Cloth seal for an inner compressor discharge case and methods of locating the seal in situ

• US 6,652,231 B2
• Filed: 01/17/2002
• Issued: 11/25/2003
• Est. Priority Date: 01/17/2002
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Fang, Ning, Aksit, Mahmut Faruk, Safi, Ahmad, Mohammed-Fakir, Abdul-Azeez, Vedantam, Srikanth
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): MCALEENAN, JAMES M
• Application Number:
  US10/047,988
• Publication Number:
  US 20030133793A1
• Time in Patent Office: 677 Days
• Field of Search: 415/214.1, 415/138, 415/139, 415/135, 415/216-218, 415/173.7, 415/174.2, 415/170.1, 415/173.6, 277/637, 277/643, 277/644, 277/649, 277/651, 277/653, 277/640, 277/167.5, 277/230, 277/236
• US Class Current: 415/214.1
• CPC Class Codes: F01D 11/005 Sealing means between non relatively rotating elements
• CPC Class Codes: F02C 7/28 Arrangement of seals
• CPC Class Codes: F05D 2240/55 Seals
• CPC Class Codes: F05D 2300/6012 Woven fabrics
• CPC Class Codes: F16J 15/061 with positioning means F16J15/0831 takes precedence
• CPC Class Codes: F16J 15/0812 with a braided or knitted body

Abstract

Upper and lower halves of the inner barrel of a compressor for a turbine are bolted to one another along a horizontal midline joint with metal-to-metal surface contact. Elongated grooves are provided in the engaging surfaces, with the upper groove having a depth greater than the depth of the lower groove. Elongated seals are provided in the grooves, including an elongated shim with a metallic woven covering on opposite sides, and margins having sealing edges. The depth of the seal is equal to or less than the depth of the upper groove and an adherent material maintains the seal in the upper groove during installation. In operation, the adherent material dissolves at temperatures above ambient and the seal drops by gravity to bear against the walls of the grooves in response to high pressure air leaking through any gap at the horizontal midline joint.

Claims

1. An inner compressor discharge case for a gas turbine, comprising:

a cylindrical barrel formed of upper and lower halves joined to one another at margins thereof along a horizontal midline to form a pair of diametrically spaced joints along opposite sides of the barrel, each of said margins having a groove extending generally parallel to an axis of the cylindrical barrel, the grooves of opposed margins of said halves on respective opposite sides of the barrel lying in registration with one another along the horizontal midline;

a seal disposed in each pair of registering grooves;

each said seal including a shim having a pair of sealing surfaces for sealing against surfaces of said registering grooves, respectively; and

a metallic cloth secured along at least one side of said shim and between said sealing surfaces thereof;

each said shim including a metal plate having a generally radially inwardly extending leg terminating in one edge thereof for sealing against a surface of one of said registering grooves, said shim being elongated in said registering grooves and lying in a plane generally tangential to the cylindrical barrel, another edge of said shim having an arcuate portion for sealing against a surface of another of said registering grooves.

2. A case according to claim 1 wherein each said seal in said registering grooves has a depth less than the distance between the bases of said registering grooves whereby the seal is at all times spaced from a base of one of said registering grooves.

3. A case according to claim 1 wherein said metallic cloth and said shim are welded to one another.

4. A case according to claim 1 wherein said edges seal respectively against a lateral side of said one groove and a base of said another groove.

5. A case according to claim 1 wherein each of said seals has a radial extent less than the width of the registering grooves whereby each seal is spaced from a side wall of each of the registering grooves.

6. A case according to claim 1 wherein each said seal in said registering grooves has a depth equal to or less than the depth of one of said registering grooves and greater than the depth of another of said registering grooves.

7. A case according to claim 6 including means for retaining said seal in said one registering groove upon installation such that the seal lies wholly within the one registering groove and releasing said seal in said one registering groove for movement in part into said another registering groove to seal between the upper and lower barrel halves along the horizontal midline.

8. A case according to claim 7 wherein said means includes a wax meltable at a temperature above ambient temperature and at or below turbine operating temperatures.

9. An inner compressor discharge case for a gas turbine, comprising:

a cylindrical barrel formed of upper and lower halves joined to one another at margins thereof along a horizontal midline to form a pair of diametrically spaced joints along opposite sides of the barrel, each of said margins having a groove extending generally parallel to an axis of the cylindrical barrel, the grooves of opposed margins of said halves on respective opposite sides of the barrel lying in registration with one another along the horizontal midline; and

a seal disposed in each pair of registering grooves;

each said seal including a metal plate having a pair of sealing surfaces for sealing against surfaces of said registering grooves, respectively, one of said sealing surfaces including an edge of said plate extending out of a plane containing said plate for sealing against a lateral surface of one of said registering grooves, another of said sealing surfaces including another edge of said plate having an arcuate portion for sealing against a base of another of said registering grooves.

10. A case according to claim 9 wherein each said plate is elongated in said registering grooves and lies in a plane generally tangential to the cylindrical barrel, each said plate in said registering grooves having a depth less than the distance between the bases of said registering grooves whereby the seal is at all times spaced from a base of one of said registering grooves.

11. A case according to claim 9 including means for retaining said seal in said one registering groove upon installation whereby the seal lies wholly within the one registering groove and releasing said seal in said one registering groove for movement in part into said another registering groove to seal between the upper and lower barrel halves along the horizontal midline.

12. A case according to claim 11 wherein said means includes a wax meltable at a temperature above ambient temperature and at or below turbine operating temperatures.

13. A method of locating a seal along registering faces of first and second mating parts of a gas turbine having an axis, comprising the steps of:

providing a first groove extending generally parallel to said axis and having a first depth in a registering face of said first part;

providing a second groove extending generally parallel to said axis and having a second depth in a registering face of said second part, the depth of said first groove being in excess of the depth of said second groove;

providing a seal having a depth equal to or less than the depth of said first groove and greater than the depth of said second groove;

retaining said seal in said first groove during installation of the seal and releasing the seal from said first groove, enabling the seal to locate in said first and second grooves, spanning the joint between the mating parts.

14. A method according to claim 13 including releasing the seal from said first groove in response to a temperature at the joint in excess of ambient temperature and at or below turbine operating temperatures.

15. A method according to claim 13 including disposing a substance in said first groove to retain said seal therein at ambient temperatures and to release the seal from said first groove in response to a temperature at the joint in excess of ambient temperature or at or below turbine operating temperatures.

16. A method according to claim 15 wherein said substance comprises a wax.

17. A method according to claim 13 wherein said seal includes a metal plate in a plane, the step of providing the seal including forming the plate with an edge extending out of the plane and another edge having an arcuate portion for sealing against a lateral surface of said first groove and against a base of said second groove, respectively.