U.S. patent application number 14/636689 was filed with the patent office on 2016-09-08 for low net-swirl configurations for gas turbine engine combustors.
The applicant listed for this patent is UNITED TECHNOLOGIES CORPORATION. Invention is credited to Albert K. Cheung, Zhongtao Dai, James B. Hoke.
Application Number | 20160258627 14/636689 |
Document ID | / |
Family ID | 55027620 |
Filed Date | 2016-09-08 |
United States Patent
Application |
20160258627 |
Kind Code |
A1 |
Cheung; Albert K. ; et
al. |
September 8, 2016 |
LOW NET-SWIRL CONFIGURATIONS FOR GAS TURBINE ENGINE COMBUSTORS
Abstract
The present disclosure relates to gas turbine engines, and in
particular to combustor swirlers and swirler configurations. In one
embodiment, a swirler includes an inner passage for receiving a
fuel injector and a plurality of outer passages concentrically
arranged around the inner passage. The plurality of outer passages
include an outer vane assembly including a plurality of vane
elements arranged at a first angle and a first middle vane assembly
include a plurality of vane elements arranged at a second angle,
wherein the outer vane assembly is concentrically arranged around
the first middle vane assembly, and wherein the outer vane assembly
and first middle vane assembly are configured to produce a low
net-swirl to control the penetration depth and improve premixing of
a fuel air mixture for the fuel injector. According to another
embodiment, the swirler includes a second middle vane assembly
include a plurality of vane elements arranged at a third angle.
Inventors: |
Cheung; Albert K.; (East
Hampton, CT) ; Dai; Zhongtao; (Glastonbury, CT)
; Hoke; James B.; (Tolland, CT) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
UNITED TECHNOLOGIES CORPORATION |
Farmington |
CT |
US |
|
|
Family ID: |
55027620 |
Appl. No.: |
14/636689 |
Filed: |
March 3, 2015 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F23R 3/06 20130101; F23R
3/286 20130101; F23R 3/14 20130101; F23C 7/004 20130101 |
International
Class: |
F23R 3/14 20060101
F23R003/14; F23R 3/28 20060101 F23R003/28 |
Goverment Interests
STATEMENT OF FEDERALLY FUNDED RESEARCH
[0001] This invention was made with Government support under
contract number NNC13TA45T awarded by the National Aeronautics and
Space Administration (NASA). The Government has certain rights in
the invention.
Claims
1. A swirler for a combustor of a gas turbine engine, the swirler
comprising: an inner passage for receiving a fuel injector; a
plurality of outer passages concentrically arranged around the
inner passage, wherein the plurality of outer passages include an
outer vane assembly including a plurality of vane elements arranged
at a first angle; and a first middle vane assembly include a
plurality of vane elements arranged at a second angle, wherein the
outer vane assembly is concentrically arranged around the first
middle vane assembly, and wherein the outer vane assembly and first
middle vane assembly are configured to produce a low net-swirl to
control the penetration depth of a fuel air mixture for the fuel
injector.
2. The swirler of claim 1, wherein the swirler is configured to
generate an air and fuel mixture downstream of a combustor pilot
flow and improve premixing of the fuel air mixture.
3. The swirler of claim 1, wherein vanes of the outer vane assembly
are angled within the range of +45 to +60 degrees.
4. The swirler of claim 1, wherein vanes of the outer vane assembly
are arranged and configured to handle within 50 to 70 percent of
the airflow received by the swirler.
5. The swirler of claim 1, wherein vanes of the first middle vane
assembly are angled within the range of 0 to -25 degrees.
6. The swirler of claim 1, wherein vanes of the first middle vane
assembly are arranged and configured to handle within 20 to 40
percent of the airflow received by the swirler.
7. The swirler of claim 1, wherein the penetration depth relates to
the penetration depth within a combustor cavity.
8. The swirler of claim 1, wherein the swirler generates a low
net-swirl by co-swirling airflow associated with the outer vane
assembly and first middle vane assembly.
