U.S. patent application number 13/006518 was filed with the patent office on 2012-07-19 for apparatus for vibration support in combustors and method for forming apparatus.
This patent application is currently assigned to GENERAL ELECTRIC COMPANY. Invention is credited to David William Cihlar, Patrick Benedict Melton, John Alfred Simo.
Application Number | 20120180492 13/006518 |
Document ID | / |
Family ID | 46397777 |
Filed Date | 2012-07-19 |
United States Patent
Application |
20120180492 |
Kind Code |
A1 |
Simo; John Alfred ; et
al. |
July 19, 2012 |
APPARATUS FOR VIBRATION SUPPORT IN COMBUSTORS AND METHOD FOR
FORMING APPARATUS
Abstract
A sleeve component assembly for a combustor, and a method for
forming the sleeve component assembly for the combustor, are
disclosed. The sleeve component assembly includes a sleeve
component, the sleeve component comprising one of an inner sleeve
component or an outer sleeve component. The sleeve component
assembly further includes at least one support feature extending
from the sleeve component, the at least one support feature
configured to contact and provide vibratory support to an adjacent
sleeve component. The at least one support feature is integral with
the sleeve component.
Inventors: |
Simo; John Alfred;
(Simpsonville, SC) ; Melton; Patrick Benedict;
(Horse Shoe, NC) ; Cihlar; David William;
(Greenville, SC) |
Assignee: |
GENERAL ELECTRIC COMPANY
Schenectady
NY
|
Family ID: |
46397777 |
Appl. No.: |
13/006518 |
Filed: |
January 14, 2011 |
Current U.S.
Class: |
60/752 ;
164/131 |
Current CPC
Class: |
F23R 2900/00018
20130101; F23R 3/60 20130101; B22D 25/00 20130101 |
Class at
Publication: |
60/752 ;
164/131 |
International
Class: |
F23R 3/44 20060101
F23R003/44; B22D 25/00 20060101 B22D025/00; B22D 29/00 20060101
B22D029/00 |
Claims
1. A sleeve component assembly for a combustor, the sleeve
component assembly comprising: a sleeve component, the sleeve
component comprising one of an inner sleeve component or an outer
sleeve component; and, at least one support feature extending from
the sleeve component, the at least one support feature configured
to contact and provide vibratory support to an adjacent sleeve
component, wherein the at least one support feature is integral
with the sleeve component.
2. The sleeve component assembly of claim 1, wherein the at least
one support feature is formed during casting of the sleeve
component.
3. The sleeve component assembly of claim 1, further comprising a
plurality of support features.
4. The sleeve component assembly of claim 1, wherein the sleeve
component is an inner sleeve component.
5. The sleeve component assembly of claim 1, wherein the sleeve
component is a transition piece.
6. The sleeve component assembly of claim 1, wherein the at least
one support feature is configured to generally continuously contact
the adjacent sleeve component.
7. The sleeve component assembly of claim 1, wherein the at least
one support feature is configured to provide a desired heat
transfer characteristic.
8. The sleeve component assembly of claim 1, wherein the at least
one support feature is configured to provide a desired vibratory
characteristic.
9. A combustor for a turbine system, the combustor comprising: an
inner sleeve component; an outer sleeve component disposed adjacent
to the inner sleeve component; and, at least one support feature
extending from one of the inner sleeve component or the outer
sleeve component, the at least one support feature configured to
contact and provide vibratory support to the other of the inner
sleeve component or the outer sleeve component, wherein the at
least one support feature is integral with the one of the inner
sleeve component or the outer sleeve component.
10. The combustor of claim 9, wherein the at least one support
feature is formed during casting of the one of the inner sleeve
component or the outer sleeve component.
11. The combustor of claim 9, further comprising a plurality of
support features.
12. The combustor of claim 9, wherein the at least one support
feature extends from the inner sleeve component.
13. The combustor of claim 9, wherein the inner sleeve component is
a transition piece and the outer sleeve component is an impingement
sleeve.
14. A method for forming a sleeve component assembly for a
combustor, the method comprising: flowing a sleeve component
substrate into a mold through at least one gate, the mold
comprising the at least one gate and at least one shell configured
to form a sleeve component therein, the sleeve component comprising
one of an inner sleeve component or an outer sleeve component;
solidifying the sleeve component substrate in the mold to form the
sleeve component assembly, the sleeve component assembly comprising
the sleeve component and at least one support feature, the at least
one support feature integral with the sleeve component and disposed
in the at least one gate; removing the sleeve component assembly
from the mold; and, adjusting a height of the at least one support
feature such that the at least one support feature is configured to
contact and provide vibratory support to an adjacent sleeve
component.
