U.S. patent application number 13/893721 was filed with the patent office on 2014-11-20 for system for vibration damping of a fuel nozzle within a combustor.
This patent application is currently assigned to General Electric Company. The applicant listed for this patent is GENERAL ELECTRIC COMPANY. Invention is credited to Marcus Byron Huffman, Dereck Joseph Ouellet, Brandon Taylor Overby, Stephen Wayne Tilley.
Application Number | 20140338343 13/893721 |
Document ID | / |
Family ID | 51894673 |
Filed Date | 2014-11-20 |
United States Patent
Application |
20140338343 |
Kind Code |
A1 |
Ouellet; Dereck Joseph ; et
al. |
November 20, 2014 |
SYSTEM FOR VIBRATION DAMPING OF A FUEL NOZZLE WITHIN A
COMBUSTOR
Abstract
A system for vibration damping a fuel nozzle within a combustor
includes a support plate, a fuel nozzle passage that extends
through the support plate and a cylindrical damping insert that is
coaxially aligned within the fuel nozzle passage and at least
partially defines the fuel nozzle passage. The damping insert may
include a metallic-mesh liner.
Inventors: |
Ouellet; Dereck Joseph;
(Pelzer, SC) ; Huffman; Marcus Byron;
(Simpsonville, SC) ; Overby; Brandon Taylor;
(Spartanburg, SC) ; Tilley; Stephen Wayne;
(Simpsonville, SC) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
GENERAL ELECTRIC COMPANY |
Schenectady |
NY |
US |
|
|
Assignee: |
General Electric Company
Schenectady
NY
|
Family ID: |
51894673 |
Appl. No.: |
13/893721 |
Filed: |
May 14, 2013 |
Current U.S.
Class: |
60/740 |
Current CPC
Class: |
F23M 20/005 20150115;
F23R 2900/00014 20130101; F23R 3/60 20130101; F23R 3/286
20130101 |
Class at
Publication: |
60/740 |
International
Class: |
F23R 3/28 20060101
F23R003/28 |
Claims
1. A system for vibration damping a fuel nozzle within a combustor,
comprising: a. a support plate; b. a fuel nozzle passage that
extends through the support plate; and c. a cylindrical damping
insert coaxially aligned within the fuel nozzle passage, wherein
the damping insert at least partially defines the fuel nozzle
passage.
2. The system as in claim 1, wherein the damping insert comprises a
metallic-mesh liner.
3. The system as in claim 2, wherein the damping insert comprises
an annular inner sleeve and an annular outer sleeve, the
metallic-mesh liner being disposed between the inner sleeve and the
outer sleeve.
4. The system as in claim 2, wherein the damping insert comprises
an outer sleeve that at least partially surrounds the metallic-mesh
liner.
5. The system as claim 2, wherein the damping insert comprises an
annular ring that surrounds the metallic-mesh liner, wherein the
annular ring is coupled to the support plate.
6. The system as in claim 5, wherein the damping insert comprises
an inner sleeve coaxially aligned within the annular ring, the
metallic-mesh liner being disposed between the inner sleeve and the
annular ring.
7. The system as in claim 1, wherein the damping insert includes an
expansion gap.
8. The system as in claim 1, wherein the damping insert includes an
outer sleeve having at least one retaining feature, the system
further comprising a retaining plate that extends circumferentially
around at least a portion of the fuel nozzle passage, wherein the
retainer plate extends at least partially across the retaining
feature.
9. A combustor for a gas turbine, comprising: a. an outer casing
and an end cover that is coupled to the outer casing; b. a fuel
nozzle that extends downstream from the end cover within the outer
casing; c. a cap assembly that extends radially and axially within
the outer casing, the cap assembly having a support plate and a cap
plate disposed downstream from the support plate, the cap plate
having an opening; d. a fuel nozzle passage that extends through
the support plate, wherein the fuel nozzle extends at least
partially through the fuel nozzle passage and the opening of the
cap plate; and e. a cylindrical damping insert coaxially aligned
within the fuel nozzle passage, wherein the damping insert extends
circumferentially around the fuel nozzle.
