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:
Oct. 09, 2018

Filed:

Feb. 22, 2015
Applicant:

United Technologies Corporation, Hartford, CT (US);

Inventors:

Brian K. Holland, Lansing, MI (US);

Michael A. Morden, Holt, MI (US);

Brandon A. Gates, DeWitt, MI (US);

William Bogue, Hebron, CT (US);

Assignee:

United Technologies Corporation, Farmington, CT (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
B29C 73/04 (2006.01); F01D 25/24 (2006.01); F02C 9/00 (2006.01); B23P 6/00 (2006.01); F01D 25/00 (2006.01); B29C 73/26 (2006.01);
U.S. Cl.
CPC ...
F01D 25/24 (2013.01); B23P 6/005 (2013.01); B29C 73/04 (2013.01); F01D 25/005 (2013.01); F02C 9/00 (2013.01); B29C 73/26 (2013.01); Y02T 50/672 (2013.01); Y10T 29/49318 (2015.01);
Abstract

A method of remanufacturing a liner panel for a gas turbine engine includes removing a bushing from a damaged component; and molding the bushing with a material charge. A liner panel for a gas turbine engine includes a forward fan exit case liner panel with a donor bushing from a damaged forward fan exit case liner panel. A liner panel for a gas turbine engine includes a forward fan exit case liner panel molded from a material charge that includes a multiple of layers. At least one of the multiple of layer includes a discontinuity.


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