9. The swirler of claim 1, further comprising a second middle vane
assembly include a plurality of vane elements arranged at a third
angle, and wherein the first middle vane assembly is arranged
concentrically around the first middle vane assembly.
10. The swirler of claim 1, wherein vanes of the outer vane
assembly are angled in a direction opposite to vanes of the first
middle vane assembly.
11. A swirler for a combustor of a gas turbine engine, the swirler
comprising: an inner passage for receiving a fuel injector; a
plurality of outer passages concentrically arranged around the
inner passage, wherein the plurality of outer passages include an
outer vane assembly including a plurality of vane elements arranged
at a first angle; a first middle vane assembly include a plurality
of vane elements arranged at a second angle; and a second middle
vane assembly include a plurality of vane elements arranged at a
third angle, wherein the first middle vane assembly is
concentrically arranged around the second middle vane assembly,
wherein the outer vane assembly is concentrically arranged around
the first middle vane assembly and second middle assembly, and
wherein the outer vane assembly, first middle vane assembly and
second middle vane assembly are configured to produce a low
net-swirl to control the penetration depth of a fuel air mixture
for the fuel injector.
12. The swirler of claim 11, wherein the swirler is configured to
generate an air and fuel mixture downstream of a combustor pilot
flow and improve premixing of the fuel air mixture.
13. The swirler of claim 11, wherein vanes of the outer vane
assembly are angled within the range of +45 to +60 degrees.
14. The swirler of claim 11, wherein vanes of the outer vane
assembly are arranged and configured to handle within 45 to 65
percent of the airflow received by the swirler.
15. The swirler of claim 11, wherein vanes of the first middle vane
assembly are angled within the range of -10 to -30 degrees and
vanes of the second middle assembly are angled within the range of
+10 to +30 degrees.
16. The swirler of claim 11, wherein vanes of the first middle vane
assembly are arranged and configured to handle within 15 to 25
percent of the airflow received by the swirler wherein vanes of the
second middle vane assembly are arranged and configured to handle
within 15 to 25 percent of the airflow received by the swirler.
17. The swirler of claim 11, wherein the penetration depth relates
to the penetration depth within a combustor cavity.
18. The swirler of claim 11, wherein the swirler generates a low
net-swirl by co-swirling airflow associated with the outer vane
assembly and first middle vane assembly.
19. The swirler of claim 11, further comprising a second middle
vane assembly include a plurality of vane elements arranged at a
third angle, and wherein the first middle vane assembly is arranged
concentrically around the first middle vane assembly.
20. The swirler of claim 11, wherein vanes of the outer vane
assembly and second middle vane assembly are angled in a direction
opposite to vanes of the first middle vane assembly.
Description
FIELD
[0002] The present disclosure relates to combustion systems for gas
turbine engines and, in particular, low net-swirl configurations
for a combustor.
BACKGROUND
[0003] Gas turbine engines, such as those used to power modern
aircraft, to power sea vessels, to generate electrical power, and
in industrial applications, include a compressor for pressurizing a
supply of air, a combustor for burning a fuel in the presence of
the pressurized air, and a turbine for extracting energy from the
resultant combustion gases. Generally, the compressor, combustor,
and turbine are disposed about a central engine axis with the
compressor disposed axially upstream or forward of the combustor
and the turbine disposed axially downstream of the combustor. In
operation of a gas turbine engine, fuel is injected into and
combusted in the combustor with compressed air from the compressor
thereby generating high-temperature combustion exhaust gases, which
may contain pollutant gases or smoke.
[0004] Accordingly, there is a desire to provide configurations
that improve fuel and air mixing within combustors. There is also a
desire to improve the configurations of gas turbine engines and
combustor assemblies to reduce unwanted pollutant emission such as
NOx and smoke.
