前縁フィルム冷却タービン動翼の研究(二次元翼列による冷却性能と空力性能)

Material type: 文書・図像類

Author: 坂田, 公夫ほか

Publisher: 航空宇宙技術研究所

Publication date: 1979-03

Material Format: Digital

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Note (General)：: To achieve a higher turbine inlet gas temperature(TIT), a new air-cooled turbine rotor blade, adopting film cooling in the vicinity of the leading edg...

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Material Type: 文書・図像類
Title: 前縁フィルム冷却タービン動翼の研究(二次元翼列による冷却性能と空力性能)
Author/Editor: 坂田, 公夫
吉田, 豊明
高原, 北雄
能瀬, 弘幸
井上, 重雄
三村, 富嗣雄
臼井, 弘
SAKATA, Kimio
YOSHIDA, Toyoaki
TAKAHARA, Kitao
NOSE, Hiroyuki
INOUE, Shigeo
MIMURA, Fujio
USUI, Hiroshi
Author Heading: 坂田, 公夫
吉田, 豊明
高原, 北雄
能瀬, 弘幸
井上, 重雄
三村, 富嗣雄
臼井, 弘
SAKATA, Kimio
YOSHIDA, Toyoaki
TAKAHARA, Kitao
NOSE, Hiroyuki
INOUE, Shigeo
MIMURA, Fujio
USUI, Hiroshi
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1979-03
Publication Date (W3CDTF): 1979-03
Alternative Title: A Study on Film-Cooled Turbine Rotor Blade(Cooling and Aerodynamic Performances of Blade Cascades)
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-565
No. or year of volume/issue: 565
Volume: 565
Pages: 36-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: jpn
Target Audience: 一般
Note (General): To achieve a higher turbine inlet gas temperature(TIT), a new air-cooled turbine rotor blade, adopting film cooling in the vicinity of the leading edge, was disigned. This blade has three cooling chambers; i.e. leading edge, center chamber and trailing edge. The center chamber has many pin-fins for promoting surface heat transfer. To make sure of the cooling and aerodynamic performances of the blade cascade, the two-dimensional cascade tests, with low velocity air stream, were carried out. Two kinds of blades were tested, of which the number of coolant ejection holes differed from each other(i.e. the blade A has 45 holes, and the blade B has 22 holes). According to the test results, average cooling effectivenesses of 0.389 with blade A and 0.322 with blade B were obtained with the coolant flow ratio of β (approximately)=2.5(％). Characteristics of the cooling performance with coolant flow ratio, Reynolds’ number and inlet angle, were clarified. Spanwise distributions of the cooling effectiveness of the blades were also obtained. Numerical calculations of the cooling performances by using simplified models were performed and satisfactory agreement with the test results was obtained. As to the aerodynamic performances of the cascades, it was shown that the profile loss characteristics were strongly affected by the coolant injection from the leading edge holes, and loss coefficients were increased with increasing injectant velocity.
資料番号: NALTR0565000
レポート番号: NAL TR-565
Access Restrictions: 限定公開
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