15. The method of claim 14, wherein the at least one support
feature is a plurality of support features.
16. The method of claim 14, wherein the sleeve component is a
transition piece.
17. The method of claim 14, further comprising designing the at
least one gate such that the at least one support feature provides
a desired heat transfer characteristic.
18. The method of claim 14, further comprising designing the at
least one gate such that the at least one support feature provides
a desired vibratory characteristic.
19. The method of claim 14, further comprising modifying the at
least one support feature such that the at least one support
feature provides a desired heat transfer characteristic.
20. The method of claim 14, further comprising modifying the at
least one support feature such that the at least one support
feature provides a desired vibratory characteristic.
Description
FIELD OF THE INVENTION
[0001] The subject matter disclosed herein relates generally to
turbine systems, and more particularly to apparatus for reducing
vibrations in combustors of turbine systems and methods for forming
the apparatus.
BACKGROUND OF THE INVENTION
[0002] Turbine systems are widely utilized in fields such as power
generation. For example, a conventional gas turbine system includes
a compressor, a combustor, and a turbine. During operation of the
turbine system, various components in the system may be subjected
to high temperature flows, which can cause the components to fail.
Since higher temperature flows generally result in increased
performance, efficiency, and power output of the gas turbine
system, the components that are subjected to high temperature flows
must be cooled to allow the gas turbine system to operate at
increased temperatures.
[0003] During operation of a turbine system, many components of the
system may be subject to significant structural vibrations. These
vibrations can stress the components and eventually cause the
components to fail. For example, in gas turbine systems, the
combustor impingement sleeves are particularly vulnerable to
structural vibrations.
[0004] Previous attempts to reduce structural vibrations in
impingement sleeves have involved thickening the walls of the
impingement sleeves or adding ribs or gussets to the impingement
sleeves. Thickening the walls, however, may make the impingement
sleeves undesirably heavy, and may further make the impingement
sleeves more expensive and difficult to manufacture. The addition
of ribs or gussets may also make the impingement sleeves more
expensive and difficult to manufacture, and may potentially add
failure points to the system.
[0005] Thus, an improved apparatus for reducing structural
vibrations in a combustor of a turbine system, and a method for
forming the apparatus, would be desired in the art. For example, a
method and apparatus that provide support features that are
integral with an existing combustor component would be
advantageous. Further, a method and apparatus that provide support
features that may be configured for optimal vibratory and heat
transfer capabilities would be desired.
BRIEF DESCRIPTION OF THE INVENTION
[0006] Aspects and advantages of the invention will be set forth in
part in the following description, or may be obvious from the
description, or may be learned through practice of the
invention.
[0007] In one embodiment, a sleeve component assembly for a
combustor is disclosed. The sleeve component assembly includes a
sleeve component, the sleeve component comprising one of an inner
sleeve component or an outer sleeve component. The sleeve component
assembly further includes at least one support feature extending
from the sleeve component, the at least one support feature
configured to contact and provide vibratory support to an adjacent
sleeve component. The at least one support feature is integral with
the sleeve component.
[0008] In another embodiment, a method for forming a sleeve
component assembly for a combustor is disclosed. The method
includes flowing a sleeve component substrate into a mold through
at least one gate, the mold comprising the at least one gate and at
least one shell configured to form a sleeve component therein, the
sleeve component comprising one of an inner sleeve component or an
outer sleeve component. The method further includes solidifying the
sleeve component substrate in the mold to form the sleeve component
assembly, the sleeve component assembly comprising the sleeve
component and at least one support feature, the at least one
support feature integral with the sleeve component and disposed in
the at least one gate. The method further includes removing the
sleeve component assembly from the mold, and adjusting a height of
the at least one support feature such that the at least one support
feature is configured to contact and provide vibratory support to
an adjacent sleeve component.
[0009] These and other features, aspects and advantages of the
present invention will become better understood with reference to
the following description and appended claims. The accompanying
drawings, which are incorporated in and constitute a part of this
specification, illustrate embodiments of the invention and,
together with the description, serve to explain the principles of
the invention.
