Method for the local heat treatment of gas turbine blades

Patent metadata

Field	Value
Publication number	US-9394597-B2
Application number	US-201013391651-A
Country	US
Kind code	B2
Filing date	Aug 31, 2010
Priority date	Sep 5, 2009
Publication date	Jul 19, 2016
Grant date	Jul 19, 2016

Abstract

A method for heat-treating gas turbine blades, namely for locally heat-treating at least one gas turbine blade in a blade section thereof; a blade root section, which is not to be heat-treated, of the gas turbine blade being positioned in a holding receptacle to prevent an unacceptable heating of the particular blade root section, which is not to be heat-treated, during the heat treatment of the particular blade section. The blade root section of the gas turbine blade is positioned in an interior space in a way that allows a remaining interior space of the holding receptacle, to be filled with a filler material; the holding receptacle, together with the gas turbine blade, being subsequently positioned in a heat treatment chamber to enable the gas turbine blade in the heat treatment chamber to undergo local heat treatment under vacuum.

First claim

The invention claimed is:

1. A method for locally heat-treating at least one gas turbine blade having a blade section and a blade root section in the blade section, the blade root section not to be heat-treated, the gas turbine blade being positioned in a holding receptacle to prevent an unacceptable heating of the blade root section during heat treatment of the blade section, the method comprising;
positioning the blade root section of the gas turbine blade in an interior space of the holding receptacle in a way that allows a remaining interior space of the holding receptacle, that is not entirely taken up by the blade root section, to be filled with a filler material; and
subsequently positioning the holding receptacle, together with the gas turbine blade, in a heat treatment chamber to enable the turbine blade in the heat treatment chamber to undergo heat treatment;
wherein the remaining interior space of the holding receptacle, that is not entirely taken up by the blade root section, is filled with solid bodies in the form of metal spheres and/or with metal powder.

2. The method as recited in claim 1 wherein the gas turbine blade in the heat treatment chamber is locally heat-treated under vacuum.

3. The method as recited in claim 1 wherein the remaining interior space of the holding receptacle is filled with solid bodies whose material has a specific thermal capacity of between 390 and 520 J*kg−1*K−1.

4. The method as recited in claim 1 wherein the solid bodies have a thermal capacity of between 50 and 400 W*m−1*K−1.

5. The method as recited in claim 1 wherein the solid bodies have a specific weight of between 70000 and 90000 N*m−3.

6. The method as recited in claim 1 wherein solid bodies do not react with the material of the gas turbine blade during the heat treatment.

7. The method as recited in claim 1 wherein the metal spheres and/or metal powder include steel spheres and/or steel powder.

8. The method as recited in claim 1 wherein the holding receptacle, together with the gas turbine blade, is positioned in a vacuum furnace for heat treatment.

9. The method as recited in claim 1 wherein a double-walled region of a housing delimiting the interior space of the holding receptacle is either filled with an insulating material or is traversed by the flow of a cooling medium.

Assignees

• Hornig Christian
• Weder Jens
• Mtu Aero Engines Gmbh

Inventors

• Hornig Christian
• Weder Jens

Classifications

• C21D9/0068

  for particular articles not mentioned below · CPC title

• B23P6/005

  using only replacement pieces of a particular form · CPC title

• C22F1/10 Primary

  of nickel or cobalt or alloys based thereon · CPC title

• C21D2221/00

  Treating localised areas of an article · CPC title