| Item type |
テクニカルレポート / Technical Report(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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タイトル |
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) |
| 言語 |
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言語 |
jpn |
| 資源タイプ |
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資源タイプ識別子 |
http://purl.org/coar/resource_type/c_18gh |
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資源タイプ |
technical report |
| その他のタイトル（英） |
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その他のタイトル |
A Study on Film-Cooled Turbine Rotor Blade(Cooling and Aerodynamic Performances of Blade Cascades) |
| 著者 |
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
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| 著者所属 |
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航空宇宙技術研究所原動機部 |
| 著者所属 |
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航空宇宙技術研究所原動機部 |
| 著者所属 |
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航空宇宙技術研究所原動機部 |
| 著者所属 |
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航空宇宙技術研究所原動機部 |
| 著者所属 |
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航空宇宙技術研究所原動機部 |
| 著者所属 |
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航空宇宙技術研究所原動機部 |
| 著者所属 |
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航空宇宙技術研究所原動機部 |
| 著者所属（英） |
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en |
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Aeroengine Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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Aeroengine Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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Aeroengine Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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Aeroengine Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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|
en |
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Aeroengine Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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Aeroengine Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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Aeroengine Division, National Aerospace Laboratory(NAL) |
| 出版者 |
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出版者 |
航空宇宙技術研究所 |
| 出版者（英） |
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出版者 |
National Aerospace Laboratory(NAL) |
| 書誌情報 |
航空宇宙技術研究所報告
en : Technical Report of National Aerospace Laboratory TR-565
巻 565,
p. 36,
発行日 1979-03
|
| 抄録（英） |
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内容記述タイプ |
Other |
|
内容記述 |
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. |
| ISSN |
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収録物識別子タイプ |
ISSN |
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収録物識別子 |
0389-4010 |
| 資料番号 |
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内容記述タイプ |
Other |
|
内容記述 |
資料番号: NALTR0565000 |
| レポート番号 |
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内容記述タイプ |
Other |
|
内容記述 |
レポート番号: NAL TR-565 |
naltr00565.pdf (4.5 MB)