BRIEF SUMMARY OF THE EMBODIMENTS
[0005] Disclosed and claimed herein are swirlers and swirler
configurations for combustors of gas turbine engines. One
embodiment is directed to a swirler including an inner passage for
receiving a fuel injector and a plurality of outer passages
concentrically arranged around the inner passage. The plurality of
outer passages include an outer vane assembly including a plurality
of vane elements arranged at a first angle and a first middle vane
assembly include a plurality of vane elements arranged at a second
angle. The outer vane assembly is concentrically arranged around
the first middle vane assembly, and the outer vane assembly and
first middle vane assembly are configured to produce a low
net-swirl to control the penetration depth of a fuel air mixture
for the fuel injector.
[0006] In one embodiment, the swirler is configured to generate an
air and fuel mixture downstream of a combustor pilot flow and
improve premixing of the fuel air mixture.
[0007] In one embodiment, vanes of the outer vane assembly are
angled within the range of +45 to +60 degrees.
[0008] In one embodiment, vanes of the outer vane assembly are
arranged and configured to handle within 50 to 70 percent of the
airflow received by the swirler.
[0009] In one embodiment, vanes of the first middle vane assembly
are angled within the range of 0 to -25 degrees.
[0010] In one embodiment, vanes of the first middle vane assembly
are arranged and configured to handle within 20 to 40 percent of
the airflow received by the swirler.
[0011] In one embodiment, the penetration depth relates to the
penetration depth within a combustor cavity.
[0012] In one embodiment, the swirler generates a low net-swirl by
co-swirling airflow associated with the outer vane assembly and
first middle vane assembly.
[0013] In one embodiment, the swirler includes a second middle vane
assembly include a plurality of vane elements arranged at a third
angle, and wherein the first middle vane assembly is arranged
concentrically around the first middle vane assembly.
[0014] In one embodiment, vanes of the outer vane assembly are
angled in a direction opposite to vanes of the first middle vane
assembly.
[0015] Another embodiment is directed to a swirler including an
inner passage for receiving a fuel injector and a plurality of
outer passages concentrically arranged around the inner passage.
The plurality of outer passages include an outer vane assembly
including a plurality of vane elements arranged at a first angle, a
first middle vane assembly include a plurality of vane elements
arranged at a second angle, and a second middle vane assembly
include a plurality of vane elements arranged at a third angle. The
first middle vane assembly is concentrically arranged around the
second middle vane assembly. The outer vane assembly is
concentrically arranged around the first middle vane assembly and
second middle assembly, and wherein the outer vane assembly, first
middle vane assembly and second middle vane assembly are configured
to produce a low net-swirl to control the penetration depth of a
fuel air mixture for the fuel injector.
[0016] In one embodiment, the swirler is configured to generate an
air and fuel mixture downstream of a combustor pilot flow and
improve premixing of the fuel air mixture.
[0017] In one embodiment, vanes of the outer vane assembly are
angled within the range of +45 to +60 degrees.
[0018] In one embodiment, vanes of the outer vane assembly are
arranged and configured to handle within 45 to 65 percent of the
airflow received by the swirler.
[0019] In one embodiment, vanes of the first middle vane assembly
are angled within the range of -10 to -30 degrees and vanes of the
second middle assembly are angled within the range of +10 to +30
degrees.
[0020] In one embodiment, vanes of the first middle vane assembly
are arranged and configured to handle within 15 to 25 percent of
the airflow received by the swirler wherein vanes of the second
middle vane assembly are arranged and configured to handle within
15 to 25 percent of the airflow received by the swirler.
[0021] In one embodiment, the penetration depth relates to the
penetration depth within a combustor cavity.
[0022] In one embodiment, the swirler generates a low net-swirl by
co-swirling airflow associated with the outer vane assembly and
first middle vane assembly.
[0023] In one embodiment, the swirler includes a second middle vane
assembly include a plurality of vane elements arranged at a third
angle, and wherein the first middle vane assembly is arranged
concentrically around the first middle vane assembly.
