並列タイトル等ガスタービン筒形燃焼器出口断面での風速および温度分布の測定
タイトル(掲載誌)航空宇宙技術研究所資料 = Technical Memorandum of National Aerospace Laboratory
一般注記Detailed velocity and temperature profile data at the exit plane of a high pressure gas turbine tubular combustor were obtained at atmospheric conditions. Such data are very requisite for designing a high performance turbine, but there is no data presently available that takes into account the combustor characteristics. Measurements were made under atmospheric conditions but were adjusted to have the same Mach number at the exit plane as under design conditions, which were a pressure of 55 atm and a temperature of 1600K. The resultant temperature profiles were compared with those data obtained in the high pressure combustion test.
資料番号: NALTM0609000
レポート番号: NAL TM-609
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=44192&item_no=1&attribute_id=31&file_no=1
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース(IRDB)(機関リポジトリ)
提供元機関・データベース宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