Method and apparatus for determining residual stresses of a component

Patent metadata

Field	Value
Publication number	US-9696142-B2
Application number	US-201514614061-A
Country	US
Kind code	B2
Filing date	Feb 4, 2015
Priority date	Feb 5, 2014
Publication date	Jul 4, 2017
Grant date	Jul 4, 2017

Abstract

A method for determining residual stresses of a component ( 14 ), in particular a component of an aircraft engine, while it is being manufactured by an additive manufacturing process. The method includes the following steps: creating at least one local melt pool ( 26 ) in a surface ( 24 ) of the component ( 14 ) to be manufactured after a predetermined portion of the component is completed; optically detecting surface distortions and/or elongations occurring at least in a region around the created melt pool ( 26 ); and determining the residual stresses of the component ( 14 ) which are present at least in the region around the created melt pool ( 26 ) based on the optically detected surface distortions and/or elongations. Further an apparatus for determining residual stresses of a component ( 14 ) while it is being manufactured by an additive manufacturing process is provided.

First claim

The invention claimed is:

1. A method for determining residual stresses of a component while being manufactured by an additive manufacturing process, the method comprising the steps of:
creating at least one local melt pool via laser energy in a surface of the component being manufactured after a predetermined portion of the component is completed;
optically detecting surface distortions or elongations occurring at least in a region around the created melt pool, wherein the optical detection of the surface distortions or elongations is carried out using an optical distortion-based method, the optical distortion-based method being a speckle interferometry method; and
determining residual stresses of the component present at least in the region around the created melt pool based on the optically detected surface distortions or elongations.

2. The method as recited in claim 1 wherein the additive manufacturing process is an additive layer manufacturing process, and the creation of at least one local melt pool in the surface of the component is effected after a predetermined number of additively manufactured component layers are completed.

3. The method as recited in claim 1 wherein the component is manufactured by selective laser melting or selective laser sintering.

4. The method as recited in claim 3 wherein the local melt pool is created using a laser light source used for the selective laser melting process or the selective laser sintering process.

5. The method as recited in claim 1 wherein the locally created melt pool has a predefined geometry.

6. The method as recited in claim 1 wherein the locally created melt pool has an average diameter from 0.5 to 3.0 mm and a depth from 0.1 to 1.0 mm.

7. The method as recited in claim 1 wherein one common laser light source is used for irradiating at least the region around the created melt pool in order to perform a speckle interferometry method, for creating the local melt pool, and for selective laser melting or selective laser sintering.

8. The method as recited in claim 1 wherein, in order to determine residual stresses of the component during manufacture, at least two melt pools of the at least one melt pool are created in component surfaces of different portions or layers of the component, and respectively occurring surface distortions or elongations are optically detected in the regions around the respective melt pools, occurring residual stresses being determined in different planes of the component.

9. The method as recited in claim 1 wherein the component is an aircraft engine component.

10. The method as recited in claim 1 wherein the component is a reference component or a calibration body.

11. The method as recited in claim 10 further comprising manufacturing a further component using the reference component or calibration body for quality control of the further component or to determine and predefine manufacturing parameters for the further component.

12. The method as recited in claim 1 wherein the laser energy is imparted by a melting laser directed at an angle to the surface.

Assignees

• MTU Aero Engines AG

Inventors

• Bamberg Joachim
• Hessert Roland

Classifications

• B33Y50/00

  Data acquisition or data processing for additive manufacturing · CPC title

• B29L2031/3076

  Aircrafts (blades, propellers B29L2031/08) · CPC title

• B23K26/032

  using optical means · CPC title

• G01L5/0047

  measuring forces due to residual stresses · CPC title

• B33Y10/00

  Processes of additive manufacturing · CPC title