Turbine exhaust cylinder/turbine exhaust manifold bolted full span turbine exhaust flaps

Patent metadata

Field	Value
Publication number	US-2016208642-A1
Application number	US-201514945857-A
Country	US
Kind code	A1
Filing date	Nov 19, 2015
Priority date	Jan 16, 2015
Publication date	Jul 21, 2016
Grant date	—

Abstract

A system and method to minimize flow induced vibration in a gas turbine exhaust is provided. The system includes a turbine exhaust manifold connected to a turbine exhaust cylinder establishing a fluid flow path, the fluid flow path bounded radially outward by an outer cylindrical surface and bounded radially inward by an inner cylindrical surface. At least one tangential strut is arranged between the outer cylindrical surface and the inner cylindrical surface. A trailing edge full span flap is removable secured behind the trailing edge of the tangential strut in a fluid flow direction and extending between the outer cylindrical surface and the inner cylindrical surface where the full span flap minimizes vortex shedding of the fluid flow from the tangential strut.

First claim

What is claimed is:

1 . A system to minimize flow induced vibration in a gas turbine exhaust, comprising:
a turbine exhaust manifold connected to a turbine exhaust cylinder establishing a fluid flow path, the fluid flow path bounded radially outward by an outer cylindrical surface and bounded radially inward by an inner cylindrical surface; a tangential strut arranged between the outer cylindrical surface and the inner cylindrical surface; and a trailing edge full span flap removably secured behind the trailing edge of the tangential strut in a fluid flow direction and extending between the outer cylindrical surface and the inner cylindrical surface, wherein the full span flap is configured to minimize vortex shedding of the fluid flow from the tangential strut.

2 . The system as claimed in claim 1 ,
wherein trailing edge full span flap includes a hollow rectangular box shape including two radial edges and two axial edges, and wherein the radial edges, extending radially with respect to a rotor centerline, of the trailing edge full span flap are rounded to promote a smooth aerodynamic fluid flow.

3 . The system as claimed in claim 2 , wherein within the hollow rectangular box shape a radially extending stiffening rib is disposed.

4 . The system as claimed in claim 2 ,
wherein the trailing edge full span flap includes a first axial edge and a second axial edge, the first axial edge extending axially with respect to the rotor centerline along the outer cylindrical surface and the second axial edge extending axially with respect to the rotor centerline along the inner cylindrical surface, and wherein the first axial edge is longer than the second axial edge.

5 . The system as claimed in claim 4 ,
wherein the first and second axial edges are slideably attached to the outer cylindrical surface and the inner cylindrical surface, respectively.

6 . The system as claimed 5 , wherein the first and second axial edges are slideably attached to the outer cylindrical surface and the inner cylindrical surface, respectively, using a flexible attachment bracket.

7 . The system as claimed in claim 6 ,
wherein the flexible attachment bracket includes a plurality of elongated holes, a first plurality of elongated holes and a second plurality of elongated holes through which a plurality of corresponding fasteners are inserted and secured in order to attach the full span flap to the outer cylindrical surface or the inner cylindrical surface.

8 . The system as claimed in claim 7 ,
wherein a first plurality of fasteners are each inserted through the first plurality of elongated holes, through a hole in the wall thickness of the full span flap and through a hole in a nut plate, wherein each fastener is secured to the nut plate with a securing means.

9 . The system as claimed in claim 8 , wherein the nut plate includes a groove such that the securing means is prevented from antirotating.

10 . The system as claimed in claim 7 , wherein the plurality of fasteners slide within the corresponding elongated hole to accommodate the differential thermal growth of the full span flap, the outer cylindrical surface, and the inner cylindrical surface.

11 . The system as claimed in claim 7 , wherein the first plurality of elongated holes enable correct positioning of the full span flap within the fluid flow path by allowing for vertical adjustability of the full span flap.

12 . The system as claimed in claim 7 , wherein each fastener protrudes through the corresponding elongated hole of the second plurality of elongated holes and is secured to the inner cylindrical surface or the outer cylindrical surface with a spherical joint,
wherein the spherical joint accommodates thermal distortion of the inner cylindrical surface or the outer cylindrical surface such that each fastener is positioned normally to the fluid flow path.

13 . A method to minimize flow induced vibration in a gas turbine exhaust system, comprising:
disposing a full span flap between an outer cylindrical surface and an inner cylindrical surface of the fluid flow path; and removably securing the full span flap behind a trailing edge of a tangential strut by coupling the full span flap to the outer cylindrical surface and the inner cylindrical surface using a plurality of flexible attachment brackets, wherein the flow path is bounded radially outward by an outer cylindrical surface and bounded radially inward by an inner cylindrical surface, wherein the full span flap is configured to minimize vortex shedding of the fluid flow from the tangential strut.

14 . The method as claimed in claim 13 comprising:
providing the full span flap with a hollow rectangular box shape including two rounded radial edges and two axial edges,
wherein each rounded radial edge extends radially, with respect to the rotor centerline, from the outer cylindrical surface to the inner cylindrical surface, and
wherein each axial edge extends axially, with respect to the rotor centerline, along the inner cylindrical surface or the outer cylindrical surface.

15 . The method as claimed in claim 14 , wherein the two radial edges are rounded to promote a smooth aerodynamic fluid flow.

16 . The method as claimed in claim 13 , wherein the securing includes inserting a plurality of fasteners through a plurality of corresponding elongated holes within the flexible attachment bracket and securing the plurality of fasteners with a securing means such that a first plurality of fasteners attaches the flexible attachment bracket to the full span flap and a second plurality of fasteners attaches the flexible attachment bracket to the outer cylindrical surface or the inner cylindrical surface.

17 . The method as claimed in claim 16 , wherein the plurality of fasteners slide within the elongated hole to accommodate the differential thermal growth of the full span flap, the outer cylindrical surface, and the inner cylindrical surface.

18 . The method as claimed in claim 16 ,
wherein a nut plate is positioned on an opposing surface to the surface of full span flap to which the flexible attachment bracket abuts and/or to an opposing surface to the surface of the inner cylindrical surface or the outer cylindrical surface to which the flexible attachment bracket abuts, wherein the fastener protrudes through the nut plate, and wherein a securing means abuts the nut plate and secures the fastener to the nut plate.

19 . The method as claimed in claim 18 , wherein the securing includes disposing a spherical joint on the opposing surface of the outer cylindrical surface or the inner cylindrical surface through which the fastener protrudes,
wherein the spherical joint is used accommodate for distortion in the flow path such that each fastener is positioned normally to the fluid flow path.

20 . The method as claimed in claim 18 , comprising welding the plate to the opposing surface and the securing means to the plate.

Assignees

• Siemens Energy Inc

Inventors

• Shteyman Yevgeniy P
• Giaimo John
• Tindell Randy

Classifications

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2230/232

  by welding · CPC title

• F01D25/04 Primary

  Antivibration arrangements · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F05D2220/32

  in gas turbines · CPC title