BRIEF DESCRIPTION OF THE DRAWINGS
[0010] A full and enabling disclosure of the present invention,
including the best mode thereof, directed to one of ordinary skill
in the art, is set forth in the specification, which makes
reference to the appended figures, in which:
[0011] FIG. 1 is a schematic illustration of a gas turbine
system;
[0012] FIG. 2 is a side cutaway view of one embodiment of various
components of the gas turbine system of the present disclosure;
[0013] FIG. 3 is a side view of one embodiment of a sleeve
component assembly of the present disclosure; and
[0014] FIG. 4 is a cross-sectional view of one embodiment of a mold
for a sleeve component assembly of the present disclosure.
DETAILED DESCRIPTION OF THE INVENTION
[0015] Reference now will be made in detail to embodiments of the
invention, one or more examples of which are illustrated in the
drawings. 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 various modifications and
variations can be made in the present invention without departing
from the scope or spirit of the invention. For instance, features
illustrated or described as part of one embodiment can be used with
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.
[0016] FIG. 1 is a schematic diagram of a gas turbine system 10.
The system 10 may include a compressor 12, a combustor 14, and a
turbine 16. Further, the system 10 may include a plurality of
compressors 12, combustors 14, and turbines 16. The compressors 12
and turbines 16 may be coupled by a shaft 18. The shaft 18 may be a
single shaft or a plurality of shaft segments coupled together to
form shaft 18.
[0017] As illustrated in FIG. 2, the combustor 14 is generally
fluidly coupled to the compressor 12 and the turbine 16. The
compressor 12 may include a diffuser 20 and a discharge plenum 22
that are coupled to each other in fluid communication, so as to
facilitate the channeling of a working fluid 24 to the combustor
14. For example, after being compressed in the compressor 12,
working fluid 24 may flow through the diffuser 20 and be provided
to the discharge plenum 22. The working fluid 24 may then flow from
the discharge plenum 22 to the combustor 14, wherein the working
fluid 24 is combined with fuel from fuel nozzles 26. After mixing
with the fuel, the working fluid 24/fuel mixture may be ignited
within combustion chamber 28 to create hot gas flow 30. The hot gas
flow 30 may be channeled through the combustion chamber 28 along a
hot gas path 32 into a transition piece cavity 34 and through a
turbine nozzle 36 to the turbine 16.
[0018] The combustor 14 may comprise a hollow annular wall
configured to facilitate working fluid 24. For example, the
combustor 14 may include a combustor liner 40 disposed within a
flow sleeve 42. The arrangement of the combustor liner 40 and the
flow sleeve 42, as shown in FIG. 2, is generally concentric and may
define an annular passage or flow path 44 therebetween. In certain
embodiments, the flow sleeve 42 and the combustor liner 40 may
define a first or upstream hollow annular wall of the combustor 14.
The flow sleeve 42 may include a plurality of inlets 46, which
provide a flow path for at least a portion of the working fluid 24
from the compressor 12 through the discharge plenum 22 into the
flow path 44. In other words, the flow sleeve 42 may be perforated
with a pattern of openings to define a perforated annular wall. The
interior of the combustor liner 40 may define the substantially
cylindrical or annular combustion chamber 28 and at least partially
define the hot gas path 32 through which hot gas flow 30 may be
directed.
[0019] Downstream from the combustor liner 40 and the flow sleeve
42, an impingement sleeve 50 may be coupled to the flow sleeve 42.
The flow sleeve 42 may include a mounting flange 52 configured to
receive a mounting member 54 of the impingement sleeve 50. A
transition piece 56 may be disposed within the impingement sleeve
50, such that the impingement sleeve 50 surrounds the transition
piece 56. A concentric arrangement of the impingement sleeve 50 and
the transition piece 56 may define an annular passage or flow path
58 therebetween. The impingement sleeve 50 may include a plurality
of inlets 60, which may provide a flow path for at least a portion
of the working fluid 24 from the compressor 12 through the
discharge plenum 22 into the flow path 58. In other words, the
impingement sleeve 50 may be perforated with a pattern of openings
to define a perforated annular wall. Interior cavity 34 of the
transition piece 56 may further define hot gas path 32 through
which hot gas flow 30 from the combustion chamber 28 may be
directed into the turbine 16.
