Turbine engine with interlocking seal

Patent metadata

Field	Value
Publication number	US-11946388-B2
Application number	US-202217863470-A
Country	US
Kind code	B2
Filing date	Jul 13, 2022
Priority date	Aug 2, 2019
Publication date	Apr 2, 2024
Grant date	Apr 2, 2024

Abstract

A turbine engine with an outer rotor that circumscribes an inner rotor. The outer rotor includes circumferentially arranged components with a radial outer end and radial inner end. Inner ends of confronting sides of adjacent components include at least one damper element to dampen the relative motion of the components or to provide at least a partial seal between adjacent components.

First claim

What is claimed is:

1. A turbine engine comprising:
an inner rotor defining and rotating about an axially extending longitudinal axis;
an outer rotor circumscribing at least a portion of the inner rotor and rotating about the longitudinal axis, wherein the outer rotor rotates about the inner rotor;
at least one component coupled to and rotating with the outer rotor or the inner rotor, the at least one component comprising a plurality of circumferentially arranged and radially extending component segments, wherein each of the component segments includes a passage segment located at an inner band and extending between and opening onto a first circumferential end to define a first opening and a second circumferential end to define a second opening; and
a damper element comprising a tube extending at least partially into the passage segments of a confronting open pair defined by the first opening and the second opening of adjacent component segments, wherein the damper element includes a spacer located between the adjacent component segments.

2. The turbine engine of claim 1 , wherein the spacer circumscribes the tube.

3. The turbine engine of claim 1 , wherein the spacer is a ridge.

4. The turbine engine of claim 1 , wherein the spacer is configured to locate the tube with respect to the adjacent component segments.

5. The turbine engine of claim 1 , wherein the tube has a cross-sectional profile smaller than the passage segment.

6. The turbine engine of claim 1 , wherein the passage segments collectively form a circumferential passage.

7. The turbine engine of claim 6 , wherein the tube extends through the circumferential passage.

8. The turbine engine of claim 1 , wherein the tube is a plurality of pieces of tubing.

9. The turbine engine of claim 1 , wherein the damper element dampens relative radial movement, relative tangential movement, or relative axial movement of the adjacent component segments.

10. The turbine engine of claim 1 , wherein the damper element, at least in part, includes nickel, cobalt base alloys, or ceramic material.

11. A turbine engine comprising:
a rotor;
a component coupled to the rotor, the component having a plurality of component segments circumferentially arranged and radially extending from the rotor, each of the plurality of component segments having a passage segment located at an inner band and extending between and opening onto a first circumferential end to define a first opening and a second circumferential end to define a second opening, wherein a confronting open pair is defined by the first opening and the second opening of adjacent component segments of the plurality of component segments; and
a damper element that extends between the confronting open pair, wherein the damper element comprises a tube having a spacer located between the confronting open pair.

12. The turbine engine of claim 11 , wherein the spacer circumscribes the damper element.

13. The turbine engine of claim 11 , wherein the spacer is a ridge.

14. The turbine engine of claim 11 , wherein the spacer is configured to locate the damper element with respect to the adjacent component segments.

15. The turbine engine of claim 11 , wherein the passage segments collectively form a circumferential passage and the damper element extends through the circumferential passage.

16. The turbine engine of claim 11 , wherein the tube is a plurality of pieces of tubing.

17. The turbine engine of claim 11 , wherein the plurality of component segments is a plurality of blades.

18. The turbine engine of claim 11 , wherein the damper element dampens relative radial movement, relative tangential movement, or relative axial movement of the adjacent component segments.

19. A turbine engine comprising:
a rotor;
a component coupled to the rotor, the component having a plurality of component segments circumferentially arranged and radially extending from the rotor, each of the plurality of component segments having a passage segment extending between and opening onto a first circumferential end to define a first opening and a second circumferential end to define a second opening, wherein a confronting open pair is defined by the first opening and the second opening of adjacent component segments of the plurality of component segments; and
a damper element that extends between the confronting open pair, wherein the damper element comprises a tube having a spacer located between the adjacent component segments, wherein the passage segments collectively form a circumferential passage and the damper element extends through the circumferential passage.

20. The turbine engine of claim 19 , wherein the tube is a plurality of pieces of tubing.

Assignees

• Ge Avio Srl

Inventors

• D'Ettole Antonio Giusseppe
• Depalma Andrea
• Maddaleno Roberto
• Usseglio Matteo Renato

Classifications

• F01D5/225 Primary

  by shrouding · CPC title

• F01D11/125

  with a reinforcing structure · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2240/30

  Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor · CPC title

• F05D2240/55

  Seals · CPC title