書誌事項
- タイトル別名
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- On the Supersonic Parts of Supersonic Axial Flow Compressor-Blade Sections
- チョウオンソクジクリュウ アッシュクキヨクケイ ノ チョウオンソクブ ニ ツイテ
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抄録
The supersonic cascade, in which a normal shock occurs and a flow is decelerated from supersonic to subsonic, is used in supersonic axial flow compressors. For cascades of this type, supersonic starting at the given inlet Mach number, high compression efficiency, larger deflection angles and thick blades enough not to be destroyed are required. Therefore it is considered to be hopeful that a blade section is divided into a supersonic part and a subsonic part, and the former gives most deflection angle to a flow and the latter gives little, consisting of straight surfaces. This report describes the method which dicides such a supersonic part of a blade section and the results of the analytical calculation about the obtainable deflection angles and compression efficiencies in the supersonic regions for the inlet Mach number from 1 to 2.
収録刊行物
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- 日本機械学會論文集
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日本機械学會論文集 28 (195), 1498-1503, 1962
一般社団法人 日本機械学会
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詳細情報 詳細情報について
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- CRID
- 1390001205159644288
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- NII論文ID
- 110002351717
- 110002461305
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- NII書誌ID
- AN00187419
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- ISSN
- 21859485
- 24242675
- 00290270
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- NDL書誌ID
- 9151060
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- 本文言語コード
- ja
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- データソース種別
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- JaLC
- NDL
- Crossref
- CiNii Articles
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- 抄録ライセンスフラグ
- 使用不可