U.S. patent application number 14/639742 was filed with the patent office on 2016-09-08 for combustor and heat shield configurations for a gas turbine engine.
The applicant listed for this patent is UNITED TECHNOLOGIES CORPORATION. Invention is credited to James B. HOKE, Timothy S. SNYDER, Robert M. SONNTAG, James S. TU.
Application Number | 20160258623 14/639742 |
Document ID | / |
Family ID | 55484931 |
Filed Date | 2016-09-08 |
United States Patent
Application |
20160258623 |
Kind Code |
A1 |
TU; James S. ; et
al. |
September 8, 2016 |
COMBUSTOR AND HEAT SHIELD CONFIGURATIONS FOR A GAS TURBINE
ENGINE
Abstract
The present disclosure relates to combustor and heat shield
configurations for gas turbine engines. A heat shield for a gas
turbine engine can include one or more effusion holes downstream of
a dilution hole to restore a cooling film applied to the heat
shield in the combustor. Effusion holes may be clustered in one or
more configurations and rows following each dilution hole and/or on
a trailing edge of each heat shield panel structure. One or more
embodiments are directed to effusion holes positioned along a
trailing edge of a heat shield panel.
Inventors: |
TU; James S.; (West
Hartford, CT) ; HOKE; James B.; (Tolland, CT)
; SONNTAG; Robert M.; (Bolton, CT) ; SNYDER;
Timothy S.; (Glastonbury, CT) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
UNITED TECHNOLOGIES CORPORATION |
Farmington |
CT |
US |
|
|
Family ID: |
55484931 |
Appl. No.: |
14/639742 |
Filed: |
March 5, 2015 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F23R 3/06 20130101; F23R
3/04 20130101; F23R 2900/03041 20130101; F23R 3/002 20130101; F23R
2900/03042 20130101 |
International
Class: |
F23R 3/00 20060101
F23R003/00; F23R 3/04 20060101 F23R003/04 |
Claims
1. A heat shield for a combustor of a gas turbine engine, the heat
shield comprising: a panel structure having a surface configured to
face a combustor cavity, the surface of the panel structure
configured to receive cooling airflow; a dilution hole in the
surface of the panel structure, the dilution hole to provide
airflow for the combustor cavity; and one or more effusion holes in
the panel structure, wherein the one or more effusion holes are
downstream of the dilution hole, wherein the one or more effusion
holes are configured to restore cooling airflow to the surface of
the panel structure downstream from dilution hole.
2. The heat shield of claim 1, wherein the panel structure is
configured to be mounted downstream from a second panel structure,
the second panel structure arranged to provide a cooling air film
to the surface.
3. The heat shield of claim 1, wherein the one or more effusion
holes are located in one or more rows, and wherein each row
includes one or more effusion holes.
4. The heat shield of claim 1, wherein the one or more effusion
holes are located in one or more regions following the dilution
hole.
5. The heat shield of claim 1, wherein the one or more effusion
holes are formed with at least one of a trumpet and cone shape.
6. The heat shield of claim 1, wherein the one or more effusion
holes include at least one pair of effusion holes angled towards
one another.
7. The heat shield of claim 1, wherein the one or more effusion
holes are formed with openings smaller than an opening of the
dilution hole.
8. The heat shield of claim 1, further comprising one or more
effusion holes along a trailing edge of the panel structure and
downstream of the dilution hole.
9. A combustor of a gas turbine engine, the combustor comprising: a
combustor structure including a combustor cavity; and one or more
panels lining the combustor shell structure, wherein each panel is
configured to include a panel structure having a surface configured
to face the combustor cavity, the surface of the panel structure
configured to receive cooling airflow, a dilution hole in the
surface of the panel structure, the dilution hole to provide
airflow for the combustor cavity; and one or more effusion holes
downstream of the dilution hole, wherein the one or more effusion
holes are configured to restore cooling airflow to the surface of
the panel structure downstream from dilution hole.
10. The combustor of claim 9, wherein the combustor structure is an
annular structure including one or more heat shield panels mounted
to an inner diameter structure and outer diameter structure of the
annular structure.
11. The combustor of claim 9, wherein the panel structure is
configured to be mounted downstream from a second panel structure,
the second panel structure arranged to provide a cooling air film
to the surface.
12. The combustor of claim 9, wherein the one or more effusion
holes are located in one or more rows, and wherein each row
includes one or more effusion holes.
13. The combustor of claim 9, wherein the one or more effusion
holes are located in one or more regions following the dilution
hole.