10. The combustor as in claim 9, wherein the damping insert
comprises a metallic-mesh liner.
11. The combustor as in claim 10, wherein the damping insert
comprises an annular inner sleeve and an annular outer sleeve, the
metallic-mesh liner being disposed between the inner sleeve and the
outer sleeve.
12. The combustor as in claim 10, wherein the damping insert
comprises an outer sleeve that at least partially surrounds the
metallic-mesh liner.
13. The combustor as in claim 10, wherein the damping insert
comprises an annular ring that surrounds the metallic-mesh liner,
wherein the annular ring is coupled to the support plate.
14. The combustor as in claim 13, wherein the damping insert
comprises an inner sleeve coaxially aligned within the annular
ring, the metallic-mesh liner being disposed between the inner
sleeve and the annular ring.
15. The combustor as in claim 10, wherein the damping insert
includes an expansion gap.
16. A gas turbine, comprising: a. a compressor; b. a combustor
downstream from the compressor, the combustor having an outer
casing, an end cover coupled to the outer casing and a fuel nozzle
that extends axially downstream from the end cover within the outer
casing; c. a turbine disposed downstream from the combustor; and d.
a system for vibration damping of the fuel nozzle, wherein the
system is disposed within the outer casing downstream from the end
cover, the vibration damping system comprising: i. a support plate;
ii. a fuel nozzle passage that extends through the support plate;
and iii. a cylindrical damping insert coaxially aligned within the
fuel nozzle passage, the damping insert comprising a metallic-mesh
liner that circumferentially surrounds a portion of the fuel
nozzle, wherein the damping insert at least partially defines the
fuel nozzle passage.
17. The gas turbine as in claim 16, wherein the damping insert
comprises an annular inner sleeve and an annular outer sleeve, the
metallic-mesh liner being disposed between the inner sleeve and the
outer sleeve.
18. The gas turbine as in claim 17, wherein the damping insert
includes an expansion gap.
19. The gas turbine as in claim 16, wherein the damping insert
comprises an outer sleeve that at least partially surrounds the
metallic-mesh liner.
20. The combustor as in claim 10, wherein the damping insert
comprises an annular ring that surrounds the metallic-mesh liner,
wherein the annular ring is coupled to the support plate.
Description
FIELD OF THE INVENTION
[0001] The present invention generally relates to a combustor for
use in a gas turbine. More particularly, this invention relates to
a fuel nozzle support collar for reducing fuel nozzle
vibration.
BACKGROUND OF THE INVENTION
[0002] A typical gas turbine includes an inlet section, a
compressor section, a combustion section, a turbine section, and an
exhaust section. The inlet section cleans and conditions a working
fluid (e.g., air) and supplies the working fluid to the compressor
section. The compressor section progressively increases the
pressure of the working fluid and supplies a compressed working
fluid to the combustion section. The compressed working fluid and a
fuel are mixed within the combustion section and burned in a
combustion chamber to generate combustion gases having a high
temperature and pressure. The combustion gases are routed along
through a hot gas path into the turbine section where they expand
to produce work. For example, expansion of the combustion gases in
the turbine section may rotate a shaft connected to a generator to
produce electricity.
[0003] The combustion section generally includes a plurality of
combustors annularly arranged and disposed between the compressor
section and the turbine section. An outer casing at least partially
surrounds the combustors and each combustor includes an end cover
that is coupled to the outer casing. At least one axially extending
fuel nozzle extends downstream from each end cover within the outer
casing. An upstream or forward end of the fuel nozzle is rigidly
connected to the end cover. In some combustor configurations, a
downstream or aft end of the fuel nozzle is generally unsupported,
thereby creating a cantilever. In alternate designs, the aft end of
the fuel nozzle may be at least partially supported within an
opening in a cap assembly that extends radially and axially within
the outer casing downstream from the end cover.
[0004] During operation of the gas turbine, various factors such as
combustion dynamics, rotor vibration and/or flow induced excitation
may cause the cantilevered fuel nozzle to vibrate at various
resonant frequencies which may affect fuel nozzle/combustor
durability due to high cycle fatigue related issues. Various
systems and methods have been deployed and/or considered to dampen
the cantilevered fuel nozzles. For example, one system includes
spring supports to shift or increase the natural frequency of the
fuel nozzle. Other attempts to shift or increase the natural
frequency of the fuel nozzle have included connecting the aft end
of the fuel nozzle to a rigid structure within the combustor using
a tether or braided wire.
