U.S. patent application number 13/682965 was filed with the patent office on 2014-05-22 for super telescoping cross-fire tube and method of assembling a combustor structure.
This patent application is currently assigned to GENERAL ELECTRIC COMPANY. The applicant listed for this patent is GENERAL ELECTRIC COMPANY. Invention is credited to Joel Russell Cloninger, Patrick Benedict Melton, Lucas John Stoia, James Harold Westmoreland.
Application Number | 20140137536 13/682965 |
Document ID | / |
Family ID | 50625744 |
Filed Date | 2014-05-22 |
United States Patent
Application |
20140137536 |
Kind Code |
A1 |
Cloninger; Joel Russell ; et
al. |
May 22, 2014 |
SUPER TELESCOPING CROSS-FIRE TUBE AND METHOD OF ASSEMBLING A
COMBUSTOR STRUCTURE
Abstract
A super-telescoping cross-fire tube includes a cross-fire tube
including a first portion and a second portion in mating
engagement, the cross-fire tube extending from a first end region
to a second end region for fluidly connecting a combustor chamber
and an adjacent combustor chamber. Also included is an outer shield
spaced radially outwardly and surrounding at least a portion of the
cross-fire tube. Further included is a spring extending from
proximate the first end region to the second end region and
disposed between the cross-fire tube and the outer shield, wherein
the cross-fire tube is telescopingly moveable between a first
position and a second position.
Inventors: |
Cloninger; Joel Russell;
(Anderson, SC) ; Melton; Patrick Benedict; (Horse
Shoe, NC) ; Stoia; Lucas John; (Taylors, SC) ;
Westmoreland; James Harold; (Greer, SC) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
GENERAL ELECTRIC COMPANY |
Schenectady |
NY |
US |
|
|
Assignee: |
GENERAL ELECTRIC COMPANY
Schenectady
NY
|
Family ID: |
50625744 |
Appl. No.: |
13/682965 |
Filed: |
November 21, 2012 |
Current U.S.
Class: |
60/39.37 |
Current CPC
Class: |
F23R 3/48 20130101 |
Class at
Publication: |
60/39.37 |
International
Class: |
F23R 3/48 20060101
F23R003/48 |
Claims
1. A super-telescoping cross-fire tube comprising: a cross-fire
tube including a first portion and a second portion in mating
engagement, the cross-fire tube extending from a first end region
to a second end region for fluidly connecting a combustor chamber
and an adjacent combustor chamber; an outer shield spaced radially
outwardly and surrounding at least a portion of the cross-fire
tube; and a spring extending from proximate the first end region to
the second end region and disposed between the cross-fire tube and
the outer shield, wherein the cross-fire tube is telescopingly
moveable between a first position and a second position.
2. The super-telescoping cross-fire tube of claim 1, further
comprising a first collar operably coupled to a combustor assembly
component, the first collar including at least one anti-rotation
component for engaging a corresponding anti-rotation surface
proximate at least one of the first end region and the second end
region of the cross-fire tube.
3. The super-telescoping cross-fire tube of claim 2, wherein the at
least one anti-rotation component comprises a non-planar geometry
and the corresponding anti-rotation surface comprises a
corresponding non-planar geometry.
4. The super-telescoping cross-fire tube of claim 2, wherein the
first collar is operably coupled to the combustor assembly
component proximate the first end region, wherein the first collar
comprises a plurality of cooling holes for cooling the first end
region.
5. The super-telescoping cross-fire tube of claim 4, further
comprising a second collar operably coupled to an adjacent
combustor assembly component proximate the second end region of the
cross-fire tube.
6. The super-telescoping cross-fire tube of claim 2, wherein the at
least one anti-rotation component comprises a plurality of conical
regions, wherein the corresponding anti-rotation surface comprises
a plurality of corresponding conical regions.
7. The super-telescoping cross-fire tube of claim 2, wherein the
first collar is welded to the combustor assembly component.
8. The super-telescoping cross-fire tube of claim 2, wherein the
combustor assembly component comprises at least one of a combustor
liner, a sleeve surrounding the combustor liner, and an air shield
surrounding the sleeve.
9. A combustor structure for a gas turbine engine comprising: a
combustor assembly and an adjacent combustor assembly, the
combustor assembly comprising a combustor chamber, the adjacent
combustor assembly comprising an adjacent combustor chamber; a
first collar operably coupled to the combustor assembly; a
cross-fire tube extending from a first end region disposed adjacent
the first collar to a second end region disposed proximate the
adjacent combustor assembly; and a spring extending from proximate
the first end region to the second end region and disposed between
the cross-fire tube and an outer shield surrounding at least a
portion of the cross-fire tube.
