COVER PLATE WITH INTERSTAGE SEAL FOR A GAS TURBINE ENGINE

• US 20120177485A1
• Filed: 01/11/2011
• Published: 07/12/2012
• Est. Priority Date: 01/11/2011
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Virkler, Scott D., Gates, Roger
• Granted Patent: US 8,740,554 B2
• Time in Patent Office: Days
• US Class Current: 415/173.7
• CPC Class Codes: F01D 1/10 having two or more stages subjected to working-fluid flow without essential intermediate pressure change, i.e. with velocity stages F01D1/12 takes precedence
• CPC Class Codes: F01D 11/001 for sealing space between stator blade and rotor
• CPC Class Codes: F01D 5/3015 with side plates
• CPC Class Codes: Y10T 29/49826 Assembling or joining

Abstract

An air seal assembly for a gas turbine engine includes a first cover plate with a radially extending knife edge seal defined about and axis of rotation. The first cover plate is mountable to a first rotor disk for rotation therewith, the first radially extending knife edge seal interfaces with a vane structure. A second cover plate with a second radially extending knife edge seal defined about the axis of rotation, the second cover plate mountable to the second rotor disk for rotation therewith. The second radially extending knife edge seal interfaces with the vane structure.

Claims

1. An air seal assembly for a gas turbine engine comprising:

a first rotor disk defined about an axis of rotation;

a second rotor disk defined about said axis of rotation;

a vane structure axially between said first rotor disk and said second rotor disk;

a first cover plate with a radially extending knife edge seal defined about said axis of rotation, said first cover plate mountable to an aft surface of said first rotor disk for rotation therewith, said first radially extending knife edge seal interfaces with said vane structure; and

a second cover plate with a second radially extending knife edge seal defined about said axis of rotation, said second cover plate mountable to a forward surface of said second rotor disk for rotation therewith, said second radially extending knife edge seal interfaces with said vane structure.

2. The air seal assembly as recited in claim 1, wherein said first radially extending knife edge seal extends outward from a first cylindrical extension that extends from said first cover plate.

3. The air seal assembly as recited in claim 2, further comprising a second radially extending knife edge seal which extends outward from said first cylindrical extension.

4. The air seal assembly as recited in claim 3, wherein said second radially extending knife edge seal is generally parallel to said radially extending knife edge seal.

5. The air seal assembly as recited in claim 3, wherein said radially extending knife edge seal defines a first diameter greater than a second diameter of said second radially extending knife edge seal.

6. The air seal assembly as recited in claim 5, wherein said second radially extending knife edge seal defines an axial end of said cylindrical extension.

7. The air seal assembly as recited in claim 1, wherein said second radially extending knife edge seal extends outward from a second cylindrical extension that extends from said second cover plate.

8. The air seal assembly as recited in claim 1, wherein said first cover plate is mounted to an aft face of said first rotor disk.

9. The air seal assembly as recited in claim 8, wherein said second cover plate is mounted to a forward face of said second rotor disk.

10. The air seal assembly as recited in claim 1, wherein said first cover plate faces said second cover plate.

11. The air seal assembly as recited in claim 1, wherein said first rotor disk is attached to said second rotor disk.

12. The air seal assembly as recited in claim 1, wherein said vane structure is a turbine vane structure.

13. The air seal assembly as recited in claim 1, wherein said vane structure includes a honeycomb seal.

14. The air seal assembly as recited in claim 1, wherein said first radially extending knife edge seal extends outward from a first cylindrical extension that extends from said first cover plate and said second radially extending knife edge seal extends outward from a second cylindrical extension that extends from said second cover plate.

15. A method to assemble an air seal assembly of a gas turbine engine comprising:

mounting a first cover plate with a radially extending knife edge seal defined about a axis of rotation to a first rotor disk for rotation therewith, the first radially extending knife edge seal interfacing with a vane structure; and

mounting a second cover plate with a radially extending knife edge seal defined about a axis of rotation to a second rotor disk for rotation therewith, the second radially extending knife edge seal interfacing with the vane structure.

16. The method as recited in claim 15, further comprising:

mounting the first rotor disk to the second rotor disk.

17. The method as recited in claim 15, further comprising:

axially spacing the first radially extending knife edge seal from the second radially extending knife edge seal.