Intersage seal assembly for counter rotating turbine

Patent metadata

Field	Value
Publication number	US-10774668-B2
Application number	US-201715709642-A
Country	US
Kind code	B2
Filing date	Sep 20, 2017
Priority date	Sep 20, 2017
Publication date	Sep 15, 2020
Grant date	Sep 15, 2020

Abstract

The present disclosure is directed to a gas turbine engine including a turbine rotor assembly that includes a first turbine rotor and a second turbine rotor. The first turbine rotor includes an outer rotor and a plurality of outer rotors extended inwardly along a radial direction from the outer rotor. The second turbine rotor includes an inner rotor and a plurality of inner rotor airfoils extended outwardly along the radial direction from the inner rotor. The plurality of outer rotor airfoils and inner rotor airfoils are disposed in alternating arrangement along a longitudinal direction. One or more rotating seal interfaces are defined between the first turbine rotor and the second turbine rotor.

First claim

What is claimed is:

1. A gas turbine engine, comprising:
a turbine rotor assembly comprising a first turbine rotor and a second turbine rotor, wherein the first turbine rotor comprises an outer rotor and a plurality of outer rotor airfoils extended inwardly along a radial direction from the outer rotor, and wherein the second turbine rotor comprises an inner rotor and a plurality of inner rotor airfoils extended outwardly along the radial direction from the inner rotor, and further wherein the plurality of outer rotor airfoils and inner rotor airfoils are disposed in alternating arrangement along a longitudinal direction, and wherein one or more rotating seal interfaces are defined between the first turbine rotor and the second turbine rotor, wherein the one or more rotating seal interfaces comprises;
a first platform extended at least partially along a longitudinal direction and along a circumferential direction relative to an axial centerline;
a second platform radially spaced from the first platform, the second platform extended at least partially along a longitudinal direction and along a circumferential direction relative to an axial centerline; and
a spring assembly coupled to the first platform, the spring assembly disposed between the first platform and the second platform, wherein the spring assembly permits displacement at least along the radial direction toward the first platform.

2. The gas turbine engine of claim 1 , wherein the one or more rotating seal interfaces are defined at an outer diameter of the plurality of inner rotor airfoils and at an inner diameter of the outer rotor.

3. The gas turbine engine of claim 1 , wherein the one or more rotating seal interfaces are defined at an inner diameter of the plurality of outer rotor airfoils and at an outer diameter of the inner rotor.

4. The gas turbine engine of claim 1 , wherein
the first platform is coupled to an inner diameter of the plurality of outer rotor airfoils or an outer diameter of the inner rotor
and wherein the second platform is coupled to the spring assembly, wherein the second platform is coupled to the spring assembly radially opposite of the first platform such as to be radially inward of the first platform.

5. The gas turbine engine of claim 4 , wherein the one or more rotating seal interfaces further comprise
a third platform coupled to the outer diameter of the plurality of inner rotor airfoils or the inner diameter of the plurality of outer rotor airfoils, wherein the third platform is disposed radially adjacent to the first turbine rotor or the second turbine rotor, and further wherein the third platform is extended at least partially along the longitudinal direction and along the circumferential direction relative to the axial centerline.

6. The gas turbine engine of claim 5 , wherein the one or more rotating seal interfaces further comprise one or more teeth extended along the radial direction and extended along the circumferential direction relative to the axial centerline, wherein the one or more teeth are in adjacent arrangement along the longitudinal direction.

7. The gas turbine engine of claim 6 , wherein the teeth are disposed on the second platform, and wherein the teeth are extended generally along the radial direction toward the third platform.

8. The gas turbine engine of claim 7 , wherein the teeth are disposed on the third platform, wherein the teeth are extended generally along the radial direction toward the second platform.

9. The gas turbine engine of claim 8 , wherein the third platform further defines a rib disposed radially inward of the teeth, the rib defining a weight promoting deflection of the third platform along the radial direction.

10. The gas turbine engine of claim 5 , wherein the third platform is extended along the longitudinal direction and cantilevered from a radial portion of the turbine rotor assembly.

11. The gas turbine engine of claim 10 , wherein a radius is defined between the third platform and a radial portion of the turbine rotor assembly, the radius promoting deflection of the third platform along the radial direction.

12. The gas turbine engine of claim 4 , wherein the one or more rotating seal interfaces define a foil seal assembly together at the first turbine rotor and the second turbine rotor.

13. The gas turbine engine of claim 4 , wherein one or more of the first platform, the spring assembly, and the second platform are segmented along the circumferential direction, permitting substantially independent radial displacement of each segment relative to one another.

14. The gas turbine engine of claim 8 , wherein the second platform defines an abradable material at least on a diameter radially opposing the teeth disposed on the third platform.

15. The gas turbine engine of claim 1 , wherein the outer rotor airfoils define a first material defining a ceramic matrix composite material or a titanium-based alloy.

16. The gas turbine engine of claim 1 , wherein the second platform comprises one or more teeth extended along the radial direction toward the first platform and extended along the circumferential direction relative to the axial centerline, wherein the one or more teeth are in adjacent arrangement along the longitudinal direction, and wherein the first platform comprises an abradable material at least on a diameter radially opposing the second platform.

17. The gas turbine engine of claim 1 , wherein the first platform is positioned at an inner diameter of the outer rotor airfoils or an outer diameter of the inner rotor airfoils, and wherein the second platform is positioned at the outer diameter of the inner rotor airfoils or at the inner diameter of the outer rotor airfoils rotor opposite of the first platform.

18. The gas turbine engine of claim 17 , wherein the second platform further comprises a first wall and a second wall extended along the radial direction and separated along the longitudinal direction, and wherein the spring assembly is positioned between the first wall and the second wall, and wherein the spring assembly permits displacement of the second platform relative to the first platform along the longitudinal direction between the first turbine rotor and the second turbine rotor.

19. The gas turbine engine of claim 18 , wherein an axial wall is coupled to the first wall and the second wall and positioned therebetween, and wherein a fluid passage is defined between the first platform, the second platform, and the axial wall.

20. The gas turbine engine of claim 17 , wherein the first platform or the second platform defines a carbon seal surface longitudinally adjacent to another of the first platform or the second platform at the first turbine rotor or the second turbine rotor, wherein the carbon seal surface is defined circumferentially along the first platform or the second platform relative to the axial centerline.

Assignees

• Gen Electric

Inventors

• Wesling Richard Alan
• Zatorski Darek Tomasz

Classifications

• F01D11/16

  by self-adjusting means (F01D11/12 takes precedence) · CPC title

• F01D11/14

  Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing (rotors with blades adjustable in operation F01D7/00) · CPC title

• F01D5/225

  by shrouding · CPC title

• F01D11/02

  by non-contact sealings, e.g. of labyrinth type (for sealing space between rotor blade tips and stator F01D11/08) · CPC title

• F05D2240/59

  Lamellar seals · CPC title