U.S. patent application number 14/978044 was filed with the patent office on 2016-06-23 for gas turbine engine components and cooling cavities.
The applicant listed for this patent is United Technologies Corporation. Invention is credited to Frank J. Cunha, Stanislav Kostka.
Application Number | 20160178201 14/978044 |
Document ID | / |
Family ID | 55024888 |
Filed Date | 2016-06-23 |
United States Patent
Application |
20160178201 |
Kind Code |
A1 |
Cunha; Frank J. ; et
al. |
June 23, 2016 |
GAS TURBINE ENGINE COMPONENTS AND COOLING CAVITIES
Abstract
The present disclosure relates to gas turbine engine components
including cooling cavities. One embodiment is directed to a
component including a forward surface, an aft surface, at least one
inlet on the forward surface and a cavity between the forward
surface and the aft surface. The cavity is configured to receive
airflow from at least one inlet to provide cooling flow for the
component. The cavity includes a plurality of structures within the
cavity. The component also includes at least one exit between the
forward surface and the aft surface. The plurality of structures
are configured to meter air flow within the cavity and to maintain
the cooling effectiveness of air flow within the cavity from the at
least one inlet to the at least one exit. The component having a
cavity may be employed by a combustor of a gas turbine engine.
Inventors: |
Cunha; Frank J.; (Avon,
CT) ; Kostka; Stanislav; (Shrewsbury, MA) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
United Technologies Corporation |
Farmington |
CT |
US |
|
|
Family ID: |
55024888 |
Appl. No.: |
14/978044 |
Filed: |
December 22, 2015 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
62095529 |
Dec 22, 2014 |
|
|
|
Current U.S.
Class: |
60/752 ; 60/755;
60/806 |
Current CPC
Class: |
F23R 3/002 20130101;
F23R 3/286 20130101; F23R 3/06 20130101; F23R 3/005 20130101; F23R
2900/03043 20130101; F23R 3/26 20130101; F23R 3/04 20130101; F23R
2900/03045 20130101 |
International
Class: |
F23R 3/06 20060101
F23R003/06; F23R 3/00 20060101 F23R003/00 |
Claims
1. A gas turbine engine component including a cooling cavity, the
component comprising: a forward surface; an aft surface; at least
one inlet on the forward surface, the at least one inlet configured
to receive air flow; a cavity between the forward surface and the
aft surface, wherein the cavity is configured to receive airflow
from the at least one inlet to provide cooling flow for the
component and wherein the cavity includes a plurality of structures
within the cavity; and at least one exit between the forward
surface and the aft surface, the at least one exit configured to
allow airflow to exit the cavity, wherein the plurality of
structures are configured to meter air flow within the cavity and
to maintain the cooling effectiveness of air flow within the cavity
from the at least one inlet to the at least one exit.
2. The component of claim 1, wherein the forward surface is a cold
side of a combustor bulkhead, and the aft surface is the hot side
of the combustor bulkhead.
3. The component of claim 1, wherein the at least one inlet is
configured to receive airflow directed to a combustor of a gas
turbine engine.
4. The component of claim 1, wherein the component is a structure
including one or more edges, and wherein the cavity is positioned
proximate to an edge of the component.
5. The component of claim 4, wherein the at least one exit is a
cavity exit, and wherein the at least one exit is positioned along
the edge of the component and displaced from the at least one
inlet.
6. The component of claim 1, wherein the plurality of structures
are configured to meter air flow by directing airflow within the
cavity based on one or more of structure spacing, structure size,
structure shape, and structure pattern.
7. The component of claim 1, wherein the plurality of structures
maintains cooling effectiveness of airflow by allowing greater flow
within a first portion of the cavity and reduced flow in a second
portion of the cavity, wherein the second portion of the cavity is
associated with the at least one exit of the cavity.
8. The component of claim 1, wherein the plurality of structures
are configured to provide a cooling efficiency that increases as
the airflow traverses the cavity, wherein cooling efficiency is a
measure of heat pickup by airflow within the cavity.
9. The component of claim 1, wherein component is configured to
interface with a second component, and a plurality of structures
associated with the exit of the component are offset from a
plurality of structures associated with an exit of the second
component.
10. The component of claim 1, wherein at least a first portion of
the plurality of structures are configured to provide higher
cooling efficiency and a second portion of the plurality of
structures are configured to provide a higher cooling
effectiveness.
