Gas turbine shroud support apparatus

• US 8,047,773 B2
• Filed: 08/23/2007
• Issued: 11/01/2011
• Est. Priority Date: 08/23/2007
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (GE Vernova, Inc.)
• Original Assignee: General Electric Company
• Inventors: Corman, Gregory Scot, Roberts, Herbert Chidsey III, Bruce, Kevin Leon, Nimmer, Ronald Phillip, Johnson, Curtis Alan, Cairo, Ronald Ralph
• Primary Examiner(s): EDGAR, RICHARD A
• Application Number:
  US11/844,046
• Publication Number:
  US 20090053050A1
• Time in Patent Office: 1,531 Days
• Field of Search: 415/173.4, 415/173.3, 415/174.1, 415/174.2
• US Class Current: 415/173.3
• CPC Class Codes: F01D 25/04 Antivibration arrangements
• CPC Class Codes: F01D 25/246 Fastening of diaphragms or stator-rings
• CPC Class Codes: F05D 2250/41 with one degree of freedom
• CPC Class Codes: F05D 2260/96 Preventing, counteracting or reducing vibration or noise

Abstract

A support apparatus for a gas turbine shroud is disclosed. The apparatus includes an outer shroud block having a coupling connectable to a casing of the gas turbine and a shroud component having a forward flange and an aft flange. The shroud component is attached to the outer shroud block via the forward flange and the aft flange. The apparatus further includes a damper disposed between the outer shroud block and the shroud component and a biasing element disposed within the outer shroud block. A translational degree of freedom between the damper and the outer shroud block defines a direction of motion of the damper. The biasing element is in operable connection between the outer shroud block and the shroud component via the damper, a bias force of the biasing element directed along the direction of motion of the damper.

Claims

1. A support apparatus for a shroud of a gas turbine, the gas turbine comprising a rotating shaft defining a radial direction perpendicular thereto, the apparatus comprising:

an outer shroud block comprising a coupling connectable to a casing of the gas turbine;

a shroud component comprising a forward flange and an aft flange, the shroud component attached to the outer shroud block via the forward flange and the aft flange;

a damper disposed between the outer shroud block and the shroud component with a translational degree of freedom between the damper and the outer shroud block that defines a direction of motion of the damper, the direction of motion forming an angle greater than zero degrees relative to the radial direction of the gas turbine;

a biasing element disposed within the outer shroud block, the biasing element in operable connection between the outer shroud block and the shroud component via the damper, a bias force of the biasing element directed along the direction of motion of the damper;

a first pin extendible through an aperture in the forward flange or the aft flange, and

a deformation interface between a head of the first pin and the outer shroud block.

2. The shroud support apparatus of claim 1, wherein:

the biasing element comprises a spring.

3. The shroud support apparatus of claim 1, wherein:

the outer shroud block comprises a first portion proximate the biasing element and a second portion proximate the shroud; and

a component of the bias force of the biasing element biases an aft end of the damper toward the second portion of the outer shroud block.

4. The shroud support apparatus of claim 3, wherein:

the aft end of the damper comprises a sealing surface in contact with the outer shroud block.

5. The shroud support apparatus of claim 1, wherein:

the damper comprises a guide surface;

the outer shroud block comprises a guiding surface; and

the guiding surface mates with the guide surface, thereby defining the translational degree of freedom of the damper relative to the outer shroud block.

6. The shroud support apparatus of claim 5, wherein:

the guide surface and the guiding surface each comprise complimentary geometry that prevents rotation of the damper relative to the outer shroud block.

7. The shroud support apparatus of claim 5, wherein:

the guide surface comprises four sides.

8. The shroud support apparatus of claim 1, wherein:

the outer shroud block comprises a cooling passage in fluid communication with the biasing element; and

the apparatus further comprises a bleed plug disposed within the cooling passage, the bleed plug comprising a surface defining an opening passing through the bleed plug.

9. The shroud support apparatus of claim 1, wherein:

the shroud component is a stationary ceramic shroud component for a turbine bucket row of the gas turbine.

10. The shroud support apparatus of claim 9, wherein:

the stationary ceramic shroud component comprises a surface adjacent the turbine bucket row, the surface comprising a raised pattern.

11. The shroud support apparatus of claim 10, wherein:

the raised pattern comprises abradable ceramic matrix composite material.

12. The shroud support apparatus of claim 9, wherein:

the stationary ceramic shroud component comprises ceramic matrix composite material.