[0020] As shown, the flow path 58 is fluidly coupled to the flow
path 44. Thus, together, the flow paths 44 and 58 define a flow
path configured to provide working fluid 24 from the compressor 12
and the discharge plenum 22 to the fuel nozzles 26, while also
cooling the combustor 14.
[0021] As discussed above, the turbine system 10, in operation, may
intake working fluid 24 and provide the working fluid 24 to the
compressor 12. The compressor 12, which is driven by the shaft 18,
may rotate and compress the working fluid 24. The compressed
working fluid 24 may then be discharged into the diffuser 20. The
majority of the compressed working fluid 24 may then be discharged
from the compressor 12, by way of the diffuser 20, through the
discharge plenum 22 and into the combustor 14. Additionally, a
small portion (not shown) of the compressed working fluid 24 may be
channeled downstream for cooling of other components of the turbine
engine 10.
[0022] A portion of the compressed working fluid 24 within the
discharge plenum 22 may enter the flow path 58 by way of the inlets
60. The working fluid 24 in the flow path 58 may then be channeled
upstream through flow path 44, such that the working fluid 24 is
directed over the combustor liner 34. Thus, a flow path is defined
in the upstream direction by flow path 58 (formed by impingement
sleeve 50 and transition piece 56) and flow path 44 (formed by flow
sleeve 42 and combustor liner 40). Accordingly, flow path 44 may
receive working fluid 24 from both flow path 58 and inlets 46. The
working fluid 24 through the flow path 44 may then be channeled
upstream towards the fuel nozzles 26, as discussed above.
[0023] Thus, the combustor liner 40, transition piece 56, flow
sleeve 42, and impingement sleeve 50 are all sleeve components for
the combustor 14. As shown in FIG. 2, both the combustor liner 40
and the transition piece 56 are inner sleeve components 100
configured to at least partially provide a flow boundary in the
combustor 14. In general, an inner sleeve component 100 according
to the present disclosure may be configured to provide a flow
boundary by providing a physical boundary between various flows or
directions of flow in the combustor 14. In some embodiments, the
various flows or directions of flow may have different
temperatures, and the inner sleeve component 100 may thus further
provide a temperature boundary in the combustor 14.
[0024] For example, the combustor liner 40 and the transition piece
56 provide a flow boundary between the flow of working fluid 24 and
the hot gas flow 30, as discussed above. Further, the working fluid
24 is generally cooler than the hot gas flow 30, and is used to
cool the combustor liner 40 and the transition piece 56. Thus, the
combustor liner 40 and transition piece 56 further provide a
temperature boundary.
[0025] Further, as shown in FIG. 2, both the flow sleeve 42 and
impingement sleeve 50 are outer sleeve components 102. In general,
an outer sleeve component 102 is a component of the combustor 14 is
disposed adjacent an inner sleeve component 100. The outer sleeve
component 102 may act as an outer sleeve or casing for the inner
sleeve component 100, and may provide an outer boundary for flows
flowing past the inner sleeve component 100. For example, the flow
sleeve 42 and impingement sleeve 50 are outer sleeve components 102
for the combustor liner 40 and the transition piece 56,
respectively.
[0026] During operation of the turbine system, the outer sleeve
component 102 according to the present disclosure may vibrate
undesirably. Thus, devices and apparatus are needed to provide
vibratory support to the outer sleeve component 102 in order to
reduce or eliminate the vibration of the outer sleeve component
102. Thus, the present disclosure is further directed to a sleeve
component assembly 104 for the turbine system 10.
[0027] As shown in FIGS. 2 and 3, the sleeve component assembly 104
may include a sleeve component. The sleeve component may in
exemplary embodiments be an inner sleeve component 100, or
alternatively may be an outer sleeve component 102. For example, in
exemplary embodiments, as discussed above, the sleeve component may
be a transition piece 56.
[0028] The sleeve component assembly 104 further includes at least
one support feature 110. In exemplary embodiments, the sleeve
component assembly 104 includes a plurality of support features
110. Each support feature 110 extends from the sleeve component,
such as the inner sleeve component 100 or outer sleeve component
102. For example, each support feature 110 may extend from a
surface 112 of the sleeve component that faces an adjacent sleeve
component, which may be the other of the inner sleeve component 100
or the outer sleeve component 102. In exemplary embodiments wherein
the sleeve component 100 is a transition piece 56, the support
features 110 may extend from the surface 112 of the transition
piece 56 facing the adjacent impingement sleeve 50.
