Method and device for producing a component of a turbomachine

Patent metadata

Field	Value
Publication number	US-10144062-B2
Application number	US-201013504888-A
Country	US
Kind code	B2
Filing date	Sep 30, 2010
Priority date	Oct 30, 2009
Publication date	Dec 4, 2018
Grant date	Dec 4, 2018

Abstract

A method for producing a component of a turbomachine is disclosed. The method includes a) layer-by-layer deposition of a powder component material onto a component platform in a region of a buildup and joining zone, where the deposition takes place in accordance with layer information of the component to be produced; b) local layer-by-layer fusion or sintering of the powder component material by energy supplied in the region of the buildup and joining zone, where the buildup and joining zone is heated to a temperature just below a melting point of the powder component material; c) layer-by-layer lowering of the component platform by a predefined layer thickness; and d) repetition of steps a) to c) until the component is finished. A device for producing a component of a turbomachine is also disclosed.

First claim

The invention claimed is:

1. A method for producing a component of a turbomachine, comprising the steps of:
a) feeding a powder component and supplying radiation from a source coaxially to provide layer-by-layer deposition of a powder component material onto a component platform in a region of a buildup and joining zone formed within a furnace, wherein the deposition takes place in accordance with layer information of the component to be produced;
b) local layer-by-layer fusing or sintering the powder component material by energy supplied in the region of the buildup and joining zone, wherein the buildup and joining zone is heated to a temperature just below a melting point of the powder component material;
c) layer-by-layer lowering of the component platform into the furnace by a predefined layer thickness; and
d) repeating steps a) to c) until the component is finished.

2. The method according to claim 1 , wherein the component is a hollow structural part of a turbine or a compressor.

3. The method according to claim 1 , wherein the deposition utilizes laser deposition welding or electron beam powder deposition welding.

4. The method according to claim 3 , wherein a gas laser, a solid-state laser or a diode laser is used for the laser deposition welding.

5. The method according to claim 1 , wherein the powder component material is made of a metal, a metal alloy, a ceramic, a silicate or a mixture thereof.

6. The method according to claim 1 , wherein a first layer of the powder component material is applied in method step a) and strengthened in method step b) such that a directionally solidified or monocrystalline basic body of the component to be produced is formed on the component platform.

7. The method according to claim 6 , wherein layers of the powder component material are deposited on the basic body in method step a) and strengthened in method step b) such that a directionally solidified or monocrystalline component is formed.

8. The method according to claim 1 , wherein prior to the layer-by-layer deposition of the powder component material according to method step a), a directionally solidified or monocrystalline basic body of the component to be produced is applied to the component platform, and a contour of the basic body of the component corresponds to a basic contour of the component.

9. The method according to claim 1 , wherein, synchronously with the deposition or directly after the deposition of a layer of the powder component material, a laser ablation of material protrusions is performed.

10. The method according to claim 9 , wherein the laser ablation is performed as a function of measurement data of contours of the component in a respective component section recorded and processed by an optical measuring system.

11. The method according to claim 9 , wherein a short pulse laser is used for the laser ablation.

12. The method according to claim 1 , wherein a shape and a material structure of the component are determined as a computer-generated model and layer information generated therefrom is used to control at least one of a powder feed, the component platform, a deposition laser, and an electron beam powder deposition device.

13. The method according to claim 1 , wherein heating of the buildup and joining zone is carried out to the temperature just below the melting point of the component material in a high temperature zone of the furnace, and the furnace is a zone furnace.

14. The method according to claim 13 , wherein the component to be produced is moved from the high temperature zone of the zone furnace by the component platform to a zone having a lower temperature.

Assignees

• Bayer Erwin
• Richter Karl Hermann
• Mtu Aero Engines Gmbh

Inventors

• Bayer Erwin
• Richter Karl-Hermann

Classifications

• B23K35/005 Primary

  at least one of the workpieces being of a refractory metal · CPC title

• B22F12/41

  characterised by the type, e.g. laser or electron beam · CPC title

• B22F10/25

  Direct deposition of metal particles, e.g. direct metal deposition [DMD] or laser engineered net shaping [LENS] · CPC title

• C04B2235/6026

  Computer aided shaping, e.g. rapid prototyping · CPC title

• C30B29/52

  Alloys · CPC title