Intersage seal assembly for counter rotating turbine

Patent metadata

Field	Value
Publication number	US-2019085712-A1
Application number	US-201715709642-A
Country	US
Kind code	A1
Filing date	Sep 20, 2017
Priority date	Sep 20, 2017
Publication date	Mar 21, 2019
Grant date	—

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 rotors 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.

2 . The gas turbine engine of claim 1 , wherein the rotating seal interface is 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 rotating seal interface is 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 rotating seal interface comprises:
a first platform coupled to an inner diameter of the plurality of outer rotor airfoils or an outer diameter of the inner rotor, wherein the first platform is extended at least partially along a longitudinal direction and along a circumferential direction relative to an axial centerline; a spring assembly coupled to the first platform, the spring assembly disposed between the first platform and a radially adjacent turbine rotor, wherein the spring assembly permits displacement at least along the radial direction toward the first platform; and a second platform 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 or radially outward of the first platform, and wherein the second platform is extended at least partially along the longitudinal direction and along the circumferential direction relative to the axial centerline.

5 . The gas turbine engine of claim 4 , wherein the rotating seal interface further comprises:
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 platform on the opposing rotor of the turbine rotor assembly, 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 rotating seal interface further defines one or more teeth extended along the radial direction toward the radially adjacent turbine rotor 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 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 and 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 the 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 rotating seal interface defines 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 defines a first material defining a density of approximately 4.0 g/cm3 or less.

16 . The gas turbine engine of claim 1 , wherein rotating seal interface comprises:
a second platform coupled to an inner diameter of the outer rotor airfoils or an outer diameter of the inner rotor airfoils; and a third platform coupled to the opposing rotor of the turbine rotor assembly radially opposite of the second platform, wherein the third platform defines one or more teeth extended along the radial direction toward the second 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 second platform defines an abradable material at least on a diameter radially opposing the third platform.

17 . The gas turbine engine of claim 1 , wherein the rotating seal interface defines a first platform extended along the radial direction and a second platform extended along the radial direction and adjacent along the longitudinal direction to the first platform, and wherein the first platform is defined at an inner diameter of the outer rotor airfoils or an outer diameter of the inner rotor airfoils, and wherein the second platform is defined at the opposing turbine rotor at the outer diameter of the inner rotor airfoils or at the inner diameter of the outer rotor airfoils.

18 . The gas turbine engine of claim 17 , wherein the second platform further defines a first wall and a second wall extended along the radial direction and separated along the longitudinal direction, and wherein a spring assembly is defined 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 defined 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 the opposing platform, 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

• F01D11/122 Primary

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

• F02K3/072

  with counter-rotating {, e.g. fan} rotors · CPC title

• F02C3/067

  having counter-rotating rotors (F02C3/073 takes precedence) · CPC title

• 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