@article{oai:jaxa.repo.nii.ac.jp:00031473,
 author = {辻, 広 and 堀, 守雄 and 岡野, 達夫 and 山岡, 市郎 and TSUJI, Hiroshi and HORI, Morio and OKANO, Tatsuo and YAMAOKA, Ichiro},
 issue = {4_B},
 journal = {東京大学宇宙航空研究所報告},
 month = {Dec},
 note = {This paper presents a detailed description of the continuous flow combustion apparatus, namely the variable pressure combustion tunnel, recently established at the combustion laboratory with the object of studying the combustion phenomena in the flowing system. This apparatus can cover the pressure range from 10 mmHg abs to 6 kg/cm^2-G, and is equipped with pneumatic control valves to maintain the flow rates and the pressure in the combustion chamber automatically at the preset values. The air is supplied from a two-stage screw compressor (flow rate, 780 Nm^3/hr at 6 kg/cm^2-G) or from a high pressure air reservoir (capacity, 524 m^3; maximum pressure, 15kg/cm^2-G). The city gas is fed by a oilfree piston-type compressor (flow rate, 200 Nm^3/hr at 6 kg/cm^2-G). In order to measure and control the flow rates over a wide range as accurately as possible, seven orifices of succesive capacities and four control valves are installed in air feed line, and six orifices and three control valves in gas feed line. Air and city gas, metered separately, are mixed and the combustible gaseous mixtures are fed to the vertical combustion chamber, the horizontal combustion chamber or the research rocket motor of gaseous propellant, etc., 資料番号: SA0124359000},
 pages = {475--498},
 title = {<論文>新たに改造設備された連続燃焼実験装置(高速内部流体実験施設報告)},
 volume = {1},
 year = {1965}
}