11. A combustor of a gas turbine engine comprising: a combustor
shell, wherein the shell is configured to engage bulkhead; and a
bulkhead including: a plurality of bulkhead panels, wherein each
bulkhead panel includes a forward surface; an aft surface; at least
one inlet on the forward surface, the at least one inlet configured
to receive air flow; a cavity between the forward surface and the
aft surface, wherein the cavity is configured to receive airflow
from the at least one inlet to provide cooling flow for the
component and wherein the cavity includes a plurality of structures
within the cavity; and at least one exit between the forward
surface and the aft surface, the at least one exit configured to
allow airflow to exit the cavity, wherein the plurality of
structures are configured to meter air flow within the cavity and
to maintain the cooling effectiveness of air flow within the cavity
from the at least one inlet to the at least one exit.
12. The combustor of claim 11, wherein the forward surface is a
cold side of a bulkhead panel, and the aft surface is the hot side
of said bulkhead panel.
13. The combustor of claim 11, wherein the at least one inlet is
configured to receive airflow directed to a combustor of a gas
turbine engine.
14. The combustor of claim 11, wherein the component is a structure
including one or more edges, and wherein the cavity is positioned
proximate to an edge of the component.
15. The combustor of claim 14, wherein the at least one exit is a
cavity exit, and wherein the at least one exit is positioned along
the edge of the component and displaced from the at least one
inlet.
16. The combustor of claim 11, wherein the plurality of structures
are configured to meter air flow by directing airflow within the
cavity based on one or more of structure spacing, structure size,
structure shape, and structure pattern.
17. The combustor of claim 11, wherein the plurality of structures
maintains cooling effectiveness of airflow by allowing greater flow
within a first portion of the cavity and reduced flow in a second
portion of the cavity, wherein the second portion of the cavity is
associated with the at least one exit of the cavity.
18. The combustor of claim 11, wherein the plurality of structures
are configured to provide a cooling efficiency that increases as
the airflow traverses the cavity, wherein cooling efficiency is a
measure of heat pickup by airflow within the cavity.
19. The combustor of claim 11, wherein component is configured to
interface with a second component, and a plurality of structures
associated with the exit of the component are offset from a
plurality of structures associated with an exit of the second
component.
20. The combustor of claim 11, wherein at least a first portion of
the plurality of structures are configured to provide higher
cooling efficiency and a second portion of the plurality of
structures are configured to provide a higher cooling
effectiveness.
Description
CROSS REFERENCE TO RELATED APPLICATIONS
[0001] This application claims the benefit of U.S. Provisional
Patent Application No. 62/095,529 filed on Dec. 22, 2014, the
entire contents of which are incorporated herein by reference
thereto.
FIELD
[0002] The present disclosure relates to components of a gas
turbine engine and, in particular, a component having a cooling
cavity.
BACKGROUND
[0003] Gas turbine engine combustors are required to operate
efficiently during engine operation and flight. Combustors are
locations of tremendous amounts of heat. Combustors also
experienced a high degree of heat and distress. High heat exposure
to the combustor may cause loss of protective thermal barrier
coating which leads to exposure to a hot gas environment. This, in
turn, leads to deformities of the combustor which have an adverse
effect on cooling airflow and back side heat transfer coefficients.
Film cooling alone may not remedy this situation and may worsen the
condition due to the addition of more air (and oxygen) which could
increase combustion temperature.
[0004] Accordingly, it is desirable to provide components which
minimize or limit heat exposure causing deformities and maximizing
cooling airflow within a gas turbine engine.
BRIEF SUMMARY OF THE EMBODIMENTS
[0005] Disclosed and claimed herein are components for a gas
turbine engine. One embodiment is directed to a component including
a cooling cavity. The component includes a forward surface, an aft
surface, and at least one inlet on the forward surface, the at
least one inlet configured to receive air flow. The component
includes a cavity between the forward surface and the aft surface,
wherein the cavity is configured to receive airflow from the at
least one inlet to provide cooling flow for the component and
wherein the cavity includes a plurality of structures within the
cavity. The component includes at least one exit between the
forward surface and the aft surface, the at least one exit
configured to allow airflow to exit the cavity, wherein the
plurality of structures are configured to meter air flow within the
cavity and to maintain the cooling effectiveness of air flow within
the cavity from the at least one inlet to the at least one
exit.
