Turbine disk interstage seal system

• US 5,236,302 A
• Filed: 10/30/1991
• Issued: 08/17/1993
• Est. Priority Date: 10/30/1991
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Glynn, Christopher C., Albrecht, Richard W., Meade, Robert J., Weisgerber, Robert H., Kutney, John T. Jr.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): Lee, Michael S.
• Application Number:
  US07/785,404
• Time in Patent Office: 657 Days
• Field of Search: 416/198 A, 415/199.5, 415/173.7, 415/174.5, 415/115
• US Class Current: 415/173.7
• CPC Class Codes: F01D 11/001 for sealing space between stator blade and rotor
• CPC Class Codes: F01D 5/06 Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections F01D5/022, F01D5/023 take precedence
• CPC Class Codes: F01D 5/066 Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
• CPC Class Codes: F01D 5/082 on the side of the rotor disc
• CPC Class Codes: F01D 5/085 cooling fluid circulating inside the rotor

Abstract

A turbine engine of the type having a compressor section, combustor section and high-pressure turbine section in which compressor air is conveyed internally of the compressor and turbine sections to cool the turbine interstage volume, a first stage turbine disk includes a shaft supporting a second stage turbine disk, a turbine interstage seal is secured by boltless engagement to the disks and is prestressed to resist flexure, and the first stage disk carries a forward seal attached by boltless connections. The interstage seal includes a bore having a rearwardly-extending arm engaging the aft shaft in a bayonet connection to prevent deflection of the bore and includes passages to allow air flow around the bore. The forward seal includes radially-extending vanes to convey cooling air along the disk, and is secured by inward and outward bayonet connections, the inward connection including locking pins which are arranged to perform a balancing function.

Claims

1. In a turbine engine of a type having a turbine section including first and second stage disks mounted on a compressor shaft, an interstage seal system comprising:

an outer, generally cylindrical housing having an outer forward arm engaging said first stage disk and an outer rearward arm engaging said second stage disk, said forward and rearward arm being arcuate in shape in an axial direction, each having a reverse catenary contour, said forward arm and said first stage disk including means forming a bayonet connection therebetween, and means forming an anti-rotation connection therebetween.

2. The system of claim 1 wherein said forward arm includes a forwardly-facing axial stop abutting said first stage disk;

and a radially outward-facing radial stop abutting said first stage disk, said axial and radial stop engagements preventing forward axial and outward radial deflection, respectively, of said forward arm.

3. The system of claim 2 wherein said bayonet connection includes said forward arm having a plurality of radially inwardly-extending teeth;

and said first stage disk having a plurality of radially outwardly-extending tabs, said tabs being spaced apart from each other and from said first stage disk to receive said teeth between said tabs, and between said tabs and said first stage disk in said bayonet connection, whereby rearward axial movement of said forward arm relative to said first stage disk is prevented.

4. In a turbine engine of a type having a turbine section including first and second stage disks mounted on a compressor shaft, an interstate seal system comprising:

an outer, generally cylindrical housing having a forward arm engaging said first stage disk and a rearward arm engaging said second stage disk, said forward arm and said first stage disk including means forming a bayonet connection therebetween, and means forming an anti-rotation connection therebetween;

said forward arm including a forwardly-facing axial stop abutting said first stage disk; and

a radially outward-facing radial stop abutting said first stage disk, said axial and radial stop engagements preventing forward axial and outward radial deflection, respectively, of said forward arm;

said bayonet connection includes said forward arm having a plurality of radially inward-extending teeth; and

said first stage disk having a plurality of radially outwardly-extending tabs, said tabs being spaced apart from each other and from said first stage disk to receive said teeth between said tabs, and between said tabs and said first stage disk in said bayonet connection, whereby rearward axial movement of said forward arm relative to said first stage disk is prevented; and

said first stage disk includes at least one blade having a tab projecting rearwardly from a root thereof; and

said forward arm includes forwardly projecting tab means for meshing with said tab.

5. The system of claim 4 wherein said forward arm includes a radially outward-extending forward blade retaining seal abutting a rear surface of said first stage disk, said seal including an annular wedge-shaped recess and an annular seal wire positioned therein forming a fluid tight seal between said forward arm and said first stage disk.

6. The system of claim 5 wherein said housing includes an aft arm, said aft arm cooperating with said second stage disk to form means for receiving a split ring;

and said system includes a split ring in said receiving means, whereby forward axial movement of said aft arm is prevented.

7. The system of claim 6 wherein said aft arm includes a radially outward-extending blade retaining aft seal abutting a forward face of said second stage disk, said aft seal including an annular wedge-shaped recess and an annular seal wire positioned therein forming a fluid tight seal between said forward arm and said second stage disk.

8. The system of claim 7 wherein said aft arm includes an annular, radially-extending axial stop abutting said second stage disk forward face.

9. The system of claim 8 wherein said forward and aft arms are arcuate in shape in an axial direction, each having a reverse catenary contour.

10. The system of claim 9 wherein said outer housing is shaped to be placed in compression when mounted between said first and second stage disks, whereby said forward and aft arms are flexed inwardly to ensure a fluid tight seal between said housing and said disks.

11. The system of claim 10 wherein said housing includes a web and bore extending radially inwardly between said first and second stage disks.

12. In a turbine engine of a type having a turbine section including first and second stage disks mounted on a compressor shaft, and interstage seal system comprising:

an outer, generally cylindrical housing having a forward arm engaging said first stage disk and a rearward arm engaging said second stage disk, said forward arm and said first stage disk including means forming a bayonet connection therebetween, and means forming an anti-rotation connection therebetween;

said housing including a web and bore extending radially inwardly between said first and second stage disks; and

said bore includes a rearwardly-extending conical arm;

said first stage disk includes a cylindrical aft shaft; and

said conical arm and said aft shaft include means cooperating to form a bayonet connection, whereby axial deflection of said web and bore is prevented.

13. The system of claim 12 wherein said bayonet connection includes a plurality of passages permitting cooling air to flow through said connection.

14. The system of claim 13 wherein said bayonet connection includes said conical arm having a plurality of radially inward-extending teeth;

and said aft shaft having a plurality of tabs spaced to receive said teeth therebetween and a circumferential rib spaced from aid tabs to receive said teeth therebetween.