[0005] Although the systems previously mentioned are generally
effective, each may require additional hardware and add complexity
to new combustor designs. In addition, the systems previously
mentioned may not be practical for retrofitting existing combustor
designs. Accordingly, an improved system for damping a fuel nozzle
within a combustor of a gas turbine would be useful.
BRIEF DESCRIPTION OF THE INVENTION
[0006] Aspects and advantages of the invention are set forth below
in the following description, or may be obvious from the
description, or may be learned through practice of the
invention.
[0007] One embodiment of the present invention is a system for
vibration damping a fuel nozzle within a combustor. The system
includes a support plate, a fuel nozzle passage that extends
through the support plate and a cylindrical damping insert that is
coaxially aligned within the fuel nozzle passage and at least
partially defines the fuel nozzle passage.
[0008] Another embodiment of the present invention is a combustor
for a gas turbine. The combustor generally includes an outer casing
and an end cover that is coupled to the outer casing and a fuel
nozzle that extends downstream from the end cover within the outer
casing. A cap assembly extends radially and axially within the
outer casing. The cap assembly includes a support plate and a cap
plate that is disposed downstream from the support plate. The cap
plate includes an opening. A fuel nozzle passage extends through
the support plate and is aligned with the opening in the cap plate.
The fuel nozzle extends at least partially through the fuel nozzle
passage and the opening. A cylindrical damping insert is coaxially
aligned with the fuel nozzle passage and extends circumferentially
around the fuel nozzle.
[0009] Another embodiment of the present invention includes a gas
turbine. The gas turbine includes a compressor and a combustor that
is disposed downstream from the compressor. The combustor includes
an outer casing, an end cover coupled to the outer casing and a
fuel nozzle that extends axially downstream from the end cover
within the outer casing. A turbine is disposed downstream from the
combustor. The gas turbine further includes a system for vibration
damping of the fuel nozzle. The system is disposed within the outer
casing downstream from the end cover. The system includes a support
plate, a fuel nozzle passage that extends through the support
plate, and a cylindrical damping insert coaxially aligned within
the fuel nozzle passage. The damping insert comprises a
metallic-mesh liner that circumferentially surrounds a portion of
the fuel nozzle. The damping insert at least partially defines the
fuel nozzle passage.
[0010] Those of ordinary skill in the art will better appreciate
the features and aspects of such embodiments, and others, upon
review of the specification.
BRIEF DESCRIPTION OF THE DRAWINGS
[0011] A full and enabling disclosure of the present invention,
including the best mode thereof to one skilled in the art, is set
forth more particularly in the remainder of the specification,
including reference to the accompanying figures, in which:
[0012] FIG. 1 is a functional block diagram of an exemplary gas
turbine within the scope of the present invention;
[0013] FIG. 2 provides a simplified cross section side view of an
exemplary combustor that may incorporate various embodiments of the
present invention;
[0014] FIG. 3 provides a cross section perspective view of an
exemplary combustor that incorporates various embodiments of the
present invention;
[0015] FIG. 4 provides a prospective view of a system for vibration
damping of a fuel nozzle within a combustor as shown in FIG. 3,
according to one embodiment of the present invention;
[0016] FIG. 5 provides an exploded perspective view of the system
for vibration damping of a fuel nozzle within a combustor as shown
in FIG. 4;
[0017] FIG. 6 provides a cross section perspective view of a
portion of the combustor as shown in FIG. 3, according to one
embodiment of the present disclosure;
[0018] FIG. 7 provides a perspective view of a damping insert
according to at least one embodiment of the present disclosure;
[0019] FIG. 8 provides a perspective view of a damping insert
according to one embodiment of the present disclosure;
[0020] FIG. 9 provides a perspective view of a portion of the
combustor as shown in FIG. 3, including the damping insert as shown
in FIG. 8;
[0021] FIG. 10 provides a perspective view of the system for
vibration damping of a fuel nozzle within a combustor including an
alternate embodiment of the damping insert, according to one
embodiment of the present disclosure; and
[0022] FIG. 11 provides an enlarged cross section perspective view
of a portion of the damping insert as shown in FIG. 10, according
to one embodiment of the present invention.