10. The combustor structure of claim 9, wherein the cross-fire tube
comprises a first portion and a second portion in mating
engagement, the cross-fire tube telescopingly moveable between a
first extended position and a second compressed position.
11. The combustor structure of claim 9, wherein the first collar
comprises at least one anti-rotation component for engaging a
corresponding anti-rotation surface proximate the first end
region.
12. The combustor structure of claim 11, wherein the at least one
anti-rotation component comprises a non-planar geometry and the
corresponding anti-rotation surface comprises a corresponding
non-planar geometry.
13. The combustor structure of claim 9, wherein the first collar
comprises a plurality of cooling holes for cooling the first end
region.
14. The combustor structure of claim 9, further comprising a second
collar operably coupled to the adjacent combustor assembly
proximate the second end region of the cross-fire tube.
15. The combustor structure of claim 11, wherein the at least one
anti-rotation component comprises a plurality of conical regions,
wherein the corresponding anti-rotation surface comprises a
plurality of corresponding conical regions.
16. The combustor structure of claim 9, wherein the first collar is
welded to the combustor assembly.
17. The combustor structure of claim 9, wherein the first collar is
welded to at least one of a combustor liner, a sleeve surrounding
the combustor liner, and an air shield surrounding the sleeve.
18. A method of assembling a combustor structure comprising:
inserting a first portion of a cross-fire tube into a portion of a
combustor assembly; rotating the first portion of the cross-fire
tube to align an anti-rotation surface of the first portion with a
corresponding anti-rotation feature of a first collar operably
coupled to the combustor assembly; matably engaging a second
portion of the cross-fire tube with the first portion, wherein a
spring is positioned from the first portion to the second portion;
and compressing the cross-fire tube from a first position to a
second position providing clearance for insertion of an adjacent
combustor assembly into the combustor structure.
19. The method of claim 18, further comprising mechanically
fastening the first portion to the combustor assembly.
20. The method of claim 18, further comprising extending the
cross-fire tube to the first position subsequent to insertion of
the adjacent combustor assembly.
Description
BACKGROUND OF THE INVENTION
[0001] The subject matter disclosed herein relates to gas turbine
systems, and more particularly to a cross-fire tube, as well as a
method of assembling a combustor structure.
[0002] Adjacent combustors of a gas turbine engine are typically
connected by a cross-fire tube to ensure substantially simultaneous
ignition and equalized pressure in all combustor chambers of the
gas turbine engine. The cross-fire tube is typically coupled to the
adjacent combustors by a variety of retention devices, including
clips, for example. Geometry constraints and spatial limitations
may hinder the ability to employ such retention devices.
Additionally, the adjacent combustors may be assembled as a module
that is inserted as a whole into a combustor structure. Assembly in
this manner may limit the retention methods that are commonly
required for cross-fire tubes having a relatively rigid
construction or one of limited flexibility to accommodate the
insertion of the module into the combustor structure, as at least a
portion of the cross-fire tube is typically disposed in the space
that is to receive the module. Furthermore, installation of the
cross-fire tube requires proper positioning of the cross-fire tube,
relative to other components, with the positioning left to an
installation operator's discretion or manipulating, thereby often
leading to human error.
BRIEF DESCRIPTION OF THE INVENTION
[0003] According to one aspect of the invention, a
super-telescoping cross-fire tube includes a cross-fire tube
including a first portion and a second portion in mating
engagement, the cross-fire tube extending from a first end region
to a second end region for fluidly connecting a combustor chamber
and an adjacent combustor chamber. Also included is an outer shield
spaced radially outwardly and surrounding at least a portion of the
cross-fire tube. Further included is a spring extending from
proximate the first end region to the second end region and
disposed between the cross-fire tube and the outer shield, wherein
the cross-fire tube is telescopingly moveable between a first
position and a second position.
[0004] According to another aspect of the invention, a combustor
structure for a gas turbine engine includes a combustor assembly
and an adjacent combustor assembly, the combustor assembly
comprising a combustor chamber, the adjacent combustor assembly
comprising an adjacent combustor chamber. Also included is a first
collar operably coupled to the combustor assembly. Further included
is a cross-fire tube extending from a first end region disposed
adjacent the first collar to a second end region disposed proximate
the adjacent combustor assembly. Yet further included is a spring
extending from proximate the first end region to the second end
region and disposed between the cross-fire tube and an outer shield
surrounding at least a portion of the cross-fire tube.