[0006] In one embodiment, the forward surface is a cold side of a
combustor bulkhead, and the aft surface is the hot side of the
combustor bulkhead.
[0007] In one embodiment, the at least one inlet is configured to
receive airflow directed to a combustor of a gas turbine
engine.
[0008] In one embodiment, the component is a structure including
one or more edges, and wherein the cavity is positioned proximate
to an edge of the component.
[0009] In one embodiment, the at least one exit is a cavity exit,
and wherein the at least one exit is positioned along the edge of
the component and displaced from the at least one inlet.
[0010] In one embodiment, the plurality of structures are
configured to meter air flow by directing airflow within the cavity
based on one or more of structure spacing, structure size,
structure shape, and structure pattern.
[0011] In one embodiment, the plurality of structures maintains
cooling effectiveness of airflow by allowing greater flow within a
first portion of the cavity and reduced flow in a second portion of
the cavity, wherein the second portion of the cavity is associated
with the at least one exit of the cavity.
[0012] In one embodiment, the plurality of structures are
configured to provide a cooling efficiency that increases as the
airflow traverses the cavity, wherein cooling efficiency is a
measure of heat pickup by airflow within the cavity.
[0013] In one embodiment, component is configured to interface with
a second component, and a plurality of structures associated with
the exit of the component are offset from a plurality of structures
associated with an exit of the second component.
[0014] In one embodiment, at least a first portion of the plurality
of structures are configured to provide higher cooling efficiency
and a second portion of the plurality of structures are configured
to provide a higher cooling effectiveness.
[0015] Another embodiment is directed to a combustor of a gas
turbine engine. The combustor includes a combustor shell, wherein
the shell is configured to engage bulkhead and a bulkhead. The
bulkhead includes a plurality of bulkhead panels. Each bulkhead
panel includes a forward surface, an aft surface, and at least one
inlet on the forward surface, the at least one inlet configured to
receive air flow. Each bulkhead panel includes a cavity between the
forward surface and the aft surface, wherein the cavity is
configured to receive airflow from the at least one inlet to
provide cooling flow for the component and wherein the cavity
includes a plurality of structures within the cavity. Each bulkhead
panel includes at least one exit between the forward surface and
the aft surface, the at least one exit configured to allow airflow
to exit the cavity, wherein the plurality of structures are
configured to meter air flow within the cavity and to maintain the
cooling effectiveness of air flow within the cavity from the at
least one inlet to the at least one exit.
[0016] In one embodiment, the forward surface is a cold side of a
bulkhead panel, and the aft surface is the hot side of said
bulkhead panel.
[0017] In one embodiment, the at least one inlet is configured to
receive airflow directed to a combustor of a gas turbine
engine.
[0018] In one embodiment, the component is a structure including
one or more edges, and wherein the cavity is positioned proximate
to an edge of the component.
[0019] In one embodiment, the at least one exit is a cavity exit,
and wherein the at least one exit is positioned along the edge of
the component and displaced from the at least one inlet.
[0020] In one embodiment, the plurality of structures are
configured to meter air flow by directing airflow within the cavity
based on one or more of structure spacing, structure size,
structure shape, and structure pattern.
[0021] In one embodiment, the plurality of structures maintains
cooling effectiveness of airflow by allowing greater flow within a
first portion of the cavity and reduced flow in a second portion of
the cavity, wherein the second portion of the cavity is associated
with the at least one exit of the cavity.
[0022] In one embodiment, the plurality of structures are
configured to provide a cooling efficiency that increases as the
airflow traverses the cavity, wherein cooling efficiency is a
measure of heat pickup by airflow within the cavity.
[0023] In one embodiment, component is configured to interface with
a second component, and a plurality of structures associated with
the exit of the component are offset from a plurality of structures
associated with an exit of the second component.
[0024] In one embodiment, at least a first portion of the plurality
of structures are configured to provide higher cooling efficiency
and a second portion of the plurality of structures are configured
to provide a higher cooling effectiveness.
