並列タイトル等Preliminary Experiments on Film Cooling of Turbine Blades with Injection near the Leading Edge(I)Injection through Holes Located near the Leading Edge
タイトル（掲載誌）航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-371
一般注記Experiments were made on film cooling with injection through holes located near the leading edge of a model in a low-speed, room-temperature wind tunnel. The model, which simulates the leading edge portion of an air-cooled turbine blade section, consists of a semicircular cylinder with four rows of blowing holes and two flat plates forming the upper and lower surfaces of its body. The change of flow coefficient of the blowing holes, the pressure distributions and the temperature distributions(film cooling effectivenesses) along the surface of several models were measured. It is proved that the inclination of the blowing holes in the spanwise direction shows very high effectiveness, but that excessive injection sometimes lowers the effectiveness. The film cooling effectiveness of the experimental model and of an air-cooled turbine nozzle are calculated by means of an approximate method.
資料番号: NALTR0371000
レポート番号: NAL TR-371
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=44619&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