U.S. patent application number 14/202969 was filed with the patent office on 2014-07-10 for 3d non-axisymmetric combustor liner.
This patent application is currently assigned to United Technologies Corporation. The applicant listed for this patent is United Technologies Corporation. Invention is credited to Paul M. Lutjen, Joel H. Wagner.
Application Number | 20140190175 14/202969 |
Document ID | / |
Family ID | 44080136 |
Filed Date | 2014-07-10 |
United States Patent
Application |
20140190175 |
Kind Code |
A1 |
Wagner; Joel H. ; et
al. |
July 10, 2014 |
3D NON-AXISYMMETRIC COMBUSTOR LINER
Abstract
A combustor liner with an input end and an output end includes
an annular inner wall and an annular outer wall. At least one of
the inner wall and outer wall is three-dimensionally contoured. The
inner wall and the outer wall form a combustion chamber with the
contours creating alternating expanding and constricting regions
inside the chamber causing combustion gases to flow in the
circumferential and axial directions.
Inventors: |
Wagner; Joel H.;
(Wethersfield, CT) ; Lutjen; Paul M.;
(Kennebunkport, ME) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
United Technologies Corporation |
Hartford |
CT |
US |
|
|
Assignee: |
United Technologies
Corporation
Hartford
CT
|
Family ID: |
44080136 |
Appl. No.: |
14/202969 |
Filed: |
March 10, 2014 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
12709951 |
Feb 22, 2010 |
8707708 |
|
|
14202969 |
|
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Current U.S.
Class: |
60/776 ; 60/746;
60/757 |
Current CPC
Class: |
F23R 3/50 20130101; F23R
3/16 20130101; F23C 3/00 20130101; F23R 3/002 20130101 |
Class at
Publication: |
60/776 ; 60/757;
60/746 |
International
Class: |
F23R 3/16 20060101
F23R003/16; F23R 3/00 20060101 F23R003/00 |
Claims
1. A combustor liner with an input end and an output end, the liner
comprising: an annular inner wall; and an annular outer wall;
wherein at least one of the inner wall and outer wall is
three-dimensionally contoured, and together the inner wall and
outer wall form a combustion chamber with the contours creating
alternating expanding and constricting regions inside the chamber
causing combustion gases to flow in the circumferential and axial
directions.
2. The combustor liner of claim 1, wherein both the inner wall and
outer wall are three-dimensionally contoured to form alternating
expanding and constricting regions inside the chamber.
3. The combustor liner of claim 1, wherein the contoured wall is
contoured around the circumference and contoured axially through
the length of the combustion chamber from input to output.
4. The combustor liner of claim 1, wherein the contoured inner wall
and contoured outer wall are contoured around the circumference and
contoured axially through the length of the combustion chamber from
input to output.
5. The combustor liner of claim 1, wherein the three-dimensional
contours promote localized mixing of gasses flowing from the input
to the output of the combustion chamber.
6. The combustor liner of claim 1, wherein the inner and outer
walls contain dilution holes.
7. The combustor liner of claim 1, wherein the combustion chamber
has a variation in volume along the axial length of the combustor
from input to output.
8. The combustor liner of claim 1, wherein the distance between the
inner wall and the outer wall in a region of constriction is about
1/3 to about 3/5 of the distance from the inner wall to the outer
wall in a region of expansion.
9. A generally cylindrical combustor to receive air and fuel at an
input end, mix the air and fuel axially through the length of the
combustor and distribute the mixture to a turbine at an output end,
the combustor comprising: a combustor liner with an annular inner
wall and an annular outer wall forming a combustion chamber, with
at least one of the walls having three-dimensional contours
creating alternating expanding and constricting regions inside the
chamber to cause combustion gases to flow in the circumferential
and axial directions; and a plurality of nozzles in an annular
shape to distribute the fuel and air into the combustion chamber at
the input end of the combustor.
10. The combustor of claim 9, wherein the inner wall and outer wall
of the combustor line have three-dimensional contours creating
alternating expanding and constricting regions inside the
chamber.
11. The combustor of claim 10, wherein the three-dimensional
contours are in a wavelike pattern on the inner and outer walls and
are located circumferentially around the walls and axially through
the length of the liner walls from input to output.
12. The combustor of claim 11, wherein at the input of the
combustor, the contours around the circumference of liner inner
wall and outer wall form regions of constriction at locations
between the nozzles, the contours around the circumference of liner
inner wall and outer wall form regions of expansion at nozzles.
13. The combustor of claim 9, wherein the three-dimensional
contours are designed to promote localized mixing of the air and
fuel in the combustor.
14. The combustor of claim 9, wherein the liner further includes a
plurality of dilution holes or jets.
15. The combustor of claim 9, wherein at the output end of the
combustor, the mixing has created a generally uniform distribution
of temperature and pressure in the mixture.
16. The combustor of claim 9, wherein the distance between liner
inner wall and liner outer wall is larger in regions of expansion
at the input end of the combustor than in regions of expansion at
the output end of the combustor.
17. The combustor of claim 9, wherein the combustion chamber has a
variation in volume from the input end than at the output end.
