Method for manufacturing a component using an additive manufacturing process

Patent metadata

Field	Value
Publication number	US-2016151860-A1
Application number	US-201514868734-A
Country	US
Kind code	A1
Filing date	Sep 29, 2015
Priority date	Nov 28, 2014
Publication date	Jun 2, 2016
Grant date	—

Abstract

The invention relates to a method for manufacturing a component, especially for gas turbines and other thermo machinery. The method includes providing a data set defining the component for being used in an additive manufacturing process; manufacturing said component by means of said additive manufacturing process according to said data set; and subjecting said manufactured component to a heat treatment (HT) in order to change the microstructure of the manufactured component. The properties of the component are improved in that at least two different component volumes (CA 1 -CA 3 ) are defined within said component prior to the manufacturing step; at least two different process parameters (A, B) are chosen for the additive manufacturing process, which process parameters (A, B) result in different driving forces for a recrystallization and therefore a different recrystallization behavior in the material of the component; and the additive manufacturing process is executed with one of the at least two process parameters (A, B) being used during manufacturing a first of the at least two component volumes (CA 1 -CA 3 ), resulting in a first recrystallization behavior in the first component volume, and with the other of the at least two process parameters (A, B) being used during manufacturing a second of said at least two component volumes (CA 1 -CA 7 ), resulting in a second recrystallization behavior different from said first recrystallization behavior, in the second component volume; and the manufactured component is subjected to a heat treatment (HT), with a holding temperature (T_HT), wherein the holding temperature (T_HT) lies above a recrystallization temperature of at least one of said at least two component volumes.

First claim

1 . A method for manufacturing a component, especially for gas turbines and other thermo machinery, comprising:
providing a data set for use in an additive manufacturing process; manufacturing said component by means of said additive manufacturing process according to said data set; subjecting said manufactured component to a heat treatment (HT) in order to change the microstructure of said manufactured component; at least two different component volumes (CA 1 -CA 7 ) are defined within said component prior to the manufacturing step; at least two different process parameters (A, B) are chosen for said additive manufacturing process, which process parameters (A, B) result in different recrystallization behavior in the material of said component; said additive manufacturing process is executed with one of said at least two process parameters (A, B) being used during manufacturing a first of said at least two component volumes (CA 1 -CA 7 ), resulting in a first recrystallization behavior in said first component volume, and with the other of said at least two process parameters (A, B) being used during manufacturing a second of said at least two component volumes (CA 1 -CA 7 ), resulting in a second recrystallization behavior different from said first recrystallization behavior, in said second component volume; and said manufactured component is subjected to a heat treatment (HT), with a holding temperature (T_HT), wherein the holding temperature (T_HT) lies above a recrystallization temperature of at least one of said at least two component volumes.

2 . The method as claimed in claim 1 , wherein the recrystallization behavior comprises a recrystallization temperature, the first recrystallization behavior comprises a first recrystallization temperature (T_RX_A or T_RX_B) and the second recrystallization behavior comprises a second recrystallization temperature (T_RX_B or T_RX_A), and that said manufactured component is subjected to a heat treatment (HT), with a holding temperature (T_HT) that lies between said first and second recrystallization temperatures (T_RX_A, T_RX_B).

3 . The method as claimed in claim 1 , wherein the recrystallization behavior comprises a change in grain size, the first recrystallization behavior comprises a first grain size and the second recrystallization behavior comprises a second grain size different from the first grain size, and wherein the holding temperature (T_HT) lies above a recrystallization temperature of at least two of said at least two component volumes.

4 . The method as claimed in claims 1 , wherein at least three different component volumes, namely a first component volume, a second component volume and a third component volume, are defined and three process parameters (A, B, C) are chosen such that after the heat treatment at the holding temperature (T_HT) the first component volume has a first grain size, the second component volume has a second grain size and the third component volume has a third grain size, wherein the first grain size, the second grain size and the third grain size are different from one another.

5 . The method as claimed in claim 1 , wherein said additive manufacturing process is a Selective Laser Melting (SLM) process.

6 . The method as claimed in claim 5 , wherein the material of said component is one of a high temperature Ni-, Co- and Fe-based alloy.

7 . The method as claimed in claim 5 , wherein said at least two process parameters (A, B) differ in at least one of the following characteristics:
weld pool size energy input, especially scan speed and/or laser power and/or laser mode hatch distance layer thickness laser beam diameter/intensity distribution/focal plane position additional volume exposure/remelting/preheating/reheating scanning strategy, especially unidirectional or bidirectional or rotating.

8 . The method as claimed in claim 1 , wherein in use of said component the first of said at least two different component volumes
(CA 1 -CA 7 ) is subjected to a creep load and the second of said at least two different component volumes (CA 1 -CA 7 ) is subjected to an LCF load, and that said process parameters (A, B) and said subsequent heat treatment temperature (T_HT) are chosen such that a coarse recrystallized grain structure is established in said first component volume, and a fine grain structure is established in said second component volume.

9 . The method as claimed in claim 1 , wherein said component is part of a turbo machine, especially a gas turbine.

10 . The method as claimed in claim 9 , wherein said component is a blade of a gas turbine.

11 . The method as claimed in claim 10 , wherein said blade has a leading edge and a trailing edge, that component volumes (CA 1 , CA 3 ; CA 4 , CA 7 ) at said leading edge and said trailing edge are manufactured with a fine grain structure suitable for LCF-loaded areas, and that the component volume (CA 2 ) between said leading edge and said trailing edge is manufactured with a coarse recrystallized grain structure suitable for creep-loaded areas.

12 . The method as claimed in claim 6 , wherein said component is made of a Ni-based superalloy, that said at least two process parameters (A, B) are chosen, such that the resulting recrystallization temperatures (T_RX_A, T_RX_B) lie in a range around 1200° C. and differ by at least 20° C.

13 . The method as claimed in claim 1 , wherein the heat treatment comprises the step of applying fast heating with a heating rate of at least 25° C./min.

14 . The method as claimed in claim 1 , wherein the step of manufacturing includes building up a crystallographic orientation, and the heat treatment removes the crystallographic orientation in at least one component volume.

Assignees

• Alstom Technology Ltd

Inventors

• Engeli Roman
• Etter Thomas
• Meidani Hossein

Classifications

• C22F1/10

  of nickel or cobalt or alloys based thereon · CPC title

• B22F3/105

  by using electric current {other than for infrared radiant energy}, laser radiation or plasma (B22F3/11 takes precedence){; by ultrasonic bonding (B22F3/115 takes precedence)} · CPC title

• B22F5/04 Primary

  of turbine blades · CPC title

• C21D9/00

  Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor · CPC title

• B23K26/342 Primary

  Build-up welding · CPC title