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:
Aug. 08, 2023

Filed:

Apr. 07, 2022
Applicant:

General Electric Company, Schenectady, NY (US);

Inventors:

Abhijit Roy, Bangalore, IN;

Nicholas Joseph Kray, Mason, OH (US);

Assignee:

General Electric Company, Schenectady, NY (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F01D 5/28 (2006.01); B32B 5/26 (2006.01); B32B 5/02 (2006.01); B29C 70/08 (2006.01); F01D 5/14 (2006.01); B29C 70/34 (2006.01);
U.S. Cl.
CPC ...
F01D 5/282 (2013.01); B29C 70/081 (2013.01); B32B 5/02 (2013.01); B32B 5/26 (2013.01); F01D 5/147 (2013.01); B29C 70/342 (2013.01); B32B 2250/20 (2013.01); B32B 2250/40 (2013.01); B32B 2260/023 (2013.01); B32B 2260/046 (2013.01); B32B 2262/0261 (2013.01); B32B 2262/101 (2013.01); B32B 2262/103 (2013.01); B32B 2262/105 (2013.01); B32B 2262/106 (2013.01); B32B 2262/16 (2021.05); B32B 2603/00 (2013.01); F05D 2220/32 (2013.01); F05D 2230/20 (2013.01); F05D 2300/6034 (2013.01);
Abstract

Composite components, such as gas turbine engine airfoils, and methods of forming composite components are provided. For example, a composite component of a gas turbine engine comprises a plurality of continuous fiber layers, each continuous fiber layer formed from a plurality of continuous fibers disposed in a matrix material, and a chopped fiber layer comprising a plurality of chopped fibers formed as a filmed sheet. The chopped fiber layer is laid up with the plurality of continuous fiber layers to form the composite component. A method for forming a composite component comprises laying up a plurality of continuous fiber layers, each continuous fiber layer comprising continuous fibers disposed in a matrix material; laying up a chopped fiber layer with the plurality of continuous fiber layers, the layup of the plurality of continuous fiber layers and the chopped fiber layer forming a reinforced layup; and curing the reinforced layup.


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