[0005] According to yet another aspect of the invention, a method
of assembling a combustor structure is provided. The method
includes inserting a first portion of a cross-fire tube into a
portion of a combustor assembly. Also included is rotating the
first portion of the cross-fire tube to align an anti-rotation
surface of the first portion with a corresponding anti-rotation
feature of a first collar operably coupled to the combustor
assembly. Further included is matably engaging a second portion of
the cross-fire tube with the first portion, wherein a spring is
positioned from the first portion to the second portion. Yet
further included is compressing the cross-fire tube from a first
position to a second position providing clearance for insertion of
an adjacent combustor assembly into the combustor structure.
[0006] These and other advantages and features will become more
apparent from the following description taken in conjunction with
the drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
[0007] The subject matter, which is regarded as the invention, is
particularly pointed out and distinctly claimed in the claims at
the conclusion of the specification. The foregoing and other
features, and advantages of the invention are apparent from the
following detailed description taken in conjunction with the
accompanying drawings in which:
[0008] FIG. 1 is a schematic illustration of a gas turbine
system;
[0009] FIG. 2 is a perspective, partial cross-sectional view of a
combustor structure;
[0010] FIG. 3 is a perspective view of a cross-fire tube of the
combustor structure;
[0011] FIG. 4 is a perspective view of a collar of the cross-fire
tube;
[0012] FIG. 5 is cross-sectional view of an end region of the
cross-fire tube;
[0013] FIG. 6 is a partial cross-sectional view of a portion of the
cross-fire tube engaged with the collar;
[0014] FIG. 7 is a perspective view of the cross-fire tube
according to another aspect of the invention;
[0015] FIG. 8 is a perspective view of a mechanical fastener for
securing the cross-fire tube;
[0016] FIG. 9 is a partial cross-sectional view of the cross-fire
tube in a compressed condition; and
[0017] FIG. 10 is a flow diagram illustrating a method of
assembling a combustor structure.
[0018] The detailed description explains embodiments of the
invention, together with advantages and features, by way of example
with reference to the drawings.
DETAILED DESCRIPTION OF THE INVENTION
[0019] Referring to FIG. 1, a gas turbine engine 10 constructed in
accordance with an exemplary embodiment of the present invention is
schematically illustrated. The gas turbine engine 10 includes a
compressor 12 and a plurality of combustor assemblies arranged in a
can annular array, one of which is indicated at 14. As shown, the
combustor assembly 14 includes an endcover assembly 16 that seals,
and at least partially defines, a combustor chamber 18. A plurality
of nozzles 20-22 are supported by the endcover assembly 16 and
extend into the combustor chamber 18. The nozzles 20-22 receive
fuel through a common fuel inlet (not shown) and compressed air
from the compressor 12. The fuel and compressed air are passed into
the combustor chamber 18 and ignited to form a high temperature,
high pressure combustion product or air stream that is used to
drive a turbine 24. The turbine 24 includes a plurality of stages
26-28 that are operationally connected to the compressor 12 through
a compressor/turbine shaft 30 (also referred to as a rotor).
[0020] In operation, air flows into the compressor 12 and is
compressed into a high pressure gas. The high pressure gas is
supplied to the combustor assembly 14 and mixed with fuel, for
example natural gas, fuel oil, process gas and/or synthetic gas
(syngas), in the combustor chamber 18. The fuel/air or combustible
mixture ignites to form a high pressure, high temperature
combustion gas stream. In any event, the combustor assembly 14
channels the combustion gas stream to the turbine 24 which converts
thermal energy to mechanical, rotational energy.