[0024] In one embodiment, vanes of the outer vane assembly and
second middle vane assembly are angled in a direction opposite to
vanes of the first middle vane assembly
[0025] 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
[0026] 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:
[0027] FIG. 1 depicts a cross-sectional representation of a
combustor for a gas turbine engine according to one or more
embodiments;
[0028] FIGS. 2A-2C depict graphical representations of swirler
configurations according to one or more embodiments;
[0029] FIGS. 3A-3B depict graphical representations of swirler
configurations according to one or more embodiments; and
[0030] FIG. 4 depicts a graphical representation of swirler
penetration according to one or more embodiments.
DETAILED DESCRIPTION OF THE EXEMPLARY EMBODIMENTS
Overview and Terminology
[0031] One aspect of this disclosure relates to configurations for
a gas turbine engine and in particular a swirler for a combustor.
According to one embodiment, a swirler configuration can include
two or more outer passages with vane elements configured to provide
a fuel-air mixture with low net-swirl. Based on the amount of
swirl, the penetration depth of the fuel-air mixture may be
controlled to in order to increase the efficiency of fuel burn
within the combustor. According to one or more embodiments,
[0032] 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.
[0033] 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
[0034] Referring now to the figures, FIG. 1 depicts a
cross-sectional representation of a combustor for a gas turbine
engine according to one or more embodiments. Gas turbine engine 100
is shown including combustor 105 and annular structure 110.
Combustor 105 extends along a portion of a gas turbine engine 100
providing a gas-flow path within combustor cavity 106. According to
one embodiment, combustor 105 may be an axially controlled
stoichiometry combustor. Combustor 105 includes fuel nozzle 111
which may be configured as a pilot fuel injector in the front end
of the combustor and may provide a pilot fuel-air mixture 115 for
cavity 106. Combustor 105 may include a second or main fuel
injector downstream of fuel nozzle 111. According to one
embodiment, combustor 105 includes swirler 120 configured to mix
air and fuel for the second or main fuel injector associated with
secondary fuel-air mixture 130 for combustor 105.
[0035] According to one embodiment, swirler 120 may include a
plurality of passages 125 to provide low net-swirl and as a result
control the penetration depth and improve premixing of fuel-air
mixture 130. By controlling the penetration depth of fuel-air
mixture 130, swirler can provide a fuel-air mixture that improves
the fuel burning ability of fuel-air mixture 130 by pilot fuel-air
mixture 115. In that fashion, NOx (e.g., nitric oxide and nitrogen
dioxide) emissions of the combustor 105 and gas turbine engine 100
may be reduced.
[0036] Swirler 120 may be configured for one or more fuel injectors
to control the penetration of a fuel air mixture and to control
premixing of the fuel air mixture. According to one embodiment,
swirler 120 improves fuel and air mixing within combustor 105 due
to premixing. In addition, swirler 120 reduces unwanted pollutant
emission such as NOx and smoke by controlling the penetration depth
of the fuel air mixture and by combustion of substantially all
fuel.
[0037] FIGS. 2A-2B depict graphical representations of swirler
configurations according to one or more embodiments. According to
one embodiment, swirler 200 includes an inner passage 205
configured to receive air flow and one or more swirl passages shown
as 210. Inner passage 205 is configured to receive and channel air
flow 215. Inner passage 205 may be configured to receive a fuel
injector. According to one embodiment, swirler 200 includes guide
structure 206 configured to channel swirler airflow with fuel
output by a fuel injector within inner passage 205.
[0038] Swirl passages include outer passages concentrically
arranged around the inner passage 205, wherein the plurality of
outer passages include an outer vane assembly 225 and first middle
vane assembly 230. Outer vane assembly 225 includes a plurality of
vane elements arranged at a first angle. First middle vane assembly
230 includes a plurality of vane elements arranged at a second
angle. As shown in FIG. 2A, outer vane assembly 225 is
concentrically arranged around the first middle vane assembly 230.
Outer vane assembly 225 and first middle vane assembly 230 are
configured to produce a low net-swirl to control the penetration
depth of a fuel air mixture for the fuel injector, such as a main
fuel injector. Outer vane assembly 225 and first middle vane
assembly 230 may also produce a low net-swirl to improve premixing
of the fuel air mixture for the fuel injector. Although FIG. 2A, is
shown and described as having a two passage swirl arrangement above
formed by outer vane assembly 225 and first middle vane assembly
230 swirler 200 may include a second middle vane assembly.
