure section we could obtain the same Mach numbers as designed, which depended on the premixed propane-oxygen mixture conditions. The temperatures in the expandedcondition were 700,820, and 1200 K.In this tunnel the liquid fuel (n-pentane) was sprayd into the laval nozzle for about 10 ms. The self ignition was observed at about 2 m from the nozzle using the time histories of gas radiation and static pressure.Through these experiments we could confirme the spray ignition and combustion in supersonic flow of Mach number 4-5. Less

大型超音速窗口风洞常用于SCRAM喷气发动机的研究。然而，如果考虑到运行成本、安全性和设施规模，就不能在小型实验室(如大学)使用大窗口隧道。为此，我们研制了小型窗口隧道，并尝试在亚毫秒内测量了两个矩形钢管窗口隧道内的流速、马赫数、密度、温度以及非定常流动的压力。为了了解上述参数，我们测量了隧道的静压，获得了3.39 nm红外He-Ne激光的阴影照片和光吸收，并测量了在冷模中加入气体的小颗粒的速度。在冷模中，高压段的室温空气和氮气通过喉道膨胀进入低压段。隧道的一个喉道宽38 mm，高10 mm，另一个喉管高20×5 mm^2。利用这些…更多的NDOW风洞可以得到马赫数4-4.5，温度30-50K，0.5-2kPa.由于我们确认了温度、速度和马赫数与静压计算的结果一致，我们使用静压测量进行了热模型实验，其中高压段富氧混合物燃烧的气体扩展到了低压段。热模型试验是在直径100 mm、长6米、排土量为150升的钢管中进行的。在低压段，可以得到与设计相同的马赫数，这取决于预混丙烷-氧气混合气的条件。膨胀条件下的温度分别为700K、820K和1200K。在这个隧道中，液体燃料(正戊烷)被喷入拉瓦尔喷嘴约10ms。利用气体辐射时程和静压时程，在距喷嘴约2m处观察到了自燃现象，从而证实了马赫数为4-5的超音速流动中的喷雾点火和燃烧。较少

项目成果

佐々木哲也: "超音速流中での噴霧着火の研究" 平成6年度衝撃波シンポジウム講演論文集. 235-238 (1995)

Tetsuya Sasaki：“超音速流中喷雾点火的研究”1994 年冲击波研讨会论文集 235-238 (1995)。

坪井孝夫,望月靖文,石井一洋: "超音速流中での噴霧燃焼の研究" 気体中の衝撃波現象とその工学的応用に関する調査研究分科会成果報告書. 81-83 (1995)

Takao Tsuboi，Yasufumi Mochizuki，Kazuhiro Ishii：“超音速流中喷雾燃烧的研究”气体冲击波现象及其工程应用研究小组的结果报告81-83（1995）。

伊藤,望月,坪井,佐々木,石井: "超音速流の温度、圧力、流速測定" 平成6年度衝撃波シンポジウム講演集. 1995.

Ito、Mochizuki、Tsuboi、Sasaki、Ishii：“超音速流的温度、压力和速度测量”1994 年冲击波研讨会论文集，1995 年。

Takao Tsuboi: "Velocity,Pressure and Temperature Measurement in Low-Pressure Supersonic Flow" Japanese Journal of Applied Physics. Vol.35. (1996)

Takao Tsuboi：“低压超音速流中的速度、压力和温度测量”日本应用物理学杂志。

Shintaro Itoh: "Temperature-, Pressure-, Velocity-Measurement in Supersonic Flow" Prepnint of Symposium on SHOCK WAVES.JAPAN'95. 673-676 (1995)

Shintaro Itoh：“超音速流中的温度、压力、速度测量”SHOCK WAVES.JAPAN95 研讨会筹备工作。