[0021] Referring now to FIG. 2, as noted above, a can annular array
of combustor assemblies is arranged in a circumferentially spaced
manner about an axial centerline of the gas turbine engine 10. For
illustration clarity, a partial view of the can annular array is
shown and includes the combustor assembly 14 and an adjacent
combustor assembly 32. The combustor chamber 18 of the combustor
assembly 14 and an adjacent combustor chamber 34 of the adjacent
combustor assembly 32 are fluidly coupled with a cross-fire tube 40
of a cross-fire tube arrangement 42, with the cross-fire tube 40
fixed at a first end region 44 proximate a component of the
combustor assembly 14. The component of the combustor assembly 14
to which the first end region 44 is fixed may be a variety of
components, including a combustor liner 46, a sleeve 48 that
surrounds the combustor liner 46, and/or an air shield 49, each of
the sleeve 48 and the air shield 49 spaced radially outwardly of
the combustor liner 46. The cross-fire tube 40 is fixed at a second
end region 50 proximate a component of the adjacent combustor
assembly 32. Similar to the components noted above, the component
of the adjacent combustor assembly 32 that the second end region 50
is fixed to may be an adjacent combustor liner 52, an adjacent
sleeve 54 and/or an adjacent air shield 56, each spaced radially
outwardly of the adjacent combustor liner 52. The cross-fire tube
40 typically includes a first portion 58 and a second portion 60
that are operably coupled to each other. In one embodiment, the
first portion 58 is referred to as a male portion that is in mating
engagement with the second portion 60 that is referred to as a
female portion for receiving the first portion 58. This arrangement
provides a telescoping engagement between the first portion 58 and
the second portion 60.
[0022] The cross-fire tube 40 includes an outer surface 62 and an
inner surface 64, with the inner surface 64 defining an interior
region 68 that provides the fluid coupling of the combustor chamber
18 and the adjacent combustor chamber 34, which allows passage of a
flame from the combustor chamber 18 to the adjacent combustor
chamber 34, or vice versa. Such passage is desirable during
light-off of the combustor assemblies of the gas turbine engine 10
and allows for nearly simultaneous ignition or re-ignition of the
combustor assemblies.
[0023] Disposed along the outer surface 62 is a spring 70 that
extends from proximate the first end region 44 of the cross-fire
tube 40 to proximate the second end region 50 of the cross-fire
tube 40. The spring 70 is at least partially retained by an outer
shield 72 that surrounds the outer surface 62 of the cross-fire
tube 40. The outer shield 72 is spaced radially outwardly from the
outer surface 62 to accommodate disposal of the spring 70 between
the cross-fire tube 40 and the outer shield 72. In the illustrated
embodiment, the outer shield 72 is segmented to only surround
portions of the cross-fire tube 40 and the spring 70. Specifically,
the outer shield 72 surrounds a portion of the first portion 58 and
a portion of the second portion 60 of the cross-fire tube 40.
However, it is to be understood that the outer shield 72 may extend
along an entire, or nearly an entire, length of the cross-fire tube
40. Irrespective of the amount of the cross-fire tube 40 that is
surrounded by the outer shield 72, the spring 70 provides a
resilient spring biasing force on the first portion 58 and the
second portion 60 of the cross-fire tube 40. The cross-fire tube 40
is telescopingly moveable between a first extended position, as
shown, and a second compressed position upon compression of the
spring 70. As will be described in detail below, compression of the
cross-fire tube 40 and the spring 70 is advantageous during certain
phases of assembly of the combustor assembly 14 and the adjacent
combustor assembly 32.
[0024] Referring now to FIGS. 3-5, in conjunction with FIG. 2, the
cross-fire tube arrangement 42 includes a first collar 80 fixedly
secured to a component of the combustor assembly 14, such as the
combustor liner 46, the sleeve 48 that surrounds the combustor
liner 46, and/or the air shield 49. Similarly, a second collar 82
is fixedly secured to a component of the adjacent combustor
assembly 32. The first collar 80 and the second collar 82 may be
welded to the component and is configured to engage the first end
region 44 of the cross-fire tube 40 and the second end region 50 of
the cross-fire tube 40, respectively. Similar reference numerals
will be employed in describing the first collar 80 and the second
collar 82, as both are similarly configured and perform similar
functions.
[0025] Both the first collar 80 and the second collar 82 include a
central opening 84 for receiving the first end region 44 and the
second end region 50, respectively, of the cross-fire tube 40. The
first end region 44 and the second end region 50 include an
anti-rotation surface 86 that corresponds to at least one
anti-rotation component 88 of the first collar 80 and the second
collar 82. In an exemplary embodiment, the at least one
anti-rotation component 88 and the anti-rotation surface 86
comprise corresponding non-planar surfaces each having conical
regions. It is to be appreciated that numerous alternative
geometries may be employed and furthermore it is contemplated that
corresponding protrusions and recesses may be utilized to form the
anti-rotation surface 86 and the at least one anti-rotation
component 88. Irrespective of the precise configuration of the
anti-rotation surface 86 and the at least one anti-rotation
component 88, the corresponding features provide a self-aligning
aspect for the cross-fire tube arrangement 42. Specifically,
disposal of the cross-fire tube 40 into an abutting manner with the
first collar 80 and the second collar 82 provides a fixed
rotational position of the cross-fire tube 40, thereby reducing
judgment of an installation operator.
