Invention Grant
US08715556B2 Gas turbine engine blade for aircraft and manufacturing method thereof
有权
用于飞机的燃气涡轮发动机叶片及其制造方法
- Patent Title: Gas turbine engine blade for aircraft and manufacturing method thereof
- Patent Title (中): 用于飞机的燃气涡轮发动机叶片及其制造方法
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Application No.: US12934339Application Date: 2009-03-27
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Publication No.: US08715556B2Publication Date: 2014-05-06
- Inventor: Tsutomu Murakami , Hideo Morita , Takahiro Ogi , Ikuo Okumura , Katsuyoshi Moriya
- Applicant: Tsutomu Murakami , Hideo Morita , Takahiro Ogi , Ikuo Okumura , Katsuyoshi Moriya
- Applicant Address: JP JP
- Assignee: IHI Corporation,IHI Aerospace Co., Ltd.
- Current Assignee: IHI Corporation,IHI Aerospace Co., Ltd.
- Current Assignee Address: JP JP
- Agency: Ostrolenk Faber LLP
- Priority: JP2008-088628 20080328
- International Application: PCT/JP2009/056357 WO 20090327
- International Announcement: WO2009/119830 WO 20091001
- Main IPC: B23P15/02
- IPC: B23P15/02
Abstract:
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.
Public/Granted literature
- US20110020130A1 GAS TURBINE ENGINE BLADE FOR AIRCRAFT AND MANUFACTURING METHOD THEREOF Public/Granted day:2011-01-27
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