GAS TURBINE NOZZLE SEALS FOR 2000 DEGREE F GAS CONTAINMENT

• US 20090322036A1
• Filed: 06/23/2009
• Published: 12/31/2009
• Est. Priority Date: 06/27/2008
• Status: Active Grant

• Current Assignee: Seal Science And Technology, LLC
• Original Assignee: Seal Science And Technology, LLC
• Inventors: Halling, Horace P.
• Granted Patent: US 8,104,772 B2
• Time in Patent Office: Days
• US Class Current: 277/434
• CPC Class Codes: F01D 11/005 Sealing means between non relatively rotating elements
• CPC Class Codes: F05D 2250/231 cylindrical
• CPC Class Codes: F05D 2250/232 conical
• CPC Class Codes: F05D 2250/292 tapered
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A seal for containment of fluids or gases during high temperature applications, separating a high pressure area on one side from a low pressure area on an opposite side, and formed to convert axial displacements into radial movements eliminating axial strains, having at least one engaging, conical ring structure with a tapering arcuate side facing radially away from the high pressure side. The conical ring structure has a side opposite the tapering side that is cylindrical, and a cylindrical diameter that is concentric with the arcuate side. The conical ring structure has an axial distal end with a larger diameter than its opposite end for engaging a flat annular surface on an adjacent structural member to form the seal. A heat-destructible wax spacer may be used for insertion within the clearance gap to locate the seal concentrically with the gland for ease of assembly.

Claims

1. A seal for containment of gases during ultra high temperature operations between gas turbine nozzles downstream of a combustion chamber, separating a high pressure area on one side from a low pressure area on an opposite side, said seal formed to convert axial displacements into radial movements thereby eliminating axial strains, including two engaging, conical ring structures, each comprising:

cross-sections with a tapering arcuate side facing radially away from said high pressure area; and

an axial distal end having a larger diameter than an opposite end for engaging a flat annular surface on an adjacent structural member.

2. The seal of claim 1 wherein each of said conical ring structures has a side opposite said tapering arcuate side that is cylindrical with a cylindrical diameter that is concentric with said arcuate side.

3. The seal of claim 1 wherein said arcuate side of said conical ring structure is dimensioned to engage a tapered sealing surface on said turbine nozzle segment.

4. The seal of claim 1 wherein said ultra high temperature applications comprise sealing in an environment having a temperature greater than or equal to 2000°

F.

5. The seal of claim 1 including having said axial distal end crowned and substantially perpendicular to said conical ring structure axis.

6. The seal of claim 1 including at least one heat-destructible, approximately cylindrical wax spacer concentric with said conical ring structure, and positioned adjacent said conical ring structure, opposite said tapering arcuate side, to aid in correct positioning during assembly for subsequent high temperature operation.

7. The seal of claim 6 including having said wax spacer inserted with said seal within a groove in said gas turbine nozzle segment.

8. The seal of claim 1 including having a sealing diameter to cross-section ratio for piston engine exhaust recirculation systems at least one order of magnitude lower than that of said turbine nozzle application.

9. A seal for containment of fluids, separating a high pressure area on one side from a low pressure area on an opposite side, said seal formed to convert axial displacements into radial movements thereby eliminating axial strains, including at least one conical ring structure comprising:

a cross-section with a tapering arcuate side facing radially away from said high pressure area;

an axial distal end having a larger diameter than an opposite end for engaging a flat annular surface on an adjacent structural member, wherein said axial distal end is crowned and substantially perpendicular to said conical ring structure axis; and

at least one heat-destructible, approximately cylindrical, wax spacer concentric with said conical ring structure, and positioned adjacent said conical ring structure, opposite said tapering arcuate side, to aid in positioning during high temperature application.

10. A seal for containing gases or fluids in a high pressure application, where there exists a high pressure area on one side of said seal, and a low pressure area on an opposite side of said seal, said seal formed to convert axial displacements into radial movements thereby eliminating axial strains, including at least one engaging, conical ring structure, comprising:

a cross-section with at least one tapering arcuate side facing radially away from said high pressure area; and

an axial distal end having a larger diameter than an opposite end for engaging a flat annular surface on an adjacent structural member.

11. The seal of claim 10 including two tapering arcuate sides, representing surfaces of said seal'"'"'s upper and conical side.

12. The seal of claim 11 wherein the side opposite said tapering arcuate conical side is cylindrical with a cylindrical diameter that is concentric with said arcuate conical side.

13. The seal of claim 10 including having said axial distal end crowned and substantially perpendicular to said at least one, engaging conical ring structure axis.

14. The seal of claim 10 wherein said high pressure application includes automotive applications or aerospace applications.

15. The seal of claim 14 wherein said automotive applications include using said seal within a piston-engine cylinder wall.