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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.

Patent No.:

US 10384316 B1

PDFFull Text
Date of Patent:
Aug. 20, 2019

Filed:

Dec. 10, 2015

Method of repairing and manufacturing of turbine engine components and turbine engine component repaired or manufactured using the same

Applicant:

Liburdi Engineering Limited, Dundas, CA;

Inventors:

Alexander B Goncharov, Toronto, CA;

Joseph Liburdi, Dundas, CA;

Paul Lowden, Cambridge, CA;

Assignee:

Liburdi Engineering Limited, Dundas, CA;

Attorney:

Ridout and Maybee LLP

Primary Examiner:

Jenny R Wu

Int. Cl.
CPC ...
B23P 6/00 (2006.01); C22C 19/05 (2006.01); C22F 1/10 (2006.01); F01D 5/14 (2006.01); B23P 15/02 (2006.01); B23K 9/04 (2006.01); B23K 9/167 (2006.01); B23K 9/235 (2006.01); B23K 10/02 (2006.01); B23K 15/00 (2006.01); B23K 26/34 (2014.01); F01D 5/00 (2006.01); B23K 101/00 (2006.01); F01D 5/28 (2006.01);
U.S. Cl.
CPC ...
B23P 6/002 (2013.01); B23K 9/044 (2013.01); B23K 9/167 (2013.01); B23K 9/235 (2013.01); B23K 10/027 (2013.01); B23K 15/0033 (2013.01); B23K 15/0086 (2013.01); B23K 15/0093 (2013.01); B23K 26/34 (2013.01); B23P 6/007 (2013.01); B23P 15/02 (2013.01); C22C 19/055 (2013.01); C22C 19/056 (2013.01); C22F 1/10 (2013.01); F01D 5/005 (2013.01); F01D 5/147 (2013.01); B23K 2101/001 (2018.08); F01D 5/28 (2013.01); F05D 2230/233 (2013.01); F05D 2230/234 (2013.01); F05D 2230/80 (2013.01); F05D 2300/175 (2013.01);
Abstract

Method of repairing and manufacturing of turbine engine components includes application of a transition layer by fusion welding with dissimilar nickel based filler material, preferably comprising from about 0.05 wt. % to about 1.2 wt. % B and other alloying elements, followed by a diffusion and primary aging heat treatment and application of the top oxidation resistance layer using dissimilar nickel based filler materials comprised 3-6 wt. % Al, 0.5-6 wt. % Si, 12-25 wt. % Cr and other alloying elements that enhance strength and oxidation resistance followed by a secondary aging heat treatment and machining of the repaired area to restore geometry of turbine engine components. The inventions also relates to a turbine engine components repaired and manufactured by the method.

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