Method, device and powder for the additive manufacturing of a component with oxide dispersion strengthening and corresponding component

Patent metadata

Field	Value
Publication number	US-11654485-B2
Application number	US-201917044820-A
Country	US
Kind code	B2
Filing date	Apr 17, 2019
Priority date	May 9, 2018
Publication date	May 23, 2023
Grant date	May 23, 2023

Abstract

A method for the additive manufacturing of a component includes providing a powdered base material for a component, in particular a component for the hot gas path of a gas turbine, building up the component layer by layer on a building platform by fusing individual layers of the base material, and introducing an oxide dispersion strengthening into a region of the component to be additively manufactured by an oxidic additive, wherein the region is usually exposed to high thermomechanical loading during operation of the component.

First claim

The invention claimed is:

1. A process for additive manufacture of a component, comprising:
providing a pulverulent base material for the component,
layerwise building up of the component on a building platform by solidification of individual layers of the base material, and
introducing oxidic dispersion strengthening into a region of the additively manufactured component by an oxidic additive, where the region is usually subjected to high thermomechanical stress during operation of the component
wherein the introducing of the oxidic dispersion strengthening is carried out layerwise, by the component being built up at least partially layerwise alternately from the base material and a mixture of the base material and the oxidic additive for formation of the oxidic dispersion strengthening.

2. The process as claimed in claim 1 , wherein the base material comprises one of the following materials: PWA795, Mer172, MAR-509, Stellite-31, Hastelloy X, Haynes 230, Haynes 625, IN939, IN738, IN713, IN792, IN718, Alloy 247 and Rene 80.

3. The process as claimed in claim 1 , wherein the component is a turbine blade and the region describes a surface region of the turbine blade, and/or a trailing edge of the turbine blade.

4. The process as claimed in claim 1 , wherein the region is a surface region and a subregion of the compenent located underneath or in an interior is firstly built up from the base material and the region is subsequently built up from a mixture of the base material and the oxidic additive for formation of the oxidic dispersion strengthening.

5. The process as claimed in claim 1 , further comprising: reducing agglomeration or flotation of the oxidic additive during the layerwise building up of the component by modifying energy inputs and/or cooling rates.

6. The process as claimed in claim 1 , further comprising: layerwise forming of oriented recrystallization along a longitudinal axis of the region, by renewed remelting of a previously solidified component layer and/or by means of a thermal treatment.

7. The process as claimed in claim 1 , wherein the component comprises a component for a hot gas path of a gas turbine.

Assignees

• Siemens Ag
• Siemens Energy Global Gmbh & Co Kg

Inventors

• Farahbod-Sternahl Lena
• Felsmann Christian
• Glass Dennis
• Grodzki Jacek
• Herfurth Robert
• Hoefener Lars
• Hornung Bernd
• Rule David
• Rühmer Tobias Thomas
• Thomas Eric

Classifications

• F05D2220/32

  in gas turbines · CPC title

• B22F10/50

  Treatment of workpieces or articles during build-up, e.g. treatments applied to fused layers during build-up · CPC title

• B22F5/04 Primary

  of turbine blades · CPC title

• Y02P10/25

  Process efficiency · CPC title

• B23K2101/001

  Turbines · CPC title