ファン中空翼の強度に関する実験的研究

Material type: 文書・図像類

Author: 祖父江, 靖ほか

Publisher: 航空宇宙技術研究所

Publication date: 1980-07

Material Format: Digital

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Note (General)：: Succeeding the results of references 1 to 3, an experimental study of the strength of diffusion bonded hollow blades for turbo-fan engine was carried ...

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Material Type: 文書・図像類
Title: ファン中空翼の強度に関する実験的研究
Author/Editor: 祖父江, 靖
池田, 為治
藤沢, 良昭
宮地, 敏雄
SOFUE, Yasushi
IKEDA, Tameharu
FUJISAWA, Yoshiaki
MIYACHI, Toshio
Author Heading: 祖父江, 靖
池田, 為治
藤沢, 良昭
宮地, 敏雄
SOFUE, Yasushi
IKEDA, Tameharu
FUJISAWA, Yoshiaki
MIYACHI, Toshio
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1980-07
Publication Date (W3CDTF): 1980-07
Alternative Title: Experimental Study of the Strength of Hollow Fan Blades
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-618
No. or year of volume/issue: 618
Volume: 618
Pages: 24-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: jpn
Target Audience: 一般
Note (General): Succeeding the results of references 1 to 3, an experimental study of the strength of diffusion bonded hollow blades for turbo-fan engine was carried out. In order to examine the strength and stiffness of hollow blades, model blades were made and tested. The model blades had a uniform cross section of 80mm chord length, 4mm maximum thickness, 1mm skin thickness and three spanwise webs(2mm in width) in the middle part(170mm) of the span. The model blades had a 300mm total span and solid parts (65mm) at both ends. The degree of hollowness of the cross section was about 27％. Tests on the bending stiffness, on the torsional stiffness, on the bending failure, on the torsional failure, on the bending fatigue and on the torsional fatigue of the model blades were carried out and the following results were obtained. (1)No separation could be detected in the bonded areas after the bending and torsional failure tests. (2)The positions of the cracks which were generated by the bending fatigue tests were dispersed from the solid pat to the hollow part of the model blades. However, the relation between the maximum cyclic bending stress and life of the model blades was nealy the same as the α-N relation of the model material(Ti-6A1-4V). (3)The failure modes which were generated by the torsional fatigue tests were more complicated than those of bending fatigue tests. The results of the torsional fatigue tests indicate that the cracks were generated by maximum principal stresses of about a half of those maximun stresses in the bending fatigue tests.
資料番号: NALTR0618000
レポート番号: NAL TR-618
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