14. The combustor of claim 9, wherein the one or more effusion
holes are formed with at least one of a trumpet and cone shape.
15. The combustor of claim 9, wherein the one or more effusion
holes include at least one pair of effusion holes angled towards
one another.
16. The combustor of claim 9, wherein the one or more effusion
holes are formed with openings smaller than an opening of the
dilution hole.
17. The combustor of claim 9, further comprising one or more
effusion holes along a trailing edge of the panel structure and
downstream of the dilution hole.
18. The combustor of claim 9, wherein the one or more panels line
second and third rows of the combustor shell structure.
Description
FIELD
[0001] The present disclosure relates to gas turbine engines, and
in particular, combustor and heat shield configurations for gas
turbine engines.
BACKGROUND
[0002] Gas turbine engines are required to operate efficiently
during operation and flight. Theses engines create a tremendous
amount of force and generate high levels of heat. As such,
components of these engines are subjected to high levels of stress,
temperature and pressure. It is necessary to provide combustor
components that can withstand the demands of high levels of heat,
stress, temperature, and pressure during operation of a gas turbine
engine. It is also desirable to provide components with increased
operating longevity.
[0003] Hot section components of a gas turbine engine are exposed
to high temperature levels for prolonged periods of time. Thermal
mechanical failure of a part can be detrimental to an engines
operation and in some cases may result in catastrophic harm. In
many cases, part failure to distress within the hot section
requires replacement and in some cases overhaul of an entire part
or assembly. Thus, there is a desire to improve tolerance of gas
turbine engine parts and their ability to withstand operation in
the hot section.
BRIEF SUMMARY OF THE EMBODIMENTS
[0004] Disclosed and claimed herein are combustor and heat shield
configurations for a gas turbine engine. In one embodiment, a heat
shield for a combustor of a gas turbine engine includes a panel
structure having a surface configured to face a combustor cavity,
the surface of the panel structure configured to receive cooling
airflow, and a dilution hole in the surface of the panel structure,
the dilution hole to provide airflow for the combustor cavity. The
heat shield includes one or more effusion holes downstream of the
dilution hole, wherein the one or more effusion holes are
configured to restore cooling airflow to the surface of the panel
structure downstream from dilution hole.
[0005] In one embodiment, the panel structure is configured to be
mounted downstream from a second panel structure, the second panel
structure arranged to provide a cooling air film to the
surface.
[0006] In one embodiment, the one or more effusion holes are
located in one or more rows, and wherein each row includes one or
more effusion holes.
[0007] In one embodiment, the one or more effusion holes are
located in one or more regions following the dilution hole.
[0008] In one embodiment, the one or more effusion holes are formed
with at least one of a trumpet and cone shape.
[0009] In one embodiment, the one or more effusion holes include at
least one pair of effusion holes angled towards one another.
[0010] In one embodiment, the one or more effusion holes are formed
with openings smaller than an opening of the dilution hole.
[0011] In one embodiment, the heat shield includes one or more
effusion holes along a trailing edge of the panel structure and
downstream of the dilution hole.
[0012] One embodiment is directed to a combustor for a gas turbine
engine. The combustor includes a combustor shell structure
including a combustor cavity, and one or more panels lining the
combustor shell structure. Each panel is configured to include a
panel structure having a surface configured to face the combustor
cavity, the surface of the panel structure configured to receive
cooling airflow and a dilution hole in the surface of the panel
structure, the dilution hole to provide airflow for the combustor
cavity. Each panel includes one or more effusion holes downstream
of the dilution hole, wherein the one or more effusion holes are
configured to restore cooling airflow to the surface of the panel
structure downstream from dilution hole.
[0013] In one embodiment, the combustor structure is an annular
structure including one or more heat shield panels mounted to an
inner diameter structure and outer diameter structure of the
annular structure.
[0014] In one embodiment, the panel structure is configured to be
mounted downstream from a second panel structure, the second panel
structure arranged to provide a cooling air film to the
surface.
[0015] In one embodiment, the one or more effusion holes are
located in one or more rows, and wherein each row includes one or
more effusion holes.
[0016] In one embodiment, the one or more effusion holes are
located in one or more regions following the dilution hole.
[0017] In one embodiment, the one or more effusion holes are formed
with at least one of a trumpet and cone shape.
[0018] In one embodiment, the one or more effusion holes include at
least one pair of effusion holes angled towards one another.
[0019] In one embodiment, the one or more effusion holes are formed
with openings smaller than an opening of the dilution hole.
