F - Mech Eng,Light,Heat,Weapons – 01 – D
Patent
F - Mech Eng,Light,Heat,Weapons
01
D
F01D 5/14 (2006.01) F04D 29/38 (2006.01) B29C 43/20 (2006.01) B29C 51/00 (2006.01)
Patent
CA 2719817
A gas turbine engine blade for aircraft which has a 3-dimensional blade surface shape twisted around a center line at an angle of 45 degrees or more and 70 degrees or less, wherein the aforementioned blade is provided with multiple composite material prepregs which contain reinforced fiber and which are integrally molded after being laminated in the thickness direction, and the aforementioned reinforced fiber runs continuously without interruption within each layer of the aforementioned composite material prepregs.
Une pale d'un moteur de turbine à gaz pour un avion a une forme de pale en trois dimensions qui est tordue selon un angle compris entre 45° et 70° autour de la ligne centrale. La pale d'un moteur de turbine à gaz pour un avion comprend des fibres renforcées, et est pourvue d'une pluralité de pré-imprégnés composites qui ont été empilés dans la direction de l'épaisseur et moulés ensemble, les fibres renforcées étant contiguës au sein des couches des pré-imprégnés composites.
Morita Hideo
Moriya Katsuyoshi
Murakami Tsutomu
Ogi Takahiro
Okumura Ikuo
Ihi Aerospace Co. Ltd.
Ihi Corporation
Marks & Clerk
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