[0025] In one embodiment, a gas turbine engine component including
a cooling cavity is provided. The component having: a forward
surface; an aft surface; at least one inlet on the forward surface,
the at least one inlet configured to receive air flow; a cavity
between the forward surface and the aft surface, wherein the cavity
is configured to receive airflow from the at least one inlet to
provide cooling flow for the component and wherein the cavity
includes a plurality of structures within the cavity; and at least
one exit between the forward surface and the aft surface, the at
least one exit configured to allow airflow to exit the cavity,
wherein the plurality of structures are configured to meter air
flow within the cavity and to maintain the cooling effectiveness of
air flow within the cavity from the at least one inlet to the at
least one exit.
[0026] In addition to one or more of the features described above,
or as an alternative to any of the foregoing embodiments, the
forward surface is a cold side of a combustor bulkhead, and the aft
surface is the hot side of the combustor bulkhead.
[0027] In addition to one or more of the features described above,
or as an alternative to any of the foregoing embodiments, the at
least one inlet is configured to receive airflow directed to a
combustor of a gas turbine engine.
[0028] In addition to one or more of the features described above,
or as an alternative to any of the foregoing embodiments, the
component is a structure including one or more edges, and wherein
the cavity is positioned proximate to an edge of the component.
[0029] In addition to one or more of the features described above,
or as an alternative to any of the foregoing embodiments, the at
least one exit is a cavity exit, and wherein the at least one exit
is positioned along the edge of the component and displaced from
the at least one inlet.
[0030] In addition to one or more of the features described above,
or as an alternative to any of the foregoing embodiments, the
plurality of structures are configured to meter air flow by
directing airflow within the cavity based on one or more of
structure spacing, structure size, structure shape, and structure
pattern.
[0031] In addition to one or more of the features described above,
or as an alternative to any of the foregoing embodiments, the
plurality of structures maintains cooling effectiveness of airflow
by allowing greater flow within a first portion of the cavity and
reduced flow in a second portion of the cavity, wherein the second
portion of the cavity is associated with the at least one exit of
the cavity.
[0032] In addition to one or more of the features described above,
or as an alternative to any of the foregoing embodiments, the
plurality of structures are configured to provide a cooling
efficiency that increases as the airflow traverses the cavity,
wherein cooling efficiency is a measure of heat pickup by airflow
within the cavity.
[0033] In addition to one or more of the features described above,
or as an alternative to any of the foregoing embodiments, the
component is configured to interface with a second component, and a
plurality of structures associated with the exit of the component
are offset from a plurality of structures associated with an exit
of the second component.
[0034] In addition to one or more of the features described above,
or as an alternative to any of the foregoing embodiments, at least
a first portion of the plurality of structures is configured to
provide higher cooling efficiency and a second portion of the
plurality of structures are configured to provide a higher cooling
effectiveness.
[0035] In yet another embodiment, a combustor of a gas turbine
engine is provided. The combustor having: a combustor shell,
wherein the shell is configured to engage bulkhead; and a bulkhead
including: a plurality of bulkhead panels, wherein each bulkhead
panel includes a forward surface; an aft surface; at least one
inlet on the forward surface, the at least one inlet configured to
receive air flow; a cavity between the forward surface and the aft
surface, wherein the cavity is configured to receive airflow from
the at least one inlet to provide cooling flow for the component
and wherein the cavity includes a plurality of structures within
the cavity; and at least one exit between the forward surface and
the aft surface, the at least one exit configured to allow airflow
to exit the cavity, wherein the plurality of structures are
configured to meter air flow within the cavity and to maintain the
cooling effectiveness of air flow within the cavity from the at
least one inlet to the at least one exit.
[0036] In addition to one or more of the features described above,
or as an alternative to any of the foregoing embodiments, the
forward surface is a cold side of a bulkhead panel, and the aft
surface is the hot side of said bulkhead panel.
[0037] In addition to one or more of the features described above,
or as an alternative to any of the foregoing embodiments, the at
least one inlet is configured to receive airflow directed to a
combustor of a gas turbine engine.
[0038] In addition to one or more of the features described above,
or as an alternative to any of the foregoing embodiments, the
component is a structure including one or more edges, and wherein
the cavity is positioned proximate to an edge of the component.
[0039] In addition to one or more of the features described above,
or as an alternative to any of the foregoing embodiments, the at
least one exit is a cavity exit, and wherein the at least one exit
is positioned along the edge of the component and displaced from
the at least one inlet.
