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航空機用ジェットエンジンの研究開発(第2期成果報告)
https://jaxa.repo.nii.ac.jp/records/44998
https://jaxa.repo.nii.ac.jp/records/449984b2347f3-18ae-4290-81c7-d61b2c510a4a
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
naltr00741.pdf (5.8 MB)
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| Item type | テクニカルレポート / Technical Report(1) | |||||||||
|---|---|---|---|---|---|---|---|---|---|---|
| 公開日 | 2015-03-26 | |||||||||
| タイトル | ||||||||||
| タイトル | 航空機用ジェットエンジンの研究開発(第2期成果報告) | |||||||||
| 言語 | ||||||||||
| 言語 | jpn | |||||||||
| 資源タイプ | ||||||||||
| 資源タイプ識別子 | http://purl.org/coar/resource_type/c_18gh | |||||||||
| 資源タイプ | technical report | |||||||||
| その他のタイトル（英） | ||||||||||
| その他のタイトル | Research and Development of the Turbofan Engine(The Second Phase, FJR710) | |||||||||
| 著者 |
原動機部
× 原動機部
× Aeroengine, Division
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| 著者所属 | ||||||||||
| 航空宇宙技術研究所原動機部 | ||||||||||
| 著者所属（英） | ||||||||||
| en | ||||||||||
| Aeroengine Division, National Aerospace Laboratory(NAL) | ||||||||||
| 出版者 | ||||||||||
| 出版者 | 航空宇宙技術研究所 | |||||||||
| 出版者（英） | ||||||||||
| 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-741 巻 741, p. 79, 発行日 1982-10 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | Research and development on a high bypass ratio turbofan engine has been conducted since 1971, under the National Research and Development Programs system(socalled Big project system)by the Agency of Industrial Science and Technology of the Ministry of International Trade and Industry. The ultimate goal was to develop a high performance turbofan engine, in the 10 to 15-ton thrust class, capable of withstanding frequent take-off and landing, economical crusing(low specific fuel consumption), less noise and less air pollution. To attain this goal, the first phase plan was established with intermediate target specifications, that is, the FJR 710 turbofan engine(5 ton thrust class). Research and development activities were devoted to the development of individual components, such as the front fans, compressors, combustors, turbines, fuel control units and fan noise suppressors having advanced performance characteristics as well as the development of prototype engines. But in 1981, the ultimate goal was changed to a program to develop a 5-ton thrust class turbofan engine. And so, the second phase plan was to bring to completion the development of the prototype FJR 710/600 turbofan engine. In the second phase plan, National Aerospace Laboratory(NAL) assumed the role of the engineering center, carrying out all research work on the components, engine test runs, and formulation of basic and detailed instructions for the engine designs. Three aircraft engine manufacturers(IHI, KHI and MHI) performed the design, manufacture and assembly of the engines. The second phase plan was completed in March, 1982, with the successful development of the FJR 710/600. This report provides details on individual component tests and engine test runs conducted at NAL during the second phase. | |||||||||
| ISSN | ||||||||||
| 収録物識別子タイプ | ISSN | |||||||||
| 収録物識別子 | 0389-4010 | |||||||||
| 資料番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | 資料番号: NALTR0741000 | |||||||||
| レポート番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | レポート番号: NAL TR-741 | |||||||||
