Damping design to reduce vibratory response in the turbine exhaust manifold centerbody

Patent metadata

Field	Value
Publication number	US-9695713-B2
Application number	US-201514619637-A
Country	US
Kind code	B2
Filing date	Feb 11, 2015
Priority date	Sep 15, 2014
Publication date	Jul 4, 2017
Grant date	Jul 4, 2017

Abstract

Disclosed are a system for damping vibrations of a gas turbine exhaust and a method to damp vibrations of a gas turbine exhaust. The system 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 clamped by a plurality of studs.

First claim

What is claimed is:

1. A system for damping vibrations of a gas turbine exhaust, comprising:
a turbine exhaust manifold connected to a turbine exhaust cylinder establishing a fluid flow path, the fluid flow path including an inner and an outer flow path;
a plurality of studs coupled to the inner surface of the inner flow path and oriented radially inward;
a damping blanket effective to damp vibrational amplitude; and
a constraining layer clamped to the damping blanket by the studs,
wherein the constraining layer is clamped with sufficient clamping pressure to provide frictional damping of vibrations of the gas turbine exhaust.

2. The system as claimed in claim 1 , further comprising a mesh layer disposed between an inner surface of the inner flow path and the damping blanket effective to provide additional frictional damping.

3. The system as claimed in claim 2 , wherein the thickness of the mesh layer is in a range of 0.5 mm to 2.0 mm.

4. The system as claimed in claim 2 , wherein the mesh layer includes a material including a bidirectional overlap on the surface or a material that is woven.

5. The system as claimed in claim 2 , wherein the damping blanket comprises insulation,
wherein an outermost portion of the insulation is coupled to the mesh layer and an innermost portion of the insulation is coupled to the constraining layer.

6. The system as claimed in claim 5 , wherein the constraining layer comprises a backing plate sufficient to compress the insulation to provide effective damping.

7. The system as claimed in claim 6 , wherein the backing plate comprises a plurality of panels positioned radially inward of the damping blanket on the inner surface of the inner flow path and around a plurality of struts.

8. The system as claimed in claim 7 , wherein the plurality of panels are spaced in order to damp panel modes generated in the inner flow path.

9. The system as claimed in claim 6 , wherein the thickness of the backing plate is in a range of 3.0 mm to 13 mm.

10. The system as claimed in claim 9 , wherein the backing plate comprises steel.

11. The system as claimed in claim 6 ,
wherein each stud includes a welded radial rod secured by a hex nut and a washer,
wherein a first end of the welded radial rod is welded to the inner surface of the inner flow path, and
wherein a second end of the welded radial rod protrudes through the backing plate.

12. The system as claimed in claim 11 ,
wherein a portion of the welded radial threaded rod includes a semicircular cross section,
wherein the welded radial threaded rod is secured to the backing pate with a corresponding semi-circular washer and a hex nut.

13. The system as claimed in claim 1 , wherein the plurality of studs are spaced effective to maintain attachment while providing effective damping of vibrations of the turbine exhaust manifold.

14. A method to damp vibrations of a gas turbine exhaust, comprising:
disposing a damping blanket against a fluid flow path of the gas turbine, the fluid flow path including an inner and an outer flow path;
coupling a plurality of studs to an inner surface of the inner flow path such that the damping blanket is arranged on the plurality of studs; and
clamping a constraining layer with sufficient clamping pressure to the damping blanket with the plurality of studs providing frictional damping of vibrations of the gas turbine exhaust,
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.

15. The method as claimed in claim 14 , wherein the coupling further comprises placing each of the plurality of studs at locations on the inner surface of the inner flow path of the gas turbine away from heat affected zones due to an existing weld.

16. The method as claimed in claim 15 , wherein each stud includes a welded radial rod and wherein each radial threaded rod is welded to the inner surface of the inner flow path.

17. The method as claimed in claim 16 ,
wherein the clamping further comprises welding the radial rod to the flow path, and securing the welded radial rod by a hex nut and a washer.

18. The method as claimed in claim 14 , further comprising determining placement of the constraining layer based on calculations of predicted displacement, and
wherein the constraining layer further comprises a plurality of backing panels.

19. The method as claimed in claim 17 , further comprising compressing the insulation to provide effective damping by the constraining layer.

20. The method as claimed in claim 14 , further comprising disposing a mesh layer between an inner surface of the inner flow path and the damping blanket, and
wherein the mesh layer is effective to provide additional frictional damping.

Assignees

• Siemens Energy Inc

Inventors

• Eshak Daniel M
• Shteyman Yevgeniy P
• Giaimo John
• Obranic Jr George J
• Bosu Sudeep

Classifications

• F01D25/04

  Antivibration arrangements · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F01D25/164

  Flexible supports; Vibration damping means associated with the bearing · CPC title

• F05D2250/281

  threaded · CPC title

• F01D25/30 Primary

  Exhaust heads, chambers, or the like · CPC title