[0040] In addition to one or more of the features described above,
or as an alternative to any of the foregoing embodiments, the
plurality of structures are configured to meter air flow by
directing airflow within the cavity based on one or more of
structure spacing, structure size, structure shape, and structure
pattern.
[0041] In addition to one or more of the features described above,
or as an alternative to any of the foregoing embodiments, the
plurality of structures maintains cooling effectiveness of airflow
by allowing greater flow within a first portion of the cavity and
reduced flow in a second portion of the cavity, wherein the second
portion of the cavity is associated with the at least one exit of
the cavity.
[0042] In addition to one or more of the features described above,
or as an alternative to any of the foregoing embodiments, the
plurality of structures are configured to provide a cooling
efficiency that increases as the airflow traverses the cavity,
wherein cooling efficiency is a measure of heat pickup by airflow
within the cavity.
[0043] In addition to one or more of the features described above,
or as an alternative to any of the foregoing embodiments, the
component is configured to interface with a second component, and a
plurality of structures associated with the exit of the component
are offset from a plurality of structures associated with an exit
of the second component.
[0044] In addition to one or more of the features described above,
or as an alternative to any of the foregoing embodiments, at least
a first portion of the plurality of structures are configured to
provide higher cooling efficiency and a second portion of the
plurality of structures are configured to provide a higher cooling
effectiveness.
[0045] Other aspects, features, and techniques will be apparent to
one skilled in the relevant art in view of the following detailed
description of the embodiments.
BRIEF DESCRIPTION OF THE DRAWINGS
[0046] The features, objects, and advantages of the present
disclosure will become more apparent from the detailed description
set forth below when taken in conjunction with the drawings in
which like reference characters identify correspondingly throughout
and wherein:
[0047] FIG. 1 depicts a graphical representation of a gas turbine
engine according to one or more embodiments;
[0048] FIGS. 2A-2C depict graphical representations of a component
according to one or more embodiments;
[0049] FIGS. 2D-2E depict structures of a component according to
one or more embodiments; and
[0050] FIGS. 3A-3B depict graphical representations of a bulkhead
according to one or more embodiments.
DETAILED DESCRIPTION OF THE EXEMPLARY EMBODIMENTS
Overview and Terminology
[0051] One aspect of this disclosure relates to components of a gas
turbine engine, and in particular components with cooling cavities.
One or more structural configurations are provided for components
to allow for cooling with a cavity or plenum of the component. The
cavity position and structures may allow for particular areas
within a gas turbine engine or high temperature environment to
receive cooling flow. According to another embodiment,
configurations are provided to meter airflow and maintain cooling
efficiency within a cavity of a component, such as a bulkhead.
[0052] According to another embodiment, configurations are provided
for components, such as combustors of gas turbine engines. By way
of example, a combustor including a combustor shell may include one
or more cavities in the bulkhead or bulkhead panels of the
combustor. Although components are described as bulkhead
components, it should be appreciated that the principles may apply
to other components.
[0053] A cavity as used herein related to an area or plenum within
a structural component. In the context of a bulkhead, the cavity is
in between the forward and aft surfaces of the bulkhead.
[0054] As used herein, the terms "a" or "an" shall mean one or more
than one. The term "plurality" shall mean two or more than two. The
term "another" is defined as a second or more. The terms
"including" and/or "having" are open ended (e.g., comprising). The
term "or" as used herein is to be interpreted as inclusive or
meaning any one or any combination. Therefore, "A, B or C" means
"any of the following: A; B; C; A and B; A and C; B and C; A, B and
C". An exception to this definition will occur only when a
combination of elements, functions, steps or acts are in some way
inherently mutually exclusive.
[0055] Reference throughout this document to "one embodiment,"
"certain embodiments," "an embodiment," or similar term means that
a particular feature, structure, or characteristic described in
connection with the embodiment is included in at least one
embodiment. Thus, the appearances of such phrases in various places
throughout this specification are not necessarily all referring to
the same embodiment. Furthermore, the particular features,
structures, or characteristics may be combined in any suitable
manner on one or more embodiments without limitation.
