# US 2013/0156966 A1 · Method for reprocessing a turbine blade having at least one platform

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- Number: US 2013/0156966 A1
- Document ID: US20130156966A1
- Status: Published application
- Kind: A1
- Application number: 13/634,642
- Filed: 2011-03-15
- Published: 2013-06-20
- Earliest claimed: 2010-03-19
- Inventors: Martin Grohnert; Andreas Oppert; Gerhard Reich; Rolf Wilkenhöner
- Web page: https://patentgrep.com/patent/US20130156966A1

## CPC

- F01D 5/005: {Repairing methods or devices}
- B23P 6/007: {using only additive methods, e.g. build-up welding}
- F05D 2230/30: with deposition of material
- F05D 2230/31: Layer deposition
- F05D 2240/80: Platforms for stationary or moving blades
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- B23P: METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS (arrangements for copying or controlling B23Q)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

A method for reprocessing a turbine blade having at least one platform which due to the action of corrosion is undersized on at least one lateral platform face is provided. According to the method, the target dimension of the platform is restored by applying material to the at least one lateral platform face such that, after the material application, the platform is oversized and then the platform is given the target dimension by machining the at least one lateral platform face. The material application is carried out with the material of an adhesion promoter layer.

## Claims

### Claim at position 1

1-12. (canceled)

### Claim 13

A process for refurbishing a turbine blade or vane having at least one platform which, on account of corrosive attack, is undersized on a platform side face, comprising:
restoring the desired dimension of the platform, the restoring comprising:
applying material to the platform side face in such a manner that, after the material application, the platform is oversized, and
machining the platform side face in order the to give the desired dimension to the platform,
wherein the material application is effected with the material of an adhesion promoter layer,
wherein the adhesion promoter material is applied within the scope of renewing a thermal barrier coating system of the turbine blade or vane which comprises an adhesion promoter layer and a thermal barrier coating, and
wherein the material of the adhesion promoter layer is an MCrAlX material.

### Claim 14 (depends on 13)

The process as claimed in claim 13, wherein the material application is effected by means of the repeated application of the adhesion promoter material.

### Claim 15 (depends on 13)

The process as claimed in claim 13, wherein the material application of at least 10 um is used each time the application of adhesion promoter material is repeated.

### Claim 16 (depends on 13)

The process as claimed in claim 13, further comprising using a bonding heat treatment after the application of adhesion promoter material.

### Claim 17 (depends on 13)

The process as claimed in claim 13, wherein the material application and the machining are effected on two opposite platform side faces.

### Claim 18 (depends on 17)

The process as claimed in claim 17, wherein the turbine blade or vane includes a central axis and the machining of the platform side face to give the platform the desired dimension is effected with respect to the central axis.

### Claim 19 (depends on 18)

The process as claimed in claim 18, wherein the current dimension of the platform is gathered by scanning at least five measurement points on the opposite platform side faces and the required material removal for the machining is determined from the current dimension.

### Claim 20 (depends on 17)

The process as claimed in claim 17, wherein the turbine blade or vane includes a main blade or vane part with a pressure side and a suction side and the opposite platform side faces are the platform side faces located on the pressure side and suction side in relation to the main blade or vane part.

### Claim 21 (depends on 13)

The process as claimed in claim 13, the machining is realized by face grinding.

### Claim 22 (depends on 21)

The process as claimed in claim 21, wherein a plurality of layers are removed from the turbine blade or vane before the thermal barrier coating system is renewed.

### Claim 23 (depends on 22)

The process as claimed in claim 22, wherein activation blasting is effected after the plurality of layers have been removed and before the thermal barrier coating system is renewed.

### Claim 24 (depends on 13)

The process as claimed in claim 13, wherein the adhesion promoter material is applied by means of a thermal spraying process.