# US 10,119,408 B2 · Method for connecting a turbine blade or vane to a turbine disc or a turbine ring

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- Number: US 10,119,408 B2
- Document ID: US10119408B2
- Status: Granted
- Kind: B2
- Application number: 13/816,269
- Filed: 2011-08-06
- Published: 2013-06-20
- Granted: 2018-11-06
- Earliest claimed: 2010-08-14
- Assignees: MTU Aero Engines AG
- Applicants: Karl-Hermann Richter
- Inventors: Karl-Hermann Richter
- Web page: https://patentgrep.com/patent/US10119408B2

## 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 1

A method for connecting a turbine blade or vane to a turbine disk or a turbine ring, wherein the method comprises:
(a) 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 to form a connecting body on the turbine blade or vane; and
(d) connecting the turbine blade or vane to the turbine disk or the turbine ring by directly fusion welding the connecting body to the turbine disk or the turbine ring.

### Claim 2 (depends on 1)

The method of claim 1, 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 3 (depends on 2)

The method of claim 2, 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 4 (depends on 2)

The method of claim 2, wherein the connecting body is formed by at least one of a laser beam melting process and an electron beam melting process.

### Claim 5 (depends on 4)

The method of claim 4, 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 6 (depends on 4)

The method of claim 4, 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 7 (depends on 4)

The method of claim 4, 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 8 (depends on 6)

The method of claim 6, 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 9 (depends on 4)

The method of claim 4, wherein the connecting body is formed in layers.

### Claim 10 (depends on 9)

The method of claim 9, wherein the layers have a thickness (d) of from 20 μm to 200 μm.

### Claim 11 (depends on 4)

The method of claim 4, wherein the additive is supplied in powder form with a mean grain diameter of from 10 μm to 100 μm.

### Claim 12 (depends on 2)

The method of claim 2, 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 13 (depends on 12)

The method of claim 12, 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 14 (depends on 12)

The method of claim 12, 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 15 (depends on 12)

The method of claim 12, wherein the connecting body is formed in layers.

### Claim 16 (depends on 15)

The method of claim 15, wherein the layers have a thickness (d) of from 0.05 mm to 2 mm.

### Claim 17 (depends on 1)

The method of claim 1, wherein after the connecting body has been formed the connecting body is subjected to hot isostatic pressing.

### Claim 18 (depends on 1)

The method of claim 1, 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 19 (depends on 1)

The method of claim 1, wherein the connecting body is formed in a region of a root of the turbine blade or vane and/or as a root of the turbine blade or vane.