Granted Patent B2

US 12,649,185 · App. 18/017,804 · Granted Jun 9, 2026

Inventors: Timo Schudeleit (Dübendorf, CH); Egon Seegers (Eschenbach, CH); Lukas Gampp (Schoenenbuch, CH); Felix Kaech (Baden, CH)

Assignee: ACCELLERON SWITZERLAND LTD.

B22F10/40B22F5/04B33Y40/20B33Y80/00

Abstract

Claims (23)

1 . A method for manufacturing a vaned component of a turbomachine, the method comprising:

providing a base portion, the base portion being part of the vaned component and serving as a starting point for manufacturing the vaned component;

additively manufacturing, on top of the base portion, a plurality of vanes and a plurality of support structures, the plurality of support structures having predetermined breaking points;

additively manufacturing, on top of the plurality of support structures and the vanes, a top portion being supported by the plurality of support structures, whereby the vanes are sandwiched between the base portion and the top portion; and

applying a pressurized jet to the plurality of support structures, thereby breaking the predetermined breaking points of the plurality of support structures and removing the plurality of support structures, wherein applying the pressurized jet to the plurality of support structures comprises alternatingly applying the pressurized jet to an outer side that faces the pressurized jet and an inner side that faces the vanes of the vaned component of the plurality of support structures, thereby targeting the plurality of support structures at their outer side and at their inner side in an alternating manner.

2 . The method according to claim 1 , wherein the pressurized jet is applied to the support structures for imparting an impulse onto a main portion of the support structures, the impulse onto the main portion resulting in the breaking of the predetermined breaking points arranged between the main portion and the top of the support structures.

3 . The method according to claim 1 , wherein the plurality of support structures comprises first support structures and second support structures, wherein the first support structures are additively manufactured on top of the base portion so that the first support structures are sandwiched between the top portion and the base portion.

4 . The method according to claim 3 , wherein the second support structures are provided on a build plate, and wherein the method further comprises

additively manufacturing, on the top of a build plate, the second support structures, so that the second support structures are sandwiched between the build plate and the top portion.

5 . The method according to claim 3 , wherein the second support structures are manually removed from the vaned component.

6 . The method according to claim 1 , wherein applying the pressurized jet comprises periodically altering a pressure of the pressurized jet for generating a pulsed pressurized jet.

7 . The method according to claim 1 , wherein applying the pressurized jet comprises periodically realigning a direction of the jet with the plurality of support structures for impacting different target points at the plurality of support structures.

8 . The method according to claim 1 , wherein the vaned component defines an essentially vertical axis, and wherein the support structures have a main portion with a horizontal cross-section, the horizontal cross-section being elongated with an axis of elongation being essentially normal to a direction from which the jet is applied.

9 . The method according to claim 1 , wherein applying the pressurized jet comprises applying a pressurized fluid jet in a volume flow of between 1 l/min and 50 l/min.

10 . The method according to claim 1 , wherein applying the pressurized jet comprises applying the pressurized jet with a jet velocity of between >150 m/s and <1000 m/s.

11 . The method according to claim 10 , wherein the jet velocity is selected according to a material of the plurality of support structures.

12 . The method according to claim 1 , wherein the vaned component is at least one selected from the group consisting of a casing, a turbine wheel, a nozzle ring, a compressor wheel and a compressor diffuser.

13 . The method according to claim 1 , wherein applying the pressurized jet to the plurality of support structures comprises one selected of the group consisting of applying the pressurized jet manually, automatically and adaptively controlled by a robot.

14 . The method according to claim 1 , wherein the pressurized jet is a pressurized fluid jet, in particular wherein the pressurized jet is a pressurized water jet.

15 . Apparatus for manufacturing a vaned component of a turbomachine, the apparatus comprising:

a first chamber comprising an additive manufacturing device for additive manufacturing a vaned component of the turbomachine having a plurality of support structures;

a second chamber comprising at least one pressurized jet device for providing a pressurized jet to remove the plurality of support structures; and

a controller being configured to issue commands to carry out the method according to claim 1 .

Assignments (3)

Priority Claims (1)

Continuity (1)

References Cited (21)