Fluid reaction surfaces (i.e. – impellers) – Specific blade structure – Hollow
Reexamination Certificate
2006-02-07
2006-02-07
Nguyen, Ninh H. (Department: 3745)
Fluid reaction surfaces (i.e., impellers)
Specific blade structure
Hollow
Reexamination Certificate
active
06994524
ABSTRACT:
Hollow fan blades for turbo fan gas turbine engines are formed of two separate detail halves. Each detail half has a plurality of cavities and ribs machined out to reduce weight. These detail halves are subsequently bonded and given an airfoil shape in the forming operation. In the present invention, the ribs are oriented biased to provide stiffness as needed in different sections of the fan blade with smooth transitions between regions. The result is a blade with good protection from a wide spectrum of external threats.
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U.S. Patent Application: “Hollow Fan Blade for Gas Turbine Engine”, U.S Appl. No. 10/765,593; filed Jan. 26, 2004.
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Owen William D.
Weisse Michael A.
Whitesell Daniel J.
Carlson & Gaskey & Olds
Nguyen Ninh H.
United Technologies Corporation
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