[0020] In one embodiment, the combustor includes one or more
effusion holes along a trailing edge of the panel structure and
downstream of the dilution hole.
[0021] In one embodiment, the one or more panels line second and
third rows of the combustor shell structure
[0022] 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
[0023] 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:
[0024] FIG. 1 depicts a graphical representation of a gas turbine
engine according to one or more embodiments;
[0025] FIGS. 2A-2B depict graphical representations a heat shield
according to one or more embodiments;
[0026] FIG. 3 depicts a cross-sectional representation of a heat
shield configuration according to one or more embodiments; and
[0027] FIG. 4 depicts a graphical representation of a combustor
configuration according to one or more embodiments.
DETAILED DESCRIPTION OF THE EXEMPLARY EMBODIMENTS
Overview and Terminology
[0028] One aspect of this disclosure relates to combustor and heat
shield configurations for a gas turbine engine. In one embodiment,
configurations are provided to restore air film cooling to one or
more regions of a heat shield where air film cooling has been
disrupted by dilution holes of the heat shield. According to one
embodiment, a heat shield includes one or more effusion holes
positioned down stream of a dilution hole in the heat shield.
Effusion holes may be positioned following the dilution hole and/or
along a trailing edge of a panel. Restoration of cooling may be
provided by air flow exiting the effusion holes to provide cooling
film to a hot side surface of the heat shield.
[0029] 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.
[0030] 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
[0031] Referring now to the figures, FIG. 1 depicts a graphical
representation of a gas turbine engine according to one or more
embodiments. In one embodiment, gas turbine engine 100 includes
combustor 105 having an annular structure 110. According to one
embodiment, annular structure 110 defines combustor cavity 120.
According to another embodiment, annular structure 110 of combustor
105 can include one or more heat shield panels, shown as 115,
lining the surfaces of annular structure 110.
[0032] Combustor 105 receives fuel from fuel nozzle 106 for
combustion. The gas flow path is shown generally as 107 in
combustor cavity 120 of annular structure 110. Gas flow path 107
flows downstream to turbine elements (not shown) of gas turbine
engine 100.
[0033] Annular structure 110 includes outer diameter 125 and inner
diameter 135. According to one or more embodiments, annular
structure 110 includes one or more cooling holes in outer diameter
125 and inner diameter 135 to provide airflow into cavity 120 and
which may be configured for cooling heat shield panels 115. Airflow
received for combustor 105 is shown generally as 130. According to
one embodiment, airflow received by combustor 105 and passing
through annular structure 110 is shown as 140. Airflow 140 may be
employed by heat shield panels 115 to provide cooling flow to a
surface of the panels, shown as 136. According to one embodiment,
dilution holes in heat shield panels 115 may disrupt cooling flow
136. As such, heat shield panels 115 may be configured with one or
more effusion holes to restore disrupted cooling flow.
[0034] FIGS. 2A-2B depict graphical representations a heat shield
according to one or more embodiments. FIG. 2A depicts a graphical
representation of heat shield 200 including panels 205.sub.1-n. In
one embodiment, heat shield 200 includes a plurality of rows of
panels 205.sub.1, each panel relating to a panel structure having a
surface 206 configured to face a combustor cavity (e.g., combustor
cavity 120). The surface 206 of each panel structure may be
configured to receive cooling airflow. According to one embodiment,
the direction of the cooling airflow across the hot-side of panels
205.sub.1-n is shown generally as 207.
[0035] FIG. 2A shows four rows of panels 205.sub.1-n. Panel
205.sub.1 may be positioned nearest to a combustor bulkhead and may
be associated with a first row of heat shield panels of a
combustor. According to one embodiment, panels 205.sub.1-n may
receive airflow to cool the surface of each panel. According to an
exemplary embodiment, and as will be described in more detail
below, cooling airflow for panels 205.sub.1-n may be provided by
way of cooling openings in a combustor shell and from openings
between one or more panels. By way of example, cooling air for
panel 205.sub.2 may be emitted from an opening in heat shield 200
between trailing edge 208 of panel 205.sub.1 and leading edge 210
of panel 205.sub.2. Similarly, cooling air for panel 205.sub.3 may
be emitted from an opening in heat shield 200 between trailing edge
211 of panel 205.sub.2 and leading edge 212 of panel 205.sub.3. In
a similar fashion, cooling air for panel 205.sub.4 may be emitted
from an opening in heat shield 200 between trailing edge 213 of
panel 205.sub.3 and leading edge 214 of panel 205.sub.4. References
to openings between leading and trailing edges of panels may
related to one or more gaps, machined structures or pathways
relative to panels of heat shield 200. Although referenced as heat
shield 200, it should be appreciated that panels 205.sub.1-n may
each be a heat shield.