[0029] The support features 110 may be configured to contact and
provide vibratory support to the adjacent sleeve component. In some
embodiments, for example, the support features 110 may be
configured to generally continuously contact and provide vibratory
support to the adjacent sleeve component. The support features 110
may thus interact with the adjacent sleeve component to support the
component and reduce the structural vibrations of the
component.
[0030] For example, the support features 110 may each define a
height 114. As shown in FIG. 3, the height 114 of each support
feature 110 may allow the support feature 110 to contact and
interact with the adjacent sleeve component, such as the adjacent
outer sleeve component 102, to provide the required vibratory
support. As discussed below, the height 114 of each support feature
110 may be adjusted as desired to ensure that the support feature
110 properly supports the adjacent sleeve component.
[0031] In some embodiments, the height 114 may be adjusted such
that the support features 110 generally continuously contact and
provide vibratory support to the adjacent sleeve component. In
these embodiments, the height 114 may be such that when the turbine
system 10 is non-operational, the adjacent sleeve component and the
support features 110 are in contact. It should be understood,
however, that during operation, vibrations may cause the generally
continuously contacting support features 110 and adjacent sleeve
component to occasionally separate, and that this vibrational
movement of the support features 110 and adjacent sleeve component
relative to one another is within the scope and spirit of the
generally continuously contacting support features 110 and adjacent
sleeve component.
[0032] In other embodiments, the height 114 may be adjusted such
that the support features 110 contact and provide vibratory support
to the adjacent sleeve component during operation of the system 10.
In these embodiments, the height 114 may be such that when the
turbine system 10 is non-operational, the adjacent sleeve component
and the support features 110 are not in contact. During operation,
vibrations may cause the generally continuously contacting support
features 110 and adjacent sleeve component to occasionally contact,
and the support features 110 may thus contact and provide vibratory
support to the adjacent sleeve component.
[0033] Each support feature 110 according to the present disclosure
is integral with the sleeve component, such as with the inner
sleeve component 100 or outer sleeve component 102. Thus, the
sleeve component and the support features 110 extending therefrom
may be formed from the same materials, and may be formed together
as a singular unit. The sleeve component and the support features
110 may in exemplary embodiments be formed from a nickel or cobalt
based alloy or super alloy. Alternatively, the sleeve component and
the support features 110 may be formed from any materials suitable
for use in a combustor 14.
[0034] Further, in exemplary embodiments, the support features 110
may be formed during casting of the sleeve component. For example,
in some embodiments, the mold shells for casting the sleeve
component assembly 104 therein, as discussed below, may be designed
and configured to form a sleeve component assembly 104 including
the sleeve component and at least one support feature 110. In other
exemplary embodiments, as discussed below, the gates utilized
during casting to flow a sleeve component substrate therethrough
into the mold shells may form the support features 110. The support
features 110 may be formed by the gates during casting of the
sleeve component. The sleeve component assembly 104 may thus be
formed as an integral unit during casting.
[0035] In exemplary embodiments, each support feature 110 may be
configured to provide a desired vibratory characteristic. For
example, each support feature 110 may be individually tailored to
impart a desired vibratory characteristic onto the adjacent sleeve
component, such as the adjacent outer sleeve component 102, that
the support feature 110 is providing vibratory support to. Each
support feature 110 may be formed with a desired shape, size,
and/or height 114, and/or the location of the support feature 110
may be individually tailored, and/or the spacing between various
support features 110 may be tailored, to provide the desired
vibratory characteristic. In exemplary embodiments, the desired
vibratory characteristic may be the natural frequency of the
adjacent sleeve component, such as the adjacent outer sleeve
component 102. Each support feature 110 may be configured to raise
or lower the natural frequency of the adjacent sleeve component or
to cause the adjacent sleeve component to have a certain desired
natural frequency. For example, the height 114 of the support
features 110 may be raised to raise the natural frequency of the
adjacent sleeve component or lowered to lower the natural frequency
of the adjacent sleeve component.
[0036] It should be understood, however, that the present
disclosure is not limited to adjusting the above characteristics of
the support features 110 to adjust the natural frequency of the
adjacent sleeve component. Rather, the adjustment of any suitable
characteristics of the support features 110 to adjust any suitable
vibratory characteristics of the adjacent sleeve component are
within the scope and spirit of the present disclosure.