13. The shroud support apparatus of claim 9, wherein:

the stationary ceramic shroud component is one of a plurality of stationary ceramic shroud components; and

the damper is one of a plurality of dampers, each damper of the plurality of dampers in contact with a respective one of the plurality of stationary ceramic shroud components.

14. The shroud support apparatus of claim 13, wherein:

each damper of the plurality of dampers comprises a seal retention interface; and

the apparatus further comprises a seal disposed within each of two adjacent seal retention interfaces of two adjacent dampers of the plurality of dampers.

15. The shroud support of claim 13, wherein:

one of the plurality of stationary ceramic shroud components is disposed adjacent another of the plurality of stationary ceramic shroud components, thereby defining a first gap therebetween;

one of the plurality of dampers is disposed adjacent another of the plurality of dampers, thereby defining a second gap therebetween, the one and the another of the plurality of dampers are in contact with the respective one and the another stationary ceramic shrouds of the plurality of stationary ceramic shrouds; and

the first gap is circumferentially offset relative to the second gap, thereby defining a tortuous flow path.

16. The shroud support of claim 1, wherein the head of the first pin and the outer shroud block each comprise complimentary geometry that prevents rotation of the first pin relative to the outer shroud block.

17. The shroud support of claim 1, wherein:

the damper comprises a first surface;

the shroud component comprises a second surface parallel and adjacent to the first surface; and

the first surface contacts the second surface.

18. The shroud support of claim 17, wherein:

the first surface comprises a perimeter of the damper; and

substantially all of an area of the first surface defined by the perimeter of the damper contacts the second surface.

19. A support apparatus for a shroud of a gas turbine, the gas turbine comprising a rotating shaft defining a radial direction perpendicular thereto, the apparatus comprising:

an outer shroud block comprising a coupling connectable to a casing of the gas turbine;

a melt-infiltrated ceramic matrix composite inner shroud component comprising a forward flange and an aft flange, the melt-infiltrated ceramic matrix composite inner shroud component shroud component attached to the outer shroud block via the forward flange and the aft flange;

a damper disposed between the outer shroud block and the melt-infiltrated ceramic matrix composite inner shroud component with a translational degree of freedom between the damper and the outer shroud block that defines a direction of motion of the damper, the direction of motion forming an angle greater than zero degrees relative to the radial direction of the gas turbine; and

a biasing element disposed within the outer shroud block, the biasing element in operable connection between the outer shroud block and the melt-infiltrated ceramic matrix composite inner shroud component via the damper, a bias force of the biasing element directed along the direction of motion.

20. A support apparatus for a shroud of a gas turbine, the gas turbine comprising a rotating shaft defining a radial direction perpendicular thereto, the apparatus comprising:

an outer shroud block comprising a coupling connectable to a casing of the gas turbine;

a shroud component comprising a forward flange and an aft flange, the shroud component attached to the outer shroud block via the forward flange and the aft flange;

a damper disposed between the outer shroud block and the shroud component with a translational degree of freedom between the damper and the outer shroud block that defines a direction of motion of the damper, the direction of motion forming an angle greater than zero degrees relative to the radial direction of the gas turbine;

a biasing element disposed within the outer shroud block, the biasing element in operable connection between the outer shroud block and the shroud component via the damper, a bias force of the biasing element directed along the direction of motion of the damper;

a first pin extendible through an aperture in the aft flange or the forward flange, the first pin comprising a retention aperture; and

a retention pin disposed within the retention aperture of the first pin.

21. A support apparatus for a shroud of a gas turbine, the gas turbine comprising a rotating shaft defining a radial direction perpendicular thereto, the apparatus comprising:

an outer shroud block comprising a coupling connectable to a casing of the gas turbine;

a shroud component comprising a forward flange and an aft flange, the shroud component attached to the outer shroud block via the forward flange and the aft flange;

a damper disposed between the outer shroud block and the shroud component with a translational degree of freedom between the damper and the outer shroud block that defines a direction of motion of the damper, the direction of motion forming an angle greater than zero degrees relative to the radial direction of the gas turbine;

a biasing element disposed within the outer shroud block, the biasing element in operable connection between the outer shroud block and the shroud component via the damper, a bias force of the biasing element directed along the direction of motion of the damper;

a first pin extendible through an aperture in the forward flange of the ceramic component,

a deformation interface between a head of the first pin and the outer shroud block;

a second pin extendible through an aperture in the aft flange or the forward, the second pin comprising a retention aperture; and

a retention pin disposed within the retention aperture of the second pin.