@techreport{oai:jaxa.repo.nii.ac.jp:00044794,
 author = {鈴木, 邦男 and 堀内, 正司 and 松木, 正勝 and 鳥崎, 忠雄 and SUZUKI, Kunio and HORIUCHI, Shoji and MATSUKI, Masakatsu and TORISAKI, Tadao},
 month = {Aug},
 note = {A facility for testing annular combustors for turbofan engines is operated in the National Aerospace Laboratory(Tokyo). The facility provides a maximum air-flow rate of 25kg/s and an operating pressure up to 15kg/cm2 abs. can be attained. An air-temperature of up to 723K at the combustor inlet is permitted. Special provision is taken at the facility to reduce both pollutants in the exhaust gas emissions, and noise, because the laboratory is situated in a residential district. The main features of the facility and the planning involved in its design are described. Construction of the facility was sponsored by the Ministry of International Trade and Industry, which is handling the National Project for development of a turbofan engine., 資料番号: NALTR0540000, レポート番号: NAL TR-540},
 title = {環状(アニュラ形)燃焼器高圧燃焼試験装置},
 year = {1978}
}