Turbine exhaust cylinder/ turbine exhaust manifold bolted stiffening ribs

Patent metadata

Field	Value
Publication number	US-2016201506-A1
Application number	US-201514596684-A
Country	US
Kind code	A1
Filing date	Jan 14, 2015
Priority date	Jan 14, 2015
Publication date	Jul 14, 2016
Grant date	—

Abstract

Disclosed are a casing arrangement and a method to reduce vibrations in a gas turbine casing. The casing arrangement includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A damping blanket damps the vibrations and is coupled to a surface of the inner flow path via a constraining layer.

First claim

What is claimed is:

1 . A casing arrangement to reduce operative vibrations in a gas turbine, comprising:
a turbine exhaust cylinder; a turbine exhaust manifold connected to the turbine exhaust cylinder establishing a fluid flow path, the fluid flow path including an inner and an outer flow path; a damping blanket effective to damp vibrational amplitude; and a constraining layer effective to keep the damping blanket in contact with the inner flow path.

2 . The casing arrangement as claimed in claim 1 , wherein the damping blanket further comprises a plurality of layers of insulation including an outermost layer and an innermost layer.

3 . The casing arrangement as claimed in claim 2 , wherein the outermost layer is coupled to an inner surface of the inner flow path.

4 . The casing arrangement as claimed in claim 2 , wherein the constraining layer comprises a plate and a plurality of stiffening ribs and is coupled to the innermost layer such that the damping blanket is disposed between the surface of the inner flow path and the constraining layer.

5 . The casing arrangement as claimed in claim 4 ,
wherein a bushing is disposed within an opening in the damping blanket, wherein a welded radial threaded rod is inserted within the opening in the bushing, and wherein the bushing ensures contact between the stiffening rib and the flow path.

6 . The casing arrangement as claimed in claim 5 ,
wherein a portion of the welded radial threaded rod includes a d-shaped [semi-circular] cross section, and wherein the welded radial threaded rod is secured to the stiffening rib with a corresponding semi-circular washer and a hex nut.

7 . The casing arrangement as claimed in claim 5 , wherein the plate is clamped to the insulation by the secured welded radial threaded rod which provides sufficient clamping pressure to provide frictional damping of vibrations of the turbine exhaust cylinder and turbine exhaust manifold.

8 . The casing arrangement as claimed in claim 7 ,
wherein the damping blanket combined with the secured welded radial rod creates a frictional damper, and wherein the frictional damper compresses the plurality of layers of insulation producing heat.

9 . The casing arrangement as claimed in claim 4 , wherein each stiffening rib comprises an arcuate segment including a plurality of attachment holes.

10 . The casing arrangement as claimed in claim 9 , wherein each of the plurality of stiffening ribs are attached circumferentially.

11 . The casing arrangement as claimed in claim 10 , wherein a bolted connection plate is disposed between adjacent stiffening ribs creating a continuous stiffening hoop.

12 . The casing arrangement as claimed in claim 11 , wherein a plurality of continuous stiffening hoops are spaced axially along the inner surface of the inner flow path.

13 . The casing arrangement as claimed in claim 12 , wherein each stiffening rib includes a T-shaped cross section.

14 . The casing arrangement as claimed in claim 12 , wherein each stiffening rib includes an L-shaped cross section.

15 . A method to reduce vibrations in a gas turbine casing, comprising:
disposing a damping blanket against a flow path of the gas turbine, the flow path defined by an inner and outer flow path; and coupling a plurality of stiffening ribs to the damping blanket, wherein a turbine exhaust cylinder and a turbine exhaust manifold connected to the turbine exhaust cylinder establish the flow path, wherein the flow path is bounded radially inward by an outer surface of the inner flow path and radially outward by an inner surface of the outer flow path, and wherein vibrations in a turbine exhaust cylinder and turbine exhaust manifold are reduced by compression of the damping blanket and the stiffness of the plurality of the stiffening ribs.

16 . The method as claimed in claim 15 , wherein the damping blanket further comprises a plurality of layers of insulation including an outermost layer and an innermost layer.

17 . The method as claimed in claim 16 , wherein the disposing further comprising coupling the outermost layer to an inner surface of the inner flow path such that the layers of insulation are circumferentially disposed against the inner surface of the inner flow path.

18 . The method as claimed in claim 17 , wherein the plurality of stiffening ribs are coupled to the innermost layer such that the damping blanket is disposed between a surface of the inner flow path and the plurality of the stiffening ribs.

19 . The method as claimed in claim 18 , further comprising disposing a bushing within an opening in the damping blanket, and
inserting a semicircular welded radial threaded rod within the opening in the bushing.

20 . The method as claimed in claim 19 , wherein the welded radial threaded rod is secured to the stiffening rib with a semicircular washer and a hex nut.

Assignees

• Siemens Energy Inc

Inventors

• Shteyman Yevgeniy P
• Giaimo John
• Eshak Daniel M
• Heylmun Thomas

Classifications

• F05D2230/644

  for adjusting the position or the alignment, e.g. wedges or eccenters · CPC title

• F01D25/30

  Exhaust heads, chambers, or the like · CPC title

• F01D25/162

  Bearing supports · CPC title

• F01D25/04 Primary

  Antivibration arrangements · CPC title

• F05D2220/32

  in gas turbines · CPC title