タービン翼の前縁部吹出しフィルム冷却に関する基礎実験(Ⅱ)吹出し流れの可視化

Material type: 規格・テクニカルリポート類

Author: 佐々木, 誠ほか

Publisher: 航空宇宙技術研究所

Publication date: 1975-07

Material Format: Digital

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Note (General)：: 出版タイプ： NACoolant flow on a plane model with a cylindrical nose, which simulates the leading edge portion of a film-cooled turbine blade, was studied b...

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Material Type: 規格・テクニカルリポート類
Title: タービン翼の前縁部吹出しフィルム冷却に関する基礎実験(Ⅱ)吹出し流れの可視化
Author/Editor: 佐々木, 誠
高原, 北雄
熊谷, 隆王
SASAKI, Makoto
TAKAHARA, Kitao
KUMAGAI, Takao
Author Heading: SASAKI, Makoto
TAKAHARA, Kitao
KUMAGAI, Takao
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1975-07
Publication Date (W3CDTF): 1975
Alternative Title: Preliminary Experiments on Film Cooling of Turbine Blades with Injection near the Leading Edge(II)Visualization of the Injected Coolant Flow
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-418
No. or year of volume/issue: 418
Volume: 418
Pages: 18-
ISSN (Periodical Title): ISSN : 0389-4010
Target Audience: 一般
Note (General): 出版タイプ： NA
Coolant flow on a plane model with a cylindrical nose, which simulates the leading edge portion of a film-cooled turbine blade, was studied by means of a visualizing technique. The secondary air injected from rows of blowing holes located near the leading edge of the model was visualized by adding vapor of paraffin into it. The change of the flow pattern of the injected jets was examined and compared with the change of the pressure distribution on the model surface, the blowing characteristics and the change of the film cooling effectiveness reported in the previous paper. When the ratio of the momentum flux of the injected jets to that of the mainstream exceeded a critical value, the jets tended to blow off the surface. This blow-off(lift-off) caused a fall in the film cooling effectiveness near the blowing holes. With injection through holes inclined in the spanwise direction, the surface was covered more effectively and the onset of the blow-off was delayed. The thickness of the injected coolant flow was much greater than that of the boundary layer without injection.
資料番号: NALTR0418000
レポート番号: NAL TR-418
Data Provider (Database): 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）
https://irdb.nii.ac.jp
Original Data Provider (Database): 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