著者

中山 卓弥 真壁 朝敏 藤川 正毅 新川 和夫

出版者

一般社団法人 日本高圧力技術協会

雑誌

圧力技術 (ISSN:03870154)

巻号頁・発行日

vol.54, no.2, pp.50-59, 2016

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The fatigue limit and crack growth behavior of slit specimens of epoxy base carbon composites were investigated. The fatigue limit was defined by maximum stress amplitude that the specimen endured 106 times stress repeating. Also, that was calculated by net stress at ligament. Carbon fiber directions were parallel and perpendicular to the load axis. The highest value of fatigue limit was obtained when all fiber directions were parallel to the load axis. However, crack grew along the fiber direction or load axis in the case of long slit. In the cases of two carbon directions that is, parallel and perpendicular to the load axis, the fatigue limits were evaluated from the result of the specimen that all carbon directions were parallel to the load axis. When measured value of fatigue limit was higher than the evaluated value, it was expected that the strain constraint occurred due to resistance of fiber in perpendicular to the load axis. When the measured value was lower, the peeling of fiber from epoxy was expected to be occurred. According to those results, it was expected that fatigue limit of smooth specimen of carbon composites with long fiber can be evaluated from the results of slit specimens

著者

中山 卓弥 真壁 朝敏 藤川 正毅 新川 和夫

出版者

一般社団法人 日本高圧力技術協会

雑誌

圧力技術 (ISSN:03870154)

巻号頁・発行日

vol.54, no.2, pp.50-59, 2016-03-25 (Released:2016-04-29)

参考文献数

7

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The fatigue limit and crack growth behavior of slit specimens of epoxy base carbon composites were investigated. The fatigue limit was defined by maximum stress amplitude that the specimen endured 106 times stress repeating. Also, that was calculated by net stress at ligament. Carbon fiber directions were parallel and perpendicular to the load axis. The highest value of fatigue limit was obtained when all fiber directions were parallel to the load axis. However, crack grew along the fiber direction or load axis in the case of long slit. In the cases of two carbon directions that is, parallel and perpendicular to the load axis, the fatigue limits were evaluated from the result of the specimen that all carbon directions were parallel to the load axis. When measured value of fatigue limit was higher than the evaluated value, it was expected that the strain constraint occurred due to resistance of fiber in perpendicular to the load axis. When the measured value was lower, the peeling of fiber from epoxy was expected to be occurred. According to those results, it was expected that fatigue limit of smooth specimen of carbon composites with long fiber can be evaluated from the results of slit specimens

著者

戸川 隼人

出版者

一般社団法人 日本高圧力技術協会

雑誌

圧力技術 (ISSN:03870154)

巻号頁・発行日

vol.11, no.5, pp.289-296, 1973-09-25 (Released:2010-08-05)

参考文献数

11

著者

稲垣 道夫

出版者

一般社団法人 日本高圧力技術協会

雑誌

高圧力 (ISSN:21851662)

巻号頁・発行日

vol.8, no.5, pp.2102-2113, 1970-09-25 (Released:2010-08-05)

著者

Gary Penney

出版者

一般社団法人 日本高圧力技術協会

雑誌

圧力技術 (ISSN:03870154)

巻号頁・発行日

vol.49, no.6, pp.281-286, 2011-11-25 (Released:2013-01-18)

著者

辻 裕一 高木 知弘 澤 俊行

出版者

一般社団法人 日本高圧力技術協会

雑誌

圧力技術 (ISSN:03870154)

巻号頁・発行日

vol.42, no.6, pp.337-346, 2004 (Released:2005-01-25)

参考文献数

12

被引用文献数

1

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A guideline for bolted flange joint assembly has been published as an HPIS technical report, in which bolts are tightened in the clockwise-pattern sequence and the tightening torque is 100% of the target torque in all steps except for an install step. This paper describes analytical and experimental backgrounds of the guideline. Numerical simulations of bolt-up procedure by using three-dimensional finite element analysis are systematically executed for JPI flange joints of various nominal sizes and classes. The number of bolt-up passes required to achieve uniform bolt preloads is determined in order to avoid excessive iterations of tightening operation. Tightening tests using various sizes of the flange joint demonstrate that HPIS procedure achieves comparable uniformity in bolt preload and in flange alignment with ASME PCC-1 procedure. The guideline developed is able to achieve accurate preloads consisting with assembly efficiency for practical use.