[0039] According to one embodiment, a fuel injector within inner
passage 205 may spray fuel axially as shown by 235. Axial fuel
spray 235 is mixed with air output by outer vane assembly 225 and
first middle vane assembly 230 as fuel-air mixture 240. Fuel-air
mixture may be characterized as having a low net-swirl that allows
for the penetration depth of fuel-air mixture 240 to be controlled
with respect to an annular structure of a combustor.
[0040] FIG. 2B depicts a partial representation of a two pass outer
passage for a swirler according to one or more embodiments. Swirler
configuration 250 includes outer passage (e.g., vane assembly) 251,
middle passage (e.g., vane assembly) 252, and inner passage 255.
Outer passage 260 may be configured with a plurality of vanes are
angled within the range of +45 to +60 degrees. Vanes of the outer
passage 260 are arranged and configured to handle within 50 to 70
percent of the airflow received by the swirler. Vanes of the middle
passage 252 are angled within the range of 0 to -25 degrees and may
be configured to handle within 20 to 40 percent of the airflow
received by the swirler Inner passage 255 may be configured receive
5 to 20 percent of the airflow received by the swirler.
[0041] Air flow output by inner passage 255 and inner passage 255
co-swirls in fuel spray location 260 and joins airflow of inner
passage 255 at exit 261 of the swirler.
[0042] FIG. 2C depicts a partial representation of a three pass
outer passage for a swirler according to one or more embodiments.
Swirler configuration 270 includes outer passage (e.g., vane
assembly) 271, middle passage (e.g., vane assembly) 272, second
middle passage (e.g., vane assembly) 273, and inner passage 275.
Outer passage 271 may be configured with a plurality of vanes are
angled within the range of +45 to +60 degrees. Vanes of the outer
passage 271 are arranged and configured to handle within 45 to 65
percent of the airflow received by the swirler. Vanes of the middle
passage 272 are angled within the range of -10 to -30 degrees and
vanes of the second middle assembly are angled within the range of
+10 to +30 degrees. Vanes of the first middle vane assembly 272,
and similarly vanes of the second middle vane assembly 273 are
arranged and configured to handle within 15 to 25 percent of the
airflow received by the swirler. Inner passage 275 may be
configured receive 5 to 20 percent of the airflow received by the
swirler.
[0043] Air flow output by inner passage 275 and inners passage 272,
273 co-swirls in fuel spray location 280 and joins airflow of inner
passage 275 at exit 281 of the swirler.
[0044] FIGS. 3A-3B depict graphical representations of swirler
configurations according to one or more embodiments. FIG. 3A
depicts a two pass swirler including vane elements according to one
or more embodiments. Swirler 300 includes outer passage 305
including vanes 310 and middle passage 315 including vanes 320.
Inner passage of swirler 300 is shown as 330. Swirler 300 is an
annular structure including vanes of each passage angled in
opposite directions.
[0045] FIG. 3B depicts a three pass swirler including vane elements
according to one or more embodiments. Swirler 350 includes outer
passage 350 including vanes 355, middle passage 360 including vanes
365 and middle passage 370 including vanes 375. Inner passage of
swirler 350 is shown as 330. Swirler 350 is an annular structure
including vanes of each passage angled in opposite directions.
[0046] FIG. 4 depicts a graphical representation of swirler
penetration according to one or more embodiments. According to one
embodiment, one or more swirler elements may be included around the
circumference of an annular combustor. FIG. 4 depicts a combustor
400 and fuel-air mixture 405 controlled by a swirler relative to
the inner diameter 410 of the combustor structure. According to one
embodiment, the amount of penetration of fuel-air mixture 405 may
be controlled to a depth 415 above the inner diameter panel.
According to another embodiment, premixing of fuel-air mixture 405
may improved by the swirler configuration to reduce unwanted
pollutant emissions such as NOx and smoke.
[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.
* * * * *