[0036] Panel 205.sub.2 includes dilution holes shown as 220 and
panel 205.sub.3 includes dilution holes shown as 230. Dilution
holes 220 and 230 are openings in surface 206 of the panels
205.sub.1-n, the dilution holes can provide airflow for combustor
chamber. According to one embodiment, effusion holes are provided
in heat shield 200 in one or more locations to restore disruption
of cooling airflow across the surface of panels 205.sub.1-n. The
effusion holes may also provide cooling to hot spots or regions of
the panels that can experience distress and wear to the hot gas
environment.
[0037] According to one embodiment, panels 205.sub.1-n include one
or more effusion holes downstream of dilution holes, such as
dilution holes 220 and 230. The one or more effusion holes are
configured to restore cooling airflow to the surface of the panel
structure downstream from dilution hole. According to another
embodiment, effusion holes may be provided in other and/or
additional rows of heat shield 200 for the second and third rows of
panels 205.sub.1-n.
[0038] FIG. 2A shows one or more configurations of effusion hole
clusters according to an exemplary embodiment. Panel 205.sub.2
includes cluster 225 of effusion holes 226 downstream of dilution
holes 220. According to another embodiment, the trailing edge of
each panel of panels 205.sub.1-n can include effusion holes. Panel
205.sub.2 includes effusion holes 227 along trailing edge 211.
According to one embodiment, effusion holes 226 and effusion holes
227 can restore cooling flow for surface 206 of panel 205.sub.2
and/or downstream of panel 205.sub.2 to restore cooling flow
disrupted by dilution holes 220. Panel 205.sub.3 includes clusters
240 of effusion holes 245 downstream of dilution holes 230. Panel
205.sub.3 includes effusion holes 235 in cluster 222 along trailing
edge 213. According to one embodiment, effusion holes 245 and
effusion holes 246 can restore cooling flow for surface 206 of
panel 205.sub.3 that has been disrupted by dilution holes 230. The
location, amount, and configuration of effusion holes 226, 227, 235
and 245 in FIG. 2A is exemplary. As will be discussed in FIG. 2B,
effusion holes may be placed in a number of locations along panels
205.sub.1-n.
[0039] According to one embodiment, effusion holes 226, 227, 235
and 245 may be formed or shaped to direct airflow out of panels
205.sub.1-n in a particular direction or directions. By way of
example, effusion holes 226, 227, 235 and 245 of panels 205.sub.1-n
may be trumpet or cone shaped. Similarly, effusion holes 226, 227,
235 and 245 of panels 205.sub.1-n may be arranged at similar or
different penetration/exit angles to control the direction or
airflow exiting effusion holes 226, 227, 235 and 245. In certain
embodiments, heat shield 200 may include a panel, such as panel
205.sub.n, that includes dilution holes 255 without effusion
holes.
[0040] Referring now to FIG. 2B, a graphical representation is
provided for a configuration of a heat shield panel according to
one or more embodiments. Heat shield 260 includes one or more
exemplary regions, such as regions 265 and 266, for placement of
one or more effusion holes. Regions 265 and 266 are down stream of
dilution holes 225 and 230, respectively. Effusion holes in regions
265 and 266 may be configured to receive cooling airflow from holes
in a combustor shell and passages or space between a combustor
shell and heat shield panels.
[0041] FIG. 3 depicts a cross-sectional representation of a heat
shield configuration according to one or more embodiments. In one
embodiment, a heat shield arrangement for a gas turbine engine
includes a plurality of panels, or rows of panels that line a
combustor. The panels may line inner and/or outer structures of the
combustor. FIG. 3 depicts leading panel 301, second panel 302, and
third panel 303. According to one embodiment, one or more of panels
301, 302, and 303 are configured to allow for cooling flow to be
provided to a hot-side of the panels and to allow for restoration
of cooling flow to a hot-side of the panels when disrupted. Panels
301, 302, and 303 are shown relative to a combustor structure 305
(e.g., combustor shell, support structure, etc.).
[0042] According to one embodiment, combustor structure 305
includes one or more impingement holes to provide cooling to the
back side of panels 301, 302, and 303. The impingement holes may
also provide cooling airflow for the hot-side or panels 301, 302,
and 303. In addition, the impingement holes may provide airflow for
effusion holes of panels 301, 302, and 303. Airflow may be provided
to the surface of a panel, such as hot side 304 of panel 302. By
way of example, in certain embodiments, combustor structure 305
includes opening 306 to provide airflow 307. Airflow 307 may be
emitted between panels 301 and 302 to cool the hot side 304.