Exemplary Embodiments
[0056] Referring now to the figures, FIG. 1 depicts a graphical
representation of a gas turbine engine 100 according to one or more
embodiments. A cross-sectional representation is provided for
components of gas turbine engine 100. Gas turbine engine 100
includes a combustor 105 which may include one or more combustor
shells, such as combustor shell 110. Components of a gas turbine
engine, such as combustor 105 combustor shell 110, and gas turbine
engine components in general, may be configured to include one or
more features to allow for cooling. According to one embodiment,
structural configurations are provided for cavities to allow for
cooling, and in particular, providing components with a cavity
including one or more structural elements within the cavity to
meter air flow within the cavity. According to an exemplary
embodiment, and as described herein, a cooling cavity may be
employed by components of a hot section of gas turbine engine 100,
such as combustor 105. It should be appreciated though, that a
cooling cavity, and components including a cavity with structural
elements as described herein, may be employed with other types of
components and non-gas turbine engine components in general.
[0057] Combustor 105 of FIG. 1 includes combustor shell 110.
Combustor 105 may include a plurality of combustion chambers or
shells, such as combustor shell 110. Combustor shell 110 receives
fuel injector 120 and provides an area for combustion of fuel and
gases within the shell. Accordingly, portions of combustor shell
110 are exposed to high temperatures which can lead to distress.
Film cooling may be applied to portions of combustor shell 110,
however, portions of the combustor shell may experience more stress
than others. By way of example, bulkhead 115 of combustor shell 110
may experience distress and possibly wear due to inadequate film
cooling. Configurations including a cavity as described herein may
provide additional cooling to one or more regions of a component
that experience higher levels of distress and wear.
[0058] Bulkhead 115 is depicted as a an annular component including
an outer circumferential surface, such as outer rail 116, inner
circumferential surface, such as inner rail 117 and opening 118.
Bulkhead 115 may be the bulkhead for combustor shell 110.
[0059] Gas turbine engine 100 may include a plurality of combustors
and/or combustor shells 110. Gas turbine engine 100 may direct
airflow, shown as airflow 125 towards combustor 105 and in
particular combustor shell 110. Output airflow of combustor shell
110 is shown as airflow 130. According to one embodiment, a
component of a gas turbine engine, such as bulkhead 115 may include
one or more inlets to received airflow, such as air flow 125.
According to one embodiment, the inlets may be on a forward
surface, shown as 135, of bulkhead 115. The component may have an
aft surface, shown as 140. The component, such as bulkhead 115 may
include a cavity between forward surface 135 (cold side) and aft
surface 140 (hot side).
[0060] Referring now to FIGS. 2A-2E, FIGS. 2A-2C depict graphical
representations of a component according to one or more
embodiments. FIGS. 2D-2E depict structures of the component
according to one or more embodiments.
[0061] FIG. 2A depicts a representation of a component 200.
According to one embodiment, component 200 may be a component of a
gas turbine engine (e.g., gas turbine engine 100), such as a
bulkhead (e.g., bulkhead 115). As such, component 200 may relate to
a section or panel of a bulkhead, such as a bulkhead panel or the
bulkhead itself. In certain embodiments, component 200 may be part
of an annular component, such as an annular bulkhead, and annular
components in general.
[0062] Acceding to one embodiment, component 200 includes a cavity
205 which may be a cooling cavity for component 200. Component 200
includes one or more inlets for cavity 205, such as inlets 210
configured to receive airflow 215 (e.g., airflow 125). Cavity 205
provides a passageway for air flow 215 to cool the component,
including the forward and aft surfaces of the component, in the
area associated with the cavity. Cavity 205 also allows airflow
within the cavity to exit as shown by 216 via one or more of exits
211. Cavity 205 may occupy a portion of the component 205.
Components may include multiple cavities per component.
[0063] Component 200 includes forward surface 220 which can include
at least one inlet 210. Component also includes an aft surface
(represented as 240). Air directed to and/or flowing toward forward
surface 220, such as airflow directed to a combustor of a gas
turbine engine, may be received by inlets 210. Component 200
includes at least one exit 211 between the forward surface 220 and
the aft surface 240. The at least one exit 211 may be configured to
allow airflow within the cavity 205 to exit the cavity. According
to one embodiment, exits 211 are offset or displaced from inlets
210. Exits 211 may be cavity exits and may be positioned along the
edge of component 200 and such that exits 211 are displaced from
the at least one inlet 210.