DETAILED DESCRIPTION OF THE INVENTION
[0023] Reference will now be made in detail to present embodiments
of the invention, one or more examples of which are illustrated in
the accompanying drawings. The detailed description uses numerical
and letter designations to refer to features in the drawings. Like
or similar designations in the drawings and description have been
used to refer to like or similar parts of the invention.
[0024] As used herein, the terms "first", "second", and "third" may
be used interchangeably to distinguish one component from another
and are not intended to signify location or importance of the
individual components. The terms "upstream," "downstream,"
"radially," and "axially" refer to the relative direction with
respect to fluid flow in a fluid pathway. For example, "upstream"
refers to the direction from which the fluid flows, and
"downstream" refers to the direction to which the fluid flows.
Similarly, "radially" refers to the relative direction
substantially perpendicular to the fluid flow, and "axially" refers
to the relative direction substantially parallel to the fluid flow.
The term "circumferentially" refers to a relative direction that
extends around an axial centerline of a particular component.
[0025] Each example is provided by way of explanation of the
invention, not limitation of the invention. In fact, it will be
apparent to those skilled in the art that modifications and
variations can be made in the present invention without departing
from the scope or spirit thereof. For instance, features
illustrated or described as part of one embodiment may be used on
another embodiment to yield a still further embodiment. Thus, it is
intended that the present invention covers such modifications and
variations as come within the scope of the appended claims and
their equivalents.
[0026] Referring now to the drawings, wherein identical numerals
indicate the same elements throughout the figures, FIG. 1 provides
a functional block diagram of an exemplary gas turbine 10 that may
incorporate various embodiments of the present invention. As shown,
the gas turbine 10 generally includes an inlet section 12 that may
include a series of filters, cooling coils, moisture separators,
and/or other devices to purify and otherwise condition a working
fluid (e.g., air) 14 entering the gas turbine 10. The working fluid
14 flows to a compressor section where a compressor 16
progressively imparts kinetic energy to the working fluid 14 to
produce a compressed working fluid 18 at a highly energized
state.
[0027] The compressed working fluid 18 is mixed with a fuel from a
fuel supply 20 to form a combustible mixture within one or more
combustors 22. The combustible mixture is burned to produce
combustion gases 24 having a high temperature and pressure. The
combustion gases 24 flow through a turbine 26 of a turbine section
to produce work. For example, the turbine 26 may be connected to a
shaft 28 so that rotation of the turbine 26 drives the compressor
16 to produce the compressed working fluid 18. Alternately or in
addition, the shaft 28 may connect the turbine 26 to a generator 30
for producing electricity. Exhaust gases 32 from the turbine 26
flow through an exhaust section 34 that connects the turbine 26 to
an exhaust stack 36 downstream from the turbine 26. The exhaust
section 34 may include, for example, a heat recovery steam
generator (not shown) for cleaning and extracting additional heat
from the exhaust gases 32 prior to release to the environment.
[0028] The combustors 22 may be any type of combustor known in the
art, and the present invention is not limited to any particular
combustor design unless specifically recited in the claims. FIG. 2
provides a simplified cross-section side view of an exemplary
combustor 22 that incorporates various embodiments of the present
invention. As shown in FIG. 2, a casing 40 and an end cover 42 may
combine to contain the compressed working fluid 18 flowing to the
combustor 22 from the compressor 16 (FIG. 1). The compressed
working fluid 18 may pass through cooling holes 44 in an annular
flow sleeve 46 such as an impingement sleeve or a combustion flow
sleeve to flow along the outside of a transition duct 48 and/or a
liner 50 towards the end cover 42.
