Seal assembly for counter rotating turbine assembly

Patent metadata

Field	Value
Publication number	US-10458267-B2
Application number	US-201715709617-A
Country	US
Kind code	B2
Filing date	Sep 20, 2017
Priority date	Sep 20, 2017
Publication date	Oct 29, 2019
Grant date	Oct 29, 2019

Abstract

The present disclosure is directed to a gas turbine engine including a turbine rotor, a turbine frame at least partially surrounding the turbine rotor, and an outer diameter seal assembly. The turbine rotor includes an inner shroud, an outer shroud, and at least one connecting airfoil coupling the inner shroud and the outer shroud. The outer shroud includes a plurality of outer shroud airfoils extended inward along a radial direction. The outer diameter seal assembly includes a sliding portion disposed between the turbine frame and the outer shroud of the turbine rotor. The outer diameter seal assembly defines a secondary tooth at the outer shroud radially inward of a longitudinal face of the sliding portion, and a primary tooth defined axially adjacent to a radial face of the sliding portion.

First claim

What is claimed is:

1. A gas turbine engine, comprising:
a turbine rotor comprising an inner shroud, an outer shroud, and at least one connecting airfoil coupling the inner shroud and the outer shroud, wherein the outer shroud comprises a plurality of outer shroud airfoils extended inward along a radial direction;
a turbine frame at least partially surrounding the turbine rotor; and
an outer diameter seal assembly comprising a sliding portion disposed between the turbine frame and the outer shroud of the turbine rotor, wherein the outer diameter seal assembly defines a secondary tooth at the outer shroud radially inward of a longitudinal face of the sliding portion, and a primary tooth defined axially adjacent to a radial face of the sliding portion.

2. The gas turbine engine of claim 1 , wherein the radial face of the sliding portion defines a plurality of feed holes therethrough, and wherein a flow of air enters and egresses therethrough.

3. The gas turbine engine of claim 1 , wherein the secondary tooth and the primary tooth are each defined on the outer shroud of the turbine rotor.

4. The gas turbine engine of claim 1 , wherein the secondary tooth and the longitudinal face of the sliding portion together define a radial gap therebetween.

5. The gas turbine engine of claim 1 , wherein the primary tooth and the radial face of the sliding portion together define an axial gap therebetween.

6. The gas turbine engine of claim 1 , wherein the sliding portion defines a plurality of vent openings therethrough.

7. The gas turbine engine of claim 1 , further comprising:
a fifth manifold coupled to the turbine frame, wherein the fifth manifold provides a pressurized flow of air to the outer diameter seal assembly.

8. The gas turbine engine of claim 7 , wherein the fifth manifold is coupled to a pressure regulating valve in fluid communication with a second manifold providing pressurized air from a first turbine bearing.

9. The gas turbine engine of claim 8 , further comprising:
a compressor section, wherein the fifth manifold is coupled to the compressor section and extended to the turbine frame to provide a pressurized flow of air to the seal assembly.

10. The gas turbine engine of claim 1 , wherein the turbine frame further comprises a springing structure providing displacement of the sliding portion of the outer diameter seal assembly.

11. A method of operating a seal assembly between a static turbine frame and an outer shroud rotor for an interdigitated turbine engine, the method comprising:
flowing air from a compressor section to a rotatable outer shroud of an interdigitated turbine section;
generating an air bearing between the outer shroud and a sliding portion of the seal assembly; and
adjusting the flow of air to the outer shroud based at least on an engine condition of the turbine engine.

12. The method of claim 11 , wherein generating the air bearing comprises:
directing the flow of air across a radial gap defined between a secondary tooth and a longitudinal face of a turbine frame; and
directing the flow of air across an axial gap defined between a primary tooth and a radial face of the sliding portion.

13. The method of claim 12 , wherein generating the air bearing further comprises:
generating a high pressure flow across the secondary tooth and the primary tooth; and
egressing the high pressure flow through a vent opening in fluid communication with a core flowpath of the engine.

14. The method of claim 13 , wherein generating the air bearing further comprises:
generating, via the high pressure flow, an opening force at the sliding portion adjacent to the primary tooth.

15. The method of claim 13 , wherein generating the air bearing further comprises:
egressing a flow of air across a cavity defined between the sliding portion and a longitudinal portion of the outer shroud.

16. The method of claim 11 , wherein adjusting the flow of air to the outer shroud further comprises:
determining a desired clearance gap between the outer shroud and a radially outward end of a plurality of second turbine airfoils of the second turbine rotor.

17. The method of claim 11 , wherein adjusting the flow of air to the outer shroud further comprises:
determining a desired radial gap between an outer diameter seal assembly and the outer shroud; and
determining a desired axial gap between the outer diameter seal assembly and the outer shroud.

18. The method of claim 11 , wherein adjusting the flow of air to the outer shroud further comprises:
pressurizing a first side of the outer diameter seal assembly, wherein pressurizing the first side provides a flow of air between the outer shroud and the outer diameter seal assembly.

19. The method of claim 18 , wherein pressurizing the first side of the outer diameter seal assembly comprises pressurizing an aspirating face seal assembly between the outer shroud and a turbine frame.

20. The method of claim 11 , further comprising:
determining a desired flow or pressure of air at one or more of the outer shroud and second turbine rotor based on one or more of a lookup table, a transfer function, and a curve comprising at least a function of radial dimensions of the outer shroud and the second turbine rotor relative to one or more of a rotational speed of the outer shroud, a rotational speed of the second turbine rotor, an exhaust gas temperature, a material thermal expansion constant relative to the outer shroud, and a material thermal expansion constant relative to the second turbine rotor.

Assignees

• Gen Electric

Inventors

• Gibson Nathan Evan Mccurdy
• Zatorski Darek Tomasz

Classifications

• F01D11/16

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

• F01D11/14 Primary

  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

• F01D11/025

  Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations · CPC title

• F01D5/03

  Annular blade-carrying members having blades on the inner periphery of the annulus and extending inwardly radially, i.e. inverted rotors · CPC title

• F05D2240/55

  Seals · CPC title