[0037] In exemplary embodiments, each support feature 110 may be
configured to provide a desired heat transfer characteristic. As
discussed above, the sleeve component, such as in exemplary
embodiments the inner sleeve component 102, may provide a
temperature boundary between, for example, a relatively hotter flow
and a relatively cooler flow. In embodiments wherein the sleeve
component is a transition piece 56, for example, the sleeve
component may provide a temperature boundary between a hot gas flow
30 and a working fluid 24. The support features 110 may thus be
utilized to provide desired heat transfer characteristics for the
sleeve component. Each support feature 110 may be formed with a
desired shape, size, and/or height 114, and/or the location of the
support feature 110 may be individually tailored, and/or the
spacing between various support features 110 may be tailored, to
provide the desired heat transfer characteristic. For example, it
may be desirable that the heat exchange through the sleeve
component is relatively uniform. Thus, various support features 110
may be formed as relatively thick support features 110, and may
thus act as insulators to heat cold spots on the sleeve component,
while other support features 110 may be formed as relatively thin
support features 110, and may thus act as fins to cool hot spots on
the sleeve component. The support features 110 may thus assist in
providing a relatively uniform heat exchange through the sleeve
component.
[0038] It should be understood, however, that the present
disclosure is not limited to adjusting the above characteristics of
the support features 110 to provide uniform heat exchange through
the sleeve component. Rather, the adjustment of any suitable
characteristics of the support features 110 to adjust any suitable
heat transfer characteristic of the sleeve component assembly 104
or adjacent sleeve component are within the scope and spirit of the
present disclosure.
[0039] The present disclosure is further directed to a method for
forming a sleeve component assembly 104 for a combustor 14. The
sleeve component assembly 104, as discussed above, includes a
sleeve component, such as an inner sleeve component 100 or an outer
sleeve component 102, and at least one support feature 110 or a
plurality of support features 110. Further, the sleeve component in
exemplary embodiments is a transition piece 56.
[0040] As shown in FIG. 4, the method includes, for example,
flowing a sleeve component substrate 200 into a mold 202 through at
least one gate 204, or through a plurality of gates 204. The mold
202 may comprise the gates 204 and at least one shell configured to
form the sleeve component 100. For example, in some embodiments as
shown in FIG. 4, the mold 202 may include at least one inner shell
206, or a plurality of inner shells 206, and at least one outer
shell 208, or a plurality of outer shells 208. The inner and outer
shells 206, 208 may fit together to form an interior molding area
210 therein for the sleeve component 100. The gates 204 may provide
access points through the outer shells 208 and/or the inner shells
206 for the sleeve component substrate 200 to flow into the
interior molding area 210.
[0041] The mold 202 in some embodiments may further include a pour
spout 212 or a plurality of pour spouts 212, a sprue 214 or a
plurality of sprues 214, and a runner 216 or a plurality of runners
216. The pour spouts 212 may be provided as inlets to the mold for
the sleeve component substrate 200. Thus, the component substrate
200 may be flowed through the pour spouts 212 into the mold 202 in
general. The sprues 214 and runners 216 may provide a network of
channels for the sleeve component substrate 200 to flow through
before flowing into the interior molding area 210. Thus, the sprues
214 and runners 216 may distribute the sleeve component substrate
200 through the mold 202, such that the sleeve component substrate
200 enters the interior molding area 210 relatively evenly and is
allowed to solidify relatively evenly. As discussed above, the
gates 204 provide access points through the outer shells 208 and/or
the inner shells 206 for the sleeve component substrate 200 to flow
into the interior molding area 210. Thus, the sprues 214 and/or
runners 216 may be in fluid communication with the gates 204, such
that the sleeve component substrate 200 flows from the sprues 214
and/or runners 216 through the gates 204 and generally into the
interior molding area 210.
[0042] The present method may further include solidifying, such as
curing, the sleeve component substrate 200 in the mold 202 to form
the sleeve component assembly 104. When the sleeve component
substrate 200 is flowed into the mold 202, a portion of the
substrate 200 may remain in the gates 204 rather than flow into the
interior molding area 210. When the sleeve component substrate 200
solidifies, the substrate 200 in the gates 204 may thus form the
support features 110 of the sleeve component assembly 104. Thus,
the sleeve component assembly 104 may comprise the sleeve component
and at least one support feature 110, and the support feature 110
may be integral with the sleeve component and disposed in the at
least one gate 204.