[0029] At the end cover 42, the compressed working fluid 18
reverses flow direction. A portion of the compressed working fluid
18 is routed through at least one fuel nozzle 52 where a fuel is
injected into the compressed working fluid 18 to provide a
combustible mixture 54. The combustible mixture 54 is injected into
a combustion chamber 56 for combustion. In particular embodiments,
the combustor 22 includes an annular cap assembly 58 that at least
partially surrounds a portion of the fuel nozzle 52. The cap
assembly 58 may be connected to the outer casing 40.
[0030] FIG. 3 provides a cross section perspective view of an
exemplary combustor 22 that incorporates various embodiments of the
present invention. As shown in FIG. 3, the combustor 22 may include
a plurality of fuel nozzles 52 that extend generally axially
downstream from an inner surface 60 of the end cover 42. The fuel
nozzles 52 are typically cantilevered from the end cover 42. For
example, a forward or upstream end 62 of each fuel nozzle 52 is
rigidly connected to the end cover 42.
[0031] As shown, the cap assembly 58 generally extends radially and
axially within the outer casing 40 downstream from the end cover
42. In particular embodiments, the cap assembly 58 includes a cap
plate 64 disposed at an aft/downstream end 66 of the cap assembly
58. An aft or downstream portion 68 of each fuel nozzle 52 extends
at least partially through a corresponding opening 70 that extends
through the cap plate 64. The cap plate 64 is generally disposed
adjacent to the combustion chamber 56 (FIG. 2).
[0032] In various embodiments, as shown in FIG. 3, the combustor 22
includes a system for vibration damping of the fuel nozzles 52,
herein referred to as "system 100." FIG. 4 provides a prospective
view of the system 100 as shown in FIG. 3 according to one
embodiment, and FIG. 5 provides an exploded perspective view of the
system 100 as shown in FIG. 4. As shown in FIGS. 4 and 5, the
system 100 includes a support plate 102, at least one fuel nozzle
passage 104 that extends through the support plate 102 and at least
one cylindrically shaped damping insert 106 that is substantially
coaxially aligned within the fuel nozzle passage 104 with respect
to an axial centerline 108 of the fuel nozzle passage 104. In one
embodiment, as shown in FIG. 3, the support plate 102 and/or the
system 100 may be provided as part of the cap assembly 58.
[0033] In particular embodiments, as shown in FIGS. 4 and 5 the
system 100 includes at least one retaining plate 110. The retaining
plate 110 generally extends circumferentially around at least a
portion of the fuel nozzle passage 104 so as to retain the damping
insert 106 in position. The fuel nozzle passage 104 may be at least
partially defined by an outer collar 112 that at least partially
circumferentially surrounds the fuel nozzle passage 104. The outer
collar 112 generally extends axially outward from the support plate
102. The outer collar 112 may at least partially surround the
damping insert 106. In particular embodiments, as shown, the system
100 may include a plurality of fuel nozzle passages 104, a
plurality of damping inserts 106, a plurality of retaining rings
110 and a plurality of outer collars 112 as described herein.
[0034] In one embodiment, as shown in FIG. 5, the damping insert
includes an outer sleeve 114 that at least partially surrounds a
metallic-mesh liner 116. The metallic-mesh liner 116 may include
any material such as wire-mesh, metallic-mesh and/or
metallic-fabric that has suitable thermal and damping properties
for the intended purpose of the present invention and that is
suitable for use within the operating environment of the combustor.
For example, the metallic-mesh material may comprise of a high
performance alloy or super alloy such as an austenitic
nickel-chromium-based alloy
[0035] FIG. 6 provides a cross section perspective view of a
portion of the combustor 22 as shown in FIG. 3. In one embodiment,
the damping insert 106 extends circumferentially around the fuel
nozzle 52 within the fuel nozzle passage 104. In this embodiment,
the metallic-mesh liner 116 is in direct contact with the fuel
nozzle 52. During operation of the gas turbine, combustion
dynamics, rotor vibration and/or flow induced excitation may cause
the cantilevered fuel nozzle 52 to vibrate at various resonant
frequencies, thereby loading individual fibers throughout the
metallic-mesh liner 116. As a result, friction coulomb damping
occurs to reduce vibration amplitudes of the fuel nozzle 52,
thereby increasing overall combustor durability.
