Hybrid inner air seal for gas turbine engines

Patent metadata

Field	Value
Publication number	US-9416673-B2
Application number	US-201213351290-A
Country	US
Kind code	B2
Filing date	Jan 17, 2012
Priority date	Jan 17, 2012
Publication date	Aug 16, 2016
Grant date	Aug 16, 2016

Abstract

A turbine section has a turbine rotor carrying turbine blades. The turbine blades include seal members at a radially inner location. A vane section is formed of a plurality of circumferentially spaced vane components, each of which has an airfoil extending radially outwardly of a platform. A first seal member is fixed to the platform, and is positioned to be adjacent a seal from a blade which is positioned in one axial direction relative to the first seal member. A second seal member extends circumferentially beyond at least a plurality of the vane components and is positioned to be adjacent a seal member of a blade on an opposed axial side from the first blade. A vane component is also disclosed and claimed.

First claim

The invention claimed is:

1. A turbine section comprising:
first and second turbine rotors each carrying turbine blades for rotation about a central axis, said rotors each having at least one rotating seal at a radially inner location;
a vane section formed of a plurality of circumferentially spaced vane components, each of said vane components having an airfoil extending radially outwardly of a platform;
a first seal fixed to said platform, said first seal having a seal material positioned to be adjacent said at least one rotating seal from the first rotor which is positioned in one axial direction relative to said first seal;
a second seal extending circumferentially beyond at least a plurality of said vane components, said second seal having seal material positioned to be adjacent said at least one rotating seal of the second rotor on an opposed axial side from said first rotor, the second seal extends for a greater circumferential extent than does the first seal;
said first and second seals include said seal material mounted onto a seal mount, and wherein said material is more abradable than a material forming said mount; and
a first arm is fixed to said platform and extends radially inwardly in an opposed direction from said airfoil, with said arm extending to said seal mount for said first seal, and a second arm extending radially inwardly from platform, with said second arm including a connection to said mount for said second seal that allows movement.

2. The turbine section as set forth in claim 1 , wherein said second seal is circumferentially continuous.

3. The turbine section as set forth in claim 2 , wherein said second seal is connected to said platforms of said plurality of vane components, but is radially movable relative to said platforms.

4. The turbine section as set forth in claim 1 , wherein each of said plurality of circumferentially spaced vane components includes a plurality of vane members.

5. The turbine section as set forth in claim 1 , wherein at least said second seal is a non-contact seal.

6. The turbine section as set forth in claim 1 , wherein said first seal extends for a circumferential extent similar to that of said platform.

7. The turbine section as set forth in claim 1 , wherein one of said second arm and said mount for said second seal has a slot that receives a pin to provide said connection to allow said radial movement.

8. A vane and seal comprising:
a vane component having an airfoil extending radially outwardly of a platform;
a first seal fixed to said platform, said first seal having a seal material positioned to be adjacent at least one rotating seal which is positioned in one axial direction relative to said first seal when the vane component is positioned in a turbine section;
a second seal extending circumferentially beyond said vane component, said second seal having seal material positioned to be adjacent at least one rotating seal when the vane component is positioned in a turbine section, and on an opposed axial side from the one axial direction;
wherein said second seal is connected to said platform of said vane component, but is radially movable relative to said platform, the second seal extends for a greater circumferential extent than does the first seal;
said first and second seal includes a said material mounted onto a seal mount, and wherein said material is more abradable than a material forming said mount; and
a first arm is fixed to said platform and extends radially inwardly in an opposed direction from said airfoil, with said first arm extending to said seal mount for said first seal and a second arm extending radially inwardly from said platform, with said second arm including a connection to said mount for said second seal that allows said radial movement.

9. The vane and seal as set forth in claim 8 , wherein said second seal is circumferentially continuous.

10. The vane and seal as set forth in claim 8 , wherein said vane component includes a plurality of vane members.

11. The vane and seal as set forth in claim 8 , wherein said second seal is a non-contact seal.

12. The vane and seal as set forth in claim 8 , wherein said first seal extends for a circumferential extent similar to that of said platform.

13. The vane and seal as set forth in claim 8 , wherein one of said second arm and said mount for said second seal has a slot that receives a pin to provide said connection to allow said radial movement.

14. A vane and seal comprising:
a vane component having an airfoil extending radially outwardly of a platform; and
a first seal fixed to said platform, said first seal having a seal material positioned to be adjacent at least one rotating seal from a first rotor which is positioned in one axial direction relative to said first seal when the vane component is positioned in a turbine section;
a second seal extending circumferentially beyond said vane component, said second seal having seal material positioned to be adjacent at least one rotating seal of a second rotor when the vane component is positioned in a turbine section, and on an opposed axial side from the first rotor;
said second seal being circumferentially continuous and connected to said platform of said vane component, but being radially movable relative to said platform;
said first and second seal including said seal material mounted onto a seal mount, and wherein said seal material being more abradable than a material forming said mount; and
a first arm being fixed to said platform and extending radially inwardly in an opposed direction from said airfoil, with said first arm extending to said seal mount for said first seal, and a second arm extending radially inwardly from said platform, with said second arm including a connection to said mount for said second seal that allows said radial movement, the second seal extends for a greater circumferential extent than does the first seal.

15. The vane and seal as set forth in claim 14 , wherein said first seal extends for a circumferential extent similar to that of said platform.

16. The vane and seal as set forth in claim 14 , wherein one of said second arm and said mount for said second seal has a slot that receives a pin to provide said connection to allow said radial movement.

Assignees

• Caprario Joseph T
• Bergman Russell J
• Humphrey Pamela A
• Sandoval Jonathan Perry
• United Technologies Corp

Inventors

• Caprario Joseph T
• Bergman Russell J
• Humphrey Pamela A
• Sandoval Jonathan Perry

Classifications

• F01D11/001 Primary

  for sealing space between stator blade and rotor · CPC title

• F01D11/025

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

• F01D9/04

  forming ring or sector · CPC title