Space Technology Research Group, National Aerospace Laboratory(NAL)
Aeroengine Division, National Aerospace Laboratory(NAL)
Aeroengine Division, National Aerospace Laboratory(NAL)
Thermofluid Dynamics Division, National Aerospace Laboratory(NAL)
TOSHIBA Corporation
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-973
巻
973
ページ
10
発行年
1988-04
抄録（英）
Detailed temperature profiles in a twin valveless pulse combustor have been measured using a simplified CARS (coherent anti-Stokes Raman spectroscopy) technique to understand the fundamental pulse combustion process for burner design purpose. Time- and ensemble-averaged temperatures in the combustion chamber were obtained from a constant 20Hz data sampling and a phase locked data sampling, respectively. The CARS method successfully offered a near-real-time, non-intrusive temperature measurement system with high spatial and time resolutions. Results show that very large temperature oscillations of up to 600K exist near the wall upstream of the combustion chamber, while stable and homogeneous temperature regions were created in other regions. The maximum temperature was found to be lower about 200 to 400K than the adiabatic flame temperature. From a comparison of one-cycle ensemble data between temperature and heat release rate, there observed a similar tendency, this indicating that fuel-air mixing rate affects significantly the ignition dalay time during pulse combustion as described previously.
Study on a Twin Valveless Pulse Burner (Temperature Characteristics during Pulse Combustion)
naltr00973.pdf
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