[0036] FIG. 7 provides a perspective view of the damping insert 106
according to at least one embodiment of the present disclosure. As
shown, the damping insert 106 may further include an inner sleeve
118. The inner sleeve 118 may be coaxially aligned within the outer
sleeve 114. The metallic-mesh liner 116 is disposed between the
inner sleeve 118 and the outer sleeve 114. The inner sleeve 118 and
the outer sleeve 114 may comprise of any material suitable for the
intended purpose as described herein. For example, the inner sleeve
118 and the outer sleeve 114 may comprise of a stainless steel or
other alloy having suitable wear and thermal properties.
[0037] As shown in FIG. 7, the damping insert 106 may also include
an expansion joint or slot 120 to allow for expansion around the
fuel nozzle 52 during installation/assembly. In this manner, the
damping insert 106 may be slightly undersized so as to provide a
spring force around the fuel nozzle 52 (FIG. 3), thereby ensuring
contact between the damping insert 106 and the fuel nozzle 52
during operation of the gas turbine 10. In addition, the expansion
joint 120 helps to avoid potential misalignment issues to assembly
tolerances.
[0038] FIG. 8 provides a perspective view of the damping insert 106
according to one embodiment of the present disclosure, and FIG. 9
provides a perspective view of a portion of the combustor 22 as
shown in FIG. 3, including the damping insert 106 as shown in FIG.
8. As show in FIGS. 8 and 9, the damping insert 106 may include at
least one step or retaining feature 122 that extends at least
partially around the outer sleeve 114. As shown in FIG. 9, the
retainer plate 110 extends at least partially across the retaining
feature 122 so as to retain the damping insert 106 in the fuel
nozzle passage 104. As shown in FIG. 9, the outer collar 112 may
include a complementary step feature 124 configured to engage with
the retaining feature 122 of the damping insert 106.
[0039] FIG. 10 provides a perspective view of the system 100
including an alternate embodiment of the damping insert 106
according to one embodiment of the present disclosure, and FIG. 11
provides an enlarged cross section perspective view of a portion of
the damping insert 106 as shown in FIG. 10. As shown in FIG. 10,
the damping insert 106 may include a retaining ring 126. The
retaining ring 126 at least partially defines the fuel nozzle
passage 104. The retaining ring 126 may be fixed to the support
plate 102 by any means known in the art that is suitable for the
intended purpose of the invention. For example, the retaining ring
126 may be brazed, bolted or brazed to the support plate 102. As
shown in FIG. 11, the retaining ring 126 generally surrounds and/or
at least partially encases the metallic-mesh liner 116. In
particular embodiments, the metallic-mesh liner 116 is disposed
between the inner sleeve 118 and the retaining ring 126.
[0040] The various embodiments as disclosed herein and as
illustrated in FIGS. 3 through 11 provide various technical
benefits over existing technologies. Specifically, this invention
takes advantage of the damping characteristics of metallic-mesh,
wire mesh or other metallic fabrics to reduce vibration in the fuel
nozzle. For example, when the fuel nozzle begins to vibrate, the
individual fibers throughout the metallic-mesh rub against each
other resulting in friction coulomb damping, thereby reducing
vibration amplitudes of the fuel nozzles. As a result, overall
mechanical performance of the combustor and/or the fuel nozzle is
improved by reducing the potential of high cycle related issues, in
particular with extended length fuel nozzles. In addition, the
system may be retrofitted into existing combustor designs with
minimal additional hardware or hardware modification required. In
addition, the metallic-mesh does not impose problems usually
associated with axial and or radial thermal expansion because the
thermal growth may be accommodated by the metallic-mesh
material.
[0041] This written description uses examples to disclose the
invention, including the best mode, and also to enable any person
skilled in the art to practice the invention, including making and
using any devices or systems and performing any incorporated
methods. The patentable scope of the invention is defined by the
claims, and may include other examples that occur to those skilled
in the art. Such other and examples are intended to be within the
scope of the claims if they include structural elements that do not
differ from the literal language of the claims, or if they include
equivalent structural elements with insubstantial differences from
the literal language of the claims.
* * * * *