The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Dec. 05, 2023

Filed:

Nov. 24, 2021
Applicant:

General Electric Company, Schenectady, NY (US);

Inventors:

Li Zheng, Niskayuna, NY (US);

Scott Roger Finn, Evendale, OH (US);

Nicholas J. Kray, West Chester, OH (US);

Trevor H. Wood, Clifton Park, NY (US);

Kishore Ramakrishnan, Rexford, NY (US);

Assignee:

GENERAL ELECTRIC COMPANY, Schenectady, NY (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F01D 5/30 (2006.01); F01D 5/28 (2006.01);
U.S. Cl.
CPC ...
F01D 5/3007 (2013.01); F01D 5/282 (2013.01); F05D 2220/32 (2013.01); F05D 2230/60 (2013.01); F05D 2240/30 (2013.01);
Abstract

Methods, apparatus, systems, and articles of manufacture are disclosed to implement a low radius ratio fan blade for a gas turbine engine. A fan blade for a gas turbine engine includes an airfoil including a leading edge and a trailing edge extending between a root and a tip of the airfoil, a distance between the leading edge and the trailing edge defining a flow path length, a leading edge hub point defined by a radially innermost point of the leading edge, and an axial dovetail including a pair of opposed pressure faces, an axial length of the axial dovetail less than the flow path length, a top edge of the axial dovetail separating the pressure faces from the airfoil, the top edge of the axial dovetail radially outward of the leading edge hub point.


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