Aeroengine Division, National Aerospace Laboratory(NAL)
Aeroengine Division, National Aerospace Laboratory(NAL)
Aeroengine Division, National Aerospace Laboratory(NAL)
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
航空宇宙技術研究所報告
雑誌名(英)
Technical Report of National Aerospace Laboratory TR-459
巻
459
ページ
15
発行年
1976-06
抄録（英）
A fluidic high temperature sensor was constructed based on the authors’previous experiments with cool air. The sensor is basically a fluid oscillator with two feedback channels, in which the pressure wave travels at a speed determined mainly by the temperature of the working gas. The shape of the feedback channels and ratio of outlet nozzle area to main nozzle area was properly selected to obtain temperature-sensitive, pressure and noise-insensitive oscillatory characteristics. The sensor was made of stainless steel by the diffusion bonding method, and was designed to permit mounting on the wall of the turbine outlet duct. A test utilizing high temperature air and combusion gas(up to 800C) was conducted to obtain the static and dynamic characteristics of the sensor. Within the limits of the capability of the test apparatus, the maximum deviation from the calibration curve was found to be ±4C(up to 470C), and ±15C(higher than 470C), and the temperature-frequency sensitivity 2.5(Hz/C) at 750C. The sensor transferred a stable output signal the frequency of which was nearly insensitive to pressure changes at the inlet port within the range of a pressure ratio exceeding 2.5. The dynamic response of the sensor was represented by the combination of two first-order delays with time constants of less than 0.5 sec and more than 10 sec respectively.
ガスタービン用流体温度検出器の試作
naltr00459.pdf
(3.43MB)
