Rotor blade shroud for a turbomachine, rotor blade, method of making a rotor blade shroud and a rotor blade

Patent metadata

Field	Value
Publication number	US-11098609-B2
Application number	US-201916253497-A
Country	US
Kind code	B2
Filing date	Jan 22, 2019
Priority date	Jan 23, 2018
Publication date	Aug 24, 2021
Grant date	Aug 24, 2021

Abstract

The present invention relates to a rotor blade shroud for a turbomachine, comprising a sealing tip and a support structure that abuts the sealing tip. The support structure has at least one intermediate region in which a structural segment is arranged, wherein the radially outwardly arranged surface of the support structure and of the structural segment forms an essentially planar surface. The present invention further relates to a rotor blade for a turbomachine, comprising a rotor blade shroud as well as two methods of manufacturing a rotor blade shroud and a method of manufacturing a rotor blade.

First claim

What is claimed is:

1. A rotor blade shroud for a turbomachine, comprising:
one sealing tip or a plurality of sealing tips and a support structure that abuts the one or plurality of sealing tips,
wherein the support structure has at least one intermediate region in which a structural segment is arranged,
wherein the radially outwardly arranged surface of the support structure and of the structural segment forms a closed hollow structure, and
wherein the at least one intermediate region forms a recess that receives the structural segment.

2. The rotor blade shroud according to claim 1 , wherein the support structure and the structural segment comprise the same material, and are formed integrally with each other, being jointly formed in an integrally additive manner.

3. The rotor blade shroud according to claim 1 , wherein the support structure is produced from a first material or comprises a first material, and wherein the structural segment is produced from a second material or comprises a second material, wherein the first material and the second material are different.

4. The rotor blade shroud according to claim 1 , wherein the support structure has at least two intermediate regions in which two structural segments are arranged.

5. The rotor blade shroud according to claim 1 , wherein the one sealing tip or a plurality of sealing tips and/or the support structure is solid in form.

6. The rotor blade shroud according to claim 1 , wherein the support structure is arranged between the plurality of sealing tips.

7. The rotor blade shroud according to claim 1 , wherein the support structure is rib-shaped in form.

8. The rotor blade shroud according to claim 1 , wherein the at least one structural segment has a hollow structure and/or has a lower density than the support structure.

9. The rotor blade shroud according to claim 1 , wherein the one sealing tip or a plurality of sealing tips have a width over the periphery that is constant and is aligned perpendicularly to the peripheral direction and/or
wherein a second sealing tip is arranged downstream of a first sealing tip, and the second sealing tip is radially displaced outward with respect to the first sealing tip, wherein the first sealing tip and the second sealing tip are arranged essentially parallel to each other in their longitudinal alignment.

10. The rotor blade shroud according to claim 1 ,
wherein the at least one sealing tip is a first sealing tip and a second sealing tip, and
wherein the radially outwardly arranged surface of the support structures and of the further structural segments, and/or the surface of the rotor blade shroud that is arranged radially outward between the first sealing tip and the second sealing tip forms a substantially planar surface over an entire periphery thereof.

11. The rotor blade shroud according to claim 1 , wherein the rotor blade shroud is configured and arranged in a rotor blade.

12. The rotor blade shroud according to claim 1 , wherein the rotor blade shroud is formed by additive manufacturing in one manufacturing step.

13. The rotor blade shroud according to claim 1 , including a rotor blade for a turbomachine formed additive manufacturing in one manufacturing step, wherein the rotor blade comprises the rotor blade shroud.

14. A method of manufacturing a rotor blade shroud for a turbomachine, comprising the steps of:
providing a rotor blade shroud, comprising at least two sealing tips and a support structure that abuts the at least two sealing tips, wherein the support structure has at least one intermediate region, wherein the intermediate region is a recess;
forming, by an additive manufacturing method, of at least one structural segment, and all structural segments, which is or are each arranged in an intermediate region of the support structure, so that, in the case of the manufactured rotor blade shroud, a radially outwardly arranged surface of the support structure and of the structural segments forms a substantially planar surface,
wherein the rotor blade shroud forms a closed hollow structure.

Assignees

• MTU Aero Engines AG

Inventors

• Gier Jochen

Classifications

• F01D11/125

  with a reinforcing structure · CPC title

• F01D5/225

  by shrouding · CPC title

• F01D11/122 Primary

  with erodable or abradable material (blades having cutting or grinding tips F01D5/20) · CPC title

• F05D2300/522

  Density · CPC title

• F05D2240/307

  related to the tip of a rotor blade · CPC title