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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 11566524 B1

PDFFull Text
Date of Patent:
Jan. 31, 2023

Filed:

Jan. 31, 2018

Method and device for repairing a damaged blade tip of a turbine blade which is armor-plated and provided with a blade coating

Applicant:

Mtu Aero Engines Ag, Munich, DE;

Inventors:

Frank Seidel, Grossburgwedel, DE;

Nils Weidlich, Neustadt, DE;

Assignee:

MTU AERO ENGINES AG, Munich, DE;

Attorney:

Abel Schillinger, LLP

Primary Examiner:

Sarang Afzali

Int. Cl.
CPC ...
F01D 5/00 (2006.01); B23P 6/00 (2006.01); B23K 15/00 (2006.01); F01D 11/12 (2006.01); B23K 31/02 (2006.01); B23K 26/34 (2014.01); B23K 26/00 (2014.01); B23K 9/04 (2006.01); B23K 31/10 (2006.01); B23K 10/02 (2006.01); F01D 5/28 (2006.01); B23K 101/00 (2006.01);
U.S. Cl.
CPC ...
F01D 5/005 (2013.01); B23K 9/04 (2013.01); B23K 10/027 (2013.01); B23K 15/0086 (2013.01); B23K 15/0093 (2013.01); B23K 26/0006 (2013.01); B23K 26/34 (2013.01); B23K 31/02 (2013.01); B23K 31/10 (2013.01); B23P 6/007 (2013.01); F01D 11/122 (2013.01); B23K 2101/001 (2018.08); F01D 5/288 (2013.01); F05D 2220/32 (2013.01); F05D 2230/237 (2013.01); F05D 2230/238 (2013.01); F05D 2230/31 (2013.01); F05D 2230/80 (2013.01); F05D 2230/90 (2013.01); F05D 2240/307 (2013.01); F05D 2300/2282 (2013.01); F05D 2300/506 (2013.01);
Abstract

The invention relates to a method for repairing a damaged blade tip of a turbine blade which is armor-plated and provided with a blade coating, of a thermal gas turbine. The method according to the invention comprises the steps of removing a blade tip armor plating of the turbine blade at least in the region of the damaged blade tip and producing a repair surface (), removing only a part of the blade coating of the turbine blade in the region of the repair surface while preserving a part of the blade coating separated from the repair surface (), restoring the blade tip reinforcement (), and restoring the blade coating in the region of the repaired blade tip (). The invention furthermore relates to a device for carrying out such a method.

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