Airflow provided by the impingement holes may supply cooling air to
gaps between panels and to effusion holes of panels 301, 302, and
303.
[0043] Combustor structure 305 may also include one or more
structures 310 to provide dilution air 312 via dilution hole 311 in
panel 302. Dilution air 312 can disrupt cooling air 307 from
providing a cooling film downstream of dilution hole 311. According
to one embodiment, panels, such as panel 302 may include one or
more effusion holes, such as effusion holes 330. Effusion holes 330
are down stream of dilution hole 311 and provide cooling air 331 to
regions of panel 302 on the hot side where the cooling has been
disrupted. Cooling air 331 may provide an air film to hot side 304.
In certain embodiments, cooling air 331 may be provided by openings
in combustor structure, such as opening 306 and opening 325. Panel
302 may similarly include one or more effusion holes, shown as 335,
at or near the trailing edge of panel 302 to provide a cooling film
to the surface of panel 302 in areas that may not receive adequate
cooling and/or regions that may be susceptible to distress.
[0044] According to another embodiment, effusion holes may be
employed in a plurality of heat shield panels. Airflow may be
provided to the surface of a panel, such as hot side 336 of panel
303. By way of example, in certain embodiments, combustor structure
305 includes opening 325 to provide airflow 326. Airflow 326 may be
emitted between panels 302 and 303 to cool the hot side 336.
Combustor structure 305 may also include structure 315 to provide
dilution air 317 via dilution hole 316 in panel 303. Dilution air
317 can disrupt cooling air 326 from providing a cooling film
downstream of dilution hole 316. According to one embodiment, panel
303 may include one or more effusion holes, such as effusion holes
340 to provide cooling air to regions of panel 303 cooling film
provided by airflow 326 has been disrupted.
[0045] In one embodiment, impingement holes of combustor structure
305 may be provided in one or more locations of the combustor
structure shell. According to one embodiment, combustor structure
305 includes openings, such as openings 306 and 325. Openings 306
and 325 provide airflow for cooling the backside of panels 301,
302, and 303. In addition, openings in combustor structure 305,
such as openings 306 and 325, provide airflow for one or more
effusion holes of panels 301, 302, and 303. In certain embodiments,
openings or impingement holes, such as openings 306 and 325, in
combustor structure 305 provide airflow upstream and downstream of
the impingement hole. By way of example, opening 325 may provide
airflow 326 which provides upstream airflow 327a and downstream
airflow 327b. At least a portion of upstream airflow 327a may merge
with airflow 307 to provide cooling airflow for hot side 304. In
certain embodiment, upstream airflow 327a may exit one or more
effusion holes 330 of panel 302 as airflow 331. Downstream airflow
327b may provide cooling airflow for hot side of panel 303.
Impingement holes in combustor structure 305 may be placed in one
or more locations. An exemplary region of combustor structure 305
that may include impingement holes is shown as 328. Impingement
holes in combustor structure 305 may collocated with effusion holes
330 and/or located downstream of dilution hole 311.
[0046] FIG. 4 depicts a graphical representation of a combustor
configuration according to one or more embodiments. Combustor 400
is shown as a partial representation of an annular structure.
Combustor 400 includes outer diameter structure 401, inner diameter
structure 402. According to one embodiment, a heat shield mounted
to surface 402 may receive cooling airflow 410. According to one
embodiment, inner diameter structure 402 includes dilution hole
405. Dilution hole 405 may provide airflow 411 to the combustor
cavity. Airflow 411 may disrupt cooling airflow 410, as shown by
415. According to one embodiment, one or more effusion holes 420
may be positioned downstream of dilution hole 405, such as in areas
425. Effusion holes 420 may provide cooling airflow 426 to restore
the film cooling downstream of dilution hole 405. According to one
embodiment, effusion holes may be angled as shown as 430 to provide
cooling airflow in one or more directions downstream of dilution
hole 405. By way of example, at least one of the opening and or
effusion hole structure itself of effusions holes 420 may be angled
such that the resulting airflow 426 and 430 exit to one or more
directions to provide a cooling film to surface 403. In addition
the angle of airflow 426 and 430 may be associated with and/or
based on cooling airflow 435 that continues past dilution hole
405.
[0047] 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.
* * * * *