[0026] During operation of the combustor assembly 14 and the
adjacent combustor assembly 32, the first end region 44 and the
second end region 50 are particularly susceptible to high
temperatures due to exposure to the combustor chamber 18 and the
adjacent combustor chamber 34. A plurality of cooling holes 90 are
formed in the first collar 80 and the second collar 82 in a region
adjacent the first end region 44 and the second end region 50 for
cooling purposes. It is noted that the first end region 44 and the
second end region 50 are formed of smooth contours, such as
circular, elliptical or the like. These smooth contours reduce any
disturbance of an airflow passing through an annulus between the
combustor liner 46 and the sleeve 48 and/or the air shield 49.
[0027] Referring now to FIGS. 6-9, various installation procedures
of the cross-fire tube arrangement 42 are illustrated. As described
above, the first end region 44 of the first portion 58 or the
second end region 50 of the second portion 60 of the cross-fire
tube 40 may be inserted into the central opening 84 of the first
collar 80 or the second collar 82, respectively (FIG. 6). Upon
contact between the anti-rotation surface 86 and the at least one
anti-rotation component 88, the cross-fire tube 40 is self-aligned
into a fixed rotational position. In the illustrated embodiment,
the second portion 60 is shown in engagement with the second collar
82. The first portion 58 is engaged with the second portion 60,
with the spring 70 sandwiched between the cross-fire tube 40 and
the outer shield 72, as well as between the first end region 44 and
the second end region 50. Engagement between the first portion 58
and the second portion 60 may take place before or after disposal
of the second portion 60 with the second collar 82. Similarly, it
is to be appreciated that the first portion 58 may be engaged with
the first collar 80 prior to engagement with the second portion 60.
As shown in FIG. 7, a threaded rod 98 may be engaged with either or
both of the first portion 58 and the second portion 60 and extends
through an aperture of the combustor assembly 14 or the adjacent
combustor assembly 32 to receive a mechanical fastener 92 (FIG. 8),
such as a washer and nut arrangement, for example. Such an
arrangement assists in securing the cross-fire tube 40 in a fixed
position.
[0028] To provide clearance for portions of the combustor assembly
14, such as a module that is inserted into the combustor assembly
14, the cross-fire tube 40 is moveable between a first position 94,
as shown in FIG. 2, and a second position 96 (FIG. 9). The second
position 96 comprises a compressed condition of the spring 70 and
the cross-fire tube 40, such that components of the combustor
assembly 14 may be inserted into the overall combustor structure.
The resiliency of the spring 70 leads to extension of the
cross-fire tube 40 after the components are sufficiently inserted
into the combustor assembly 14. Large distances of compression of
the cross-fire tube 40 are typically required to establish
necessary clearance for reliable insertion of the combustor
assembly 14 components. Disposal of the spring 70 along
substantially the entire length of the cross-fire tube 40 allows
compression of the cross-fire tube 40 to a large degree.
[0029] As illustrated in the flow diagram of FIG. 10, and with
reference to FIGS. 1-9, a method of assembling a combustor
structure 100 is also provided. The gas turbine engine 10 and the
cross-fire tube arrangement 42 have been previously described and
specific structural components need not be described in further
detail. The method of assembling a combustor structure 100 includes
inserting a first portion of a cross-fire tube into a portion of a
combustor assembly 102. The first portion of the cross-fire tube is
rotated to align an anti-rotation surface of the first portion with
a corresponding anti-rotation feature of a first collar 104. A
second portion of the cross-fire tube is matably engaged with the
first portion 106, with the spring 70 extended from the first
portion 58 to the second portion 60. The cross-fire tube is
compressed from a first position to a second position 108, thereby
providing clearance for insertion of an adjacent combustor assembly
or associated components.
[0030] While the invention has been described in detail in
connection with only a limited number of embodiments, it should be
readily understood that the invention is not limited to such
disclosed embodiments. Rather, the invention can be modified to
incorporate any number of variations, alterations, substitutions or
equivalent arrangements not heretofore described, but which are
commensurate with the spirit and scope of the invention.
Additionally, while various embodiments of the invention have been
described, it is to be understood that aspects of the invention may
include only some of the described embodiments. Accordingly, the
invention is not to be seen as limited by the foregoing
description, but is only limited by the scope of the appended
claims.
* * * * *