[0043] The present method may further include removing the sleeve
component assembly 104 from the mold 202. For example, the various
shells 206, 208, gates 204, and other components of the mold 202
may be removed from the sleeve component assembly 104 using any
suitable methods or devices.
[0044] The present method may further include adjusting the heights
114 of the support features 110. The heights 114 may be adjusted
such that the support features 110 are configured to provide
vibratory support in the turbine system 10. For example, the
heights 114 may be adjusted such that the support features 110 are
configured to contact and provide vibratory support to adjacent
sleeve components. To adjust the heights 114, the support features
110 may be measured and trimmed, cut, sanded, or otherwise reduced
as required so that the support features 110 contact and interact
as desired with the adjacent sleeve components.
[0045] In some embodiments, the present method may include the step
of, for example, designing the gates 204 such that the support
features 110 provide a desired vibratory characteristic. For
example, as discussed above, the support features 110 may be
configured to provide a desired vibratory characteristic. Thus,
each support feature 110 may be formed with, for example, a desired
shape, size, and/or height 114, and/or the location of the support
feature 110 may be individually tailored, and/or the spacing
between various support features 110 may be tailored, to provide
the desired vibratory characteristic. To form the support features
110 with these configurations in order to provide the desired
vibratory characteristic, the gates 204 may be sized and positioned
such that the support features 110 formed therein generally have
these configurations.
[0046] In some embodiments, the present method may include the step
of, for example, designing the gates 204 such that the support
features 110 provide a desired heat transfer characteristic. For
example, as discussed above, the support features 110 may be
configured to provide a desired heat transfer characteristic. Thus,
each support feature 110 may be formed with, for example, a desired
shape, size, and/or height 114, and/or the location of the support
feature 110 may be individually tailored, and/or the spacing
between various support features 110 may be tailored, to provide
the desired heat transfer characteristic. To form the support
features 110 with these configurations in order to provide a
desired heat transfer characteristic, the gates 204 may be sized
and positioned such that the support features 110 formed therein
generally have these configurations.
[0047] In some embodiments, the present method may include the step
of, for example, modifying the support features 110 such that the
support features 110 provide a desired vibratory characteristic.
For example, after forming of the sleeve component assembly 104,
the support features 110 may not have the appropriate
configurations to provide a desired vibratory characteristic. Thus,
various characteristics of various support features 110 such as the
shape, size, and/or height 114 may be modified, and/or various
support features 110 may be eliminated, and/or the various support
features 110 may be otherwise modified, to provide the desired
vibratory characteristic. To modify the support features 110,
various portions of the support features 110 may be removed, or the
support features 110 may be reshaped, or the support features 110
may be otherwise modified as desired.
[0048] In some embodiments, the present method may include the step
of, for example, modifying the support features 110 such that the
support features 110 provide a desired heat transfer
characteristic. For example, after forming of the sleeve component
assembly 104, the support features 110 may not have the appropriate
configurations to provide a desired heat transfer characteristic.
Thus, various characteristics of various support features 110 such
as the shape, size, and/or height 114 may be modified, and/or
various support features 110 may be eliminated, and/or the various
support features 110 may be otherwise modified, to provide the
desired heat transfer characteristic. To modify the support
features 110, various portions of the support features 110 may be
removed, or the support features 110 may be reshaped, or the
support features 110 may be otherwise modified as desired.
[0049] In exemplary embodiments, the present disclosure thus
advantageously utilizes the gates 204 of the mold 202 for forming
the sleeve component to additionally form the support features 110.
During the forming process, which may in exemplary embodiments be a
casting process, it is generally advantageous to have a multitude
of gates 204 to provide a variety of access points for a substrate
to enter the mold. More gates 204 allow for better, more uniform
solidifying of the substrate into the desired component. However,
previously, the addition of gates 204 had to be weighed against the
cost of removing the resulting protrusions from the desired
component. The present disclosure reduces this cost by requiring
that the resulting protrusions, rather than being removed, be
configured to provide vibratory support in the combustor 14. Thus,
more gates 204 may be advantageously utilized during the forming
process according to the present disclosure. More gates 204 will
provide for higher quality sleeve component assemblies 104 with
more support features 110, which may provide improved vibratory
support.
[0050] 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 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 languages of the claims.
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