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:
Feb. 15, 2022

Filed:

Aug. 02, 2019
Applicant:

United Technologies Corporation, Farmington, CT (US);

Inventors:

Daniel A. Bales, Avon, CT (US);

Dmitri Novikov, Avon, CT (US);

Robert C. Dolan, Coventry, CT (US);

Eric W. Malmborg, Amston, CT (US);

Steven T. Gordon, Glastonbury, CT (US);

Assignee:

RAYTHEON TECHNOLOGIES CORPORATION, Farmington, CT (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F01D 5/14 (2006.01); F01D 5/30 (2006.01); B23K 1/00 (2006.01); F04D 29/38 (2006.01); B23K 101/00 (2006.01);
U.S. Cl.
CPC ...
F01D 5/3061 (2013.01); B23K 1/0018 (2013.01); F01D 5/147 (2013.01); F04D 29/388 (2013.01); B23K 2101/001 (2018.08); F05D 2230/232 (2013.01); F05D 2240/301 (2013.01);
Abstract

An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, a first portion welded to a second portion along an interface such that at least the first portion establishes an airfoil section and the second portion establishes a root section mountable to a rotatable hub. The airfoil section includes an airfoil body extending between leading and trailing edges in a chordwise direction, extending between pressure and suction sides separated in a thickness direction, and extending from the root section in a spanwise direction to a tip portion. A recessed region extends inwardly from at least one of the pressure and suction sides. The airfoil body includes at least one rib bounding a respective pocket within a perimeter of the recessed region. A cover skin is welded to the airfoil body along the at least one rib to enclose the recessed region. A method of forming a gas turbine engine component is also disclosed.


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