[0064] The position of cavity 205 may be based on areas of
component 200 that need additional cooling. In the context of a gas
turbine engine component and in particular a bulkhead, cavity 205
may be associated with positions of a bulkhead or bulkhead panel
that need additional cooling. Component 200 may be a structure
including one or more edges, and cavity 205 may be positioned
proximate to an edge of the component. Component 200 may optionally
include opening 225 (e.g., opening 118) such as a fuel injector
opening. In certain embodiments, cavity 205 may be positioned
relative to opening 225. By way of example, opening 225 may be an
opening for fuel injector, such that distress in the component 200
due to combustion from the fuel injector may be modeled and/or
determined. Cavity 205 may be associated with locations of distress
for component 200. According to another embodiment, cavity 205 may
be position between rails 230 (e.g., outer circumferential edge)
and rail 235 (e.g., inner circumferential edge) of the component
200.
[0065] Cavity 205 may be provided between the forward surface 220
and the aft surface 240. Cavity 205 may be configured to receive
airflow 215 from the at least one inlet 210 to provide cooling flow
for the component 200 and wherein the cavity 205 includes a
plurality of structures within the cavity. As will be described in
more detail below, component 200 may include one or more structures
internal to the cavity 205. In certain embodiments, cavity 205 may
be formed by a refractory metal core, such that structures are
formed within the cavity during a casting or manufacturing process
of component 200. Cavity 205 may be a plenum, such as a plenum
cooling space formed by a refractory metal core during a casting or
formation process.
[0066] According to certain embodiments, component 200 may
interface with one or more similar components (e.g., panels). FIG.
2B depicts a configuration of component 200 with cavity 205
relative to component 201 with cavity 206. Component 200 is
configured to interface with a second component, component 201, and
a plurality of structures associated with the exit of the component
200 may be offset from a plurality of structures associated with an
exit of the second component 201. Components 200 and 201 may be
bulkhead panels, for example. According to one embodiment,
components 200 and 201 may include cavities 205 and 206,
respectively to provide cooling. Airflow exits of components 200
and 201 are shown as 216 and 217, respectively. According to one
embodiment, structures within cavities 205 and 206 may be arranged
to allow for airflows 216 and 217 to efficiently exit. For example,
structures within cavities 205 and 206 may be configured to stagger
the exit points of airflows 216 and 217.
[0067] FIG. 2C depicts structures of cavities 205 and 206 according
to one or more embodiments. Each cavity may include a plurality of
structures. FIG. 2C depicts an exemplary representation (cut-away
view) of structures for each of cavities 205 and 206.
[0068] Cavity 205 includes a plurality of structures, shown as
structures 250 and 255 configured to meter airflow within cavity
205. Cavity 205 may receive airflow form inlets 210. Airflow within
cavity 205 is shown as 245. Airflow 245 then exits cavity 205 and
is shown as 216 relative to exits 211. Structures 250 and 255 of
cavity 205 may be cylindrical pillars position in order to meter
flow. Structures 250 are configured to meter air flow by directing
airflow within cavity 205 based on one or more of structure
spacing, structure size, structure shape, and structure pattern.
Structures 255 operate similar to structures 250. Structures 255
are at least one of a cylindrical and oblong shape. Structures 255
are positioned near an exit area of cavity 205. According to one
embodiment structures 255 may be shaped to control airflow 216 that
exits cavity 205.
[0069] Cavity 206 includes a plurality of structures, shown as
structures 251 and 256 configured to meter airflow within cavity
206. Structures 251 and 256 of cavity 206 may operate similarly to
structures of cavity 205. Cavity 206 may receive airflow from
inlets 210 and airflow within cavity 206 is shown as 246. Airflow
246 then exits cavity 206 and is shown as 217 relative to exits of
cavity 206. Structures 251 and 256 of cavity 206 may be cylindrical
pillars position in order to meter flow. According to another
embodiment structures 255 of cavity 205 may be positioned in an
alternating location with structures 256 of cavity 206.
