Method for creating a blade for a flow engine and blade for a flow force engine

Patent metadata

Field	Value
Publication number	US-9670782-B2
Application number	US-201214234569-A
Country	US
Kind code	B2
Filing date	Jul 20, 2012
Priority date	Aug 1, 2011
Publication date	Jun 6, 2017
Grant date	Jun 6, 2017

Abstract

A method for creating a blade ( 11 ) for a turbo-engine and such a blade are disclosed. Components ( 19 ) of the blade are produced by an additive production method such as selective laser melting or fusion, while a main body ( 18 ) is produced by casting, for example. The blade components ( 19 ) may consist of a different material than the basic body ( 18 ). The components or body may carry functions such as serving as drainage slots ( 24 ). Expense related to the use of additive production methods occurs only for the components ( 19 ) in which a complicated geometry, for example, must be implemented. The remaining components in the form of the main body ( 18 ), comprising the blade ( 27 ), the blade foot ( 28 ) and the blade head ( 29 ), can be cost-effectively implemented as a cast part or a sheet metal part.

First claim

The invention claimed is:

1. A method for repairing a damaged blade of a turbo-engine, the damaged blade having a damaged portion, and the method comprising the steps of:
producing a basic body from the damaged blade by removing the damaged portion to make a clearance, the making of the clearance producing a surface on the basic body; and
integrating the basic body permanently with a plurality of completing blade components to form a finished blade by producing each completing blade component directly on the surface on the basic body through additive manufacturing;
wherein the plurality of completing blade components are provided to butt one another directly and together define a completing structure for the finished blade.

2. The method as claimed in claim 1 , wherein the at least one of the completing blade components has a joining surface adapted to the basic body and the joining surface is joined to the basic body in a materially integral manner.

3. The method as claimed in claim 1 , wherein at least one of the completing blade components is manufactured from a material other than a material of the basic body.

4. The method as claimed in claim 1 , wherein at least one of the completing blade components is comprised of a replacement material that deviates from an original material of the damaged portion and the replacement material is selected to have better properties than the original material of the damaged portion.

5. The method as claimed in claim 4 , wherein the replacement material is more resistant to wear than the original material of the damaged blade.

Assignees

• Göhler Jens
• Kernstock Frank
• Rehme Olaf
• Schäfer Martin
• Siemens Ag

Inventors

• Göhler Jens
• Kernstock Frank
• Rehme Olaf
• Schäfer Martin

Classifications

• F01D5/14 Primary

  Form or construction (selecting particular materials, measures against erosion or corrosion F01D5/28) · CPC title

• B22F5/04 Primary

  of turbine blades · CPC title

• B22F10/28

  Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM] · CPC title

• B23K26/34 Primary

  Laser welding for purposes other than joining · CPC title

• F05D2230/21

  by casting · CPC title