# US 2013/0156586 A1 · Method for connecting a turbine blade or vane to a turbine disc or a turbine ring

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- Number: US 2013/0156586 A1
- Document ID: US20130156586A1
- Status: Published application
- Kind: A1
- Application number: 13/816,269
- Filed: 2011-08-06
- Published: 2013-06-20
- Earliest claimed: 2010-08-14
- Assignees: MTU Aero Engines AG
- Inventors: Karl-Hermann Richter
- Web page: https://patentgrep.com/patent/US20130156586A1

## CPC

- F01D 5/3061: {by welding, brazing}
- B23K 15/0006: {specially adapted for particular articles or work}
- B23K 15/0086: {welding for purposes other than joining, e.g. build-up welding}
- B23K 26/32: taking account of the properties of the material involved
- B23K 26/342: Build-up welding
- B23K 35/0244: {Powders, particles or spheres; Preforms made therefrom}
- B23K 35/24: Selection of soldering or welding materials proper (B23K35/34 takes precedence)
- B23K 2101/001: {Turbines}
- B23K 2103/18: Dissimilar materials
- B23K 2103/26: {Alloys of Nickel and Cobalt and Chromium}
- F05D 2230/232: by welding
- F05D 2230/237: Brazing
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- B23K: SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

The present invention provides a method for connecting a turbine blade or vane to a turbine disk or to a turbine ring. First, a connecting body is formed on the turbine blade or vane by supplying an additive suitable for fusion welding to a surface of the turbine blade or vane, melting the additive on the surface, with incipient melting of the surface, and allowing the additive and the surface to solidify. Then, the connecting body is connected to the turbine disk or to the turbine ring by means of a fusion welding process.

## Claims

### Claim at position 1

-15. (canceled)

### Claim 16

A method for connecting a turbine blade or vane to a turbine disk or a turbine ring, wherein the method comprises:
(a) forming a connecting body on the turbine blade or vane by supplying an additive suitable for fusion welding to a surface of the turbine blade or vane,
(b) melting the additive on the surface of the turbine blade or vane, with incipient melting of the surface,
(c) allowing the additive and the surface to solidify; and
(d) connecting the connecting body to the turbine disk or the turbine ring by a fusion welding process.

### Claim 17 (depends on 16)

The method of claim 16, wherein the melting of (b) is effected by at least one of a laser beam and an electron beam that is guided over the surface.

### Claim 18 (depends on 17)

The method of claim 17, wherein the at least one of a laser beam and an electron beam is operated with a power of from 100 W to 2000 W.

### Claim 19 (depends on 17)

The method of claim 17, wherein the at least one of a laser beam and an electron beam is operated with a power of about 400 W.

### Claim 20 (depends on 17)

The method of claim 17, wherein the connecting body is formed by at least one of a laser beam melting process and an electron beam melting process.

### Claim 21 (depends on 20)

The method of claim 20, wherein the at least one of a laser beam and an electron beam is guided over the surface with a track spacing of from 0.01 mm to 0.2 mm.

### Claim 22 (depends on 20)

The method of claim 20, wherein the at least one of a laser beam and an electron beam is guided over the surface with a track spacing of about 0.03 mm.

### Claim 23 (depends on 20)

The method of claim 20, wherein the at least one of a laser beam and an electron beam is guided over the surface with a scanning speed of from 50 mm/s to 1000 mm/s.

### Claim 24 (depends on 22)

The method of claim 22, wherein the at least one of a laser beam and an electron beam is guided over the surface with a scanning speed of about 300 mm/s.

### Claim 25 (depends on 20)

The method of claim 20, wherein the connecting body is formed in layers.

### Claim 26 (depends on 25)

The method of claim 25, wherein the layers have a thickness (d) of from 20 μm to 200 μm.

### Claim 27 (depends on 20)

The method of claim 20, wherein the additive is supplied in powder form with a mean grain diameter of from 10 μm to 100 μm.

### Claim 28 (depends on 17)

The method of claim 17, wherein the connecting body is formed by at least one of a laser beam deposition welding process and an electron beam deposition welding process.

### Claim 29 (depends on 28)

The method of claim 28, wherein a laser beam or electron beam is guided over the surface with a track spacing of from 0.1 mm to 2 mm.

### Claim 30 (depends on 28)

The method of claim 28, wherein a laser beam or electron beam is guided over the surface with a feed rate of from 50 mm/s to 2000 mm/s.

### Claim 31 (depends on 28)

The method of claim 28, wherein the connecting body is formed in layers.

### Claim 32 (depends on 31)

The method of claim 31, wherein the layers have a thickness (d) of from 0.05 mm to 2 mm.

### Claim 33 (depends on 16)

The method of claim 16, wherein after the connecting body has been formed the connecting body is subjected to hot isostatic pressing.

### Claim 34 (depends on 16)

The method of claim 16, wherein after the connecting body has been formed, the connecting body is machined at least one of with the removal of material and electrochemically.

### Claim 35 (depends on 16)

A turbine stage for a turbine of a turbomachine having a turbine disk or a turbine ring which is connected at least indirectly to at least one turbine blade or vane by a connecting body formed on the turbine blade or vane by the method of claim 16.