[0070] FIG. 2D depicts a representation of structures within a
cavity according to one or more embodiments. Structures 250 may be
configured to meter air flow within the cavity and to maintain the
cooling effectiveness of air flow within the cavity from the at
least one inlet to the at least one exit. Cooling flow 265 may be
based on airflow received by inlets for a cavity. One embodiment is
directed to providing an arrangement of structures to maintain the
ability of cooling flow 265 within a cavity such that air flow 267
exiting cavity may cool the component. According to one embodiment,
structures 250 may be arranged in sections. Structures 250 may also
be arranged in rows or formations. FIG. 2D depicts an exemplary
division 266 separating structures into first portion 268 and
second portion 269. By arranging structures to maintain cooling
efficiency, cooling flow 270 near the exit of the cavity may retain
the ability to provide cooling effectiveness for the component. In
that fashion, structures 250 are configured to meter airflow within
a cavity and to provide a cooling effectiveness that increases
towards a rail or exit of the cavity, such that cooling
effectiveness is the capacity to cool a portion of component.
[0071] FIG. 2E depicts a graphical representation of structures 250
within a cavity of a component. According to one embodiment and
regarding cooling provided by structures, a portion of the
structures may be associated with providing high efficiency
cooling, and a portion of the structures within the cavity may be
configured to provide high effectiveness. Structures 250 maintain
cooling effectiveness of airflow by allowing greater flow within a
first portion of the cavity and reduced flow in a second portion of
the cavity, wherein the second portion of the cavity is associated
with the at least one exit of the cavity. Structures may also be
configured to provide a cooling efficiency that increases as the
airflow traverses the cavity, wherein cooling efficiency is a
measure of heat pickup by airflow within the cavity. For example, a
first portion of structures may be configured to provide higher
cooling efficiency and a second portion of the plurality of
structures may be configured to provide a higher cooling
effectiveness.
[0072] Structures 250 may be arranged such that a portion of the
structures (e.g., rows 1-3) provide cooling with higher efficiency,
shown as 280. According to another embodiment, Structures 250 may
be arranged such that a portion of the structures (e.g., rows 4-6)
provide cooling with higher effectiveness, shown as 287. Structures
250 associated with section 280 may be populated more densely,
compared to the arrangement of structures in section 287 to provide
effective and efficient heat transfer. In that fashion, the air
flow may be controlled within a cavity.
[0073] FIGS. 3A-3B depict graphical representations of a bulkhead
according to one or more embodiments. According to one embodiment,
bulkhead 300 may include one or more cavities to provide cooling.
FIG. 3A depicts a forward surface 301 of bulkhead 300. Bulkhead 300
may be an annular structure. Bulkhead 300 may include a plurality
of bulkhead panels 305.sub.1-n. Bulkhead 300 may be associated with
the bulkhead of a combustor shell of a gas turbine engine (e.g.,
gas turbine engine 100). Bulkhead 300 is represented as an annular
bulkhead including a plurality of combustor panels 305.sub.1-n.
Bulkhead 300 and panels 305.sub.1-n may be arranged around a
rotating axial shaft in opening 316 of gas turbine engine.
[0074] FIG. 3A depicts inlets 310 which may be configured to
receive air flow for a cavity within a panel of bulkhead 300.
Inlets 310 are shown near the edge of bulkhead 300. The position of
inlets 310 may be associated with the position of cavities within
panels 305.sub.1-n. The position of inlets 310 may be exemplary.
Inlets of bulkhead 300 may be positioned in other portions of
panels 305. Exemplary inlet positions, which are optional, for
bulkhead 300 are shown as 311. Surface 301 may be a forward surface
of the bulkhead 300. Bulkhead 300 is shown with openings 320 for
fuel injectors, with inner circumferential rail 315, panel rail 325
between bulkhead panels, opening 316, and outer circumferential
rail 330.
[0075] FIG. 3B depicts an aft or back surface 302 of bulkhead 300.
Bulkhead 300 may include one or more cavities between forward
surface 301 and aft surface 302. Exemplary positions for cavities
are shown as 335 and 340 for bulkhead 300. These locations may be
areas that may be susceptible to distress and/or wear within a
combustor shell. However, it should be appreciated that these areas
are exemplary, and that cavities may be position in other locations
of bulkhead 300. Positions 335 relate to positions along an outer
circumferential rail 330. Positions 340 relate to positions between
panels and associated with panel rails 325. When cavities are
associated with positions between panels, such as panel rails 325,
the structural elements of adjoining panels may be offset within
the cavities to allow for alternating exits paths of airflow.
[0076] While this disclosure has been particularly shown and
described with references to exemplary embodiments thereof, it will
be understood by those skilled in the art that various changes in
form and details may be made therein without departing from the
scope of the claimed embodiments.
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