18. The combustor of claim 9, wherein the distance between the
inner wall and the outer wall in a region of constriction is about
1/3 to about 3/5 of the distance from the inner wall to the outer
wall in a region of expansion.
19. A method comprising: injecting fuel and air into an annular
combustion chamber between inner and outer liner walls of the
combustion chamber at an input end; and creating localized mixing
of the fuel and air in the combustion chamber with
three-dimensional contours on at least one of the inner and outer
liner walls around the circumference and axially through the length
of the combustion chamber, with the contours forming alternating
regions of expansion and constriction within the combustion
chamber.
20. The method of claim 19, wherein the step of creating localized
mixing of the fuel and air with three dimensional contours further
comprises: injecting additional air into the combustor through a
plurality of dilution holes or jets in the liner.
Description
CROSS-REFERENCE TO RELATED APPLICATION(S)
[0001] This application is a continuation of U.S. patent
application Ser. No. 12/709,951, filed on Feb. 22, 2010 which is
incorporated by reference in its entirety.
BACKGROUND
[0002] A gas turbine engine extracts energy from a flow of hot
combustion gases. Compressed air is mixed with fuel in a combustor
assembly of the gas turbine engine, and the mixture is ignited to
produce hot combustion gases. The hot gases flow through the
combustor assembly and into a turbine where energy is
extracted.
[0003] Generally there are an array of fuel nozzles between the
compressor and the turbine. One type of combustor is a can
combustor. In a can combustor, each fuel nozzle goes into a
generally cylindrical combustor can, and one combustor can fuels
the combustion process for each fuel nozzle. At the output end of
the combustor can comes a concentric heated jet of combustion gases
that goes into the turbine and produces work. The combustor may
include dilution holes and cooling jets to keep the combustor from
melting.
[0004] Another type of combustor is an annular combustor. An
annular combustor generally has a liner with an inner wall and an
outer wall, and a combustion chamber in between. At the input end
(the compressor end) of the combustor, discrete nozzles are placed
in an annular shape to inject fuel and air into the combustion
chamber. An annular combustor can include dilution holes and/or
dilution jets for cooling and mixing within the combustor. It can
also include a thermal barrier coating to prevent the combustor
from melting.
SUMMARY
[0005] A combustor liner with an input end and an output end
includes an annular inner wall and an annular outer wall. At least
one of the inner wall and outer wall is three-dimensionally
contoured. The inner wall and the outer wall form a combustion
chamber with the contours creating alternating expanding and
constricting regions inside the chamber causing combustion gases to
flow in the circumferential and axial directions.
[0006] A method including injecting fuel and air into an annular
combustion chamber between inner and outer liner walls of the
combustion chamber. It further includes creating localized mixing
of the fuel and air in the combustion chamber with
three-dimensional contours on at least one of the inner and outer
liner walls around the circumference and axially through the length
of the combustion chamber, with the contours forming alternating
regions of expansion and constriction within the combustor.
BRIEF DESCRIPTION OF THE DRAWINGS
[0007] FIG. 1 is a cross-sectional view of a gas turbine
engine.
[0008] FIG. 2 is an end view of the input end of an annular
combustor including a three-dimensionally contoured combustor
liner.
[0009] FIG. 3A is a cross-sectional view of a first embodiment of
the combustor of FIG. 2 from line A-A.
[0010] FIG. 3B is a cross-sectional view of a first embodiment of
the combustor of FIG. 2 from line B-B.
[0011] FIG. 4A is a cross-sectional view of a second embodiment of
the combustor of FIG. 2 from line A-A.
[0012] FIG. 4B is a cross-sectional view of a second embodiment of
the combustor of FIG. 2 from line B-B.
DETAILED DESCRIPTION
[0013] FIG. 1 is a cross-sectional view of gas turbine engine 10,
which includes turbofan 12, compressor section 14, combustion
section 16 and turbine section 18. Compressor section 14 includes
low-pressure compressor 20 and high-pressure compressor 22. Air is
taken in through fan 12 as fan 12 spins. A portion of the inlet air
is directed to compressor section 14 where it is compressed by a
series of rotating blades and vanes. The compressed air is mixed
with fuel, and is then inserted into combustor section 16 through
nozzles and ignited. The combustion exhaust is directed to turbine
section 18. Blades and vanes in turbine section 18 extract energy
from the combustion exhaust to turn shaft 24 and provide power
output for engine 10. The portion of inlet air that is taken in
through fan 12 and not directed through compressor section 14 is
bypass air. Bypass air is directed through bypass duct 26 by guide
vanes 28. Some of the bypass air flows through opening 29 to cool
combustor section 16, high pressure compressor 22 and turbine
section 18.
[0014] FIG. 2 shows an end view of an annular combustor 30 at the
input end (compressor end), which includes nozzles 32, combustor
liner inner wall 34, combustor liner outer wall 36 and combustion
chamber 37. Engine center line 38 and dimensions R.sub.IE,
R.sub.OE, R.sub.IC, R.sub.OC, D.sub.E and D.sub.C are also shown.
Nozzles 32 generally are evenly spaced between liner inner wall 34
and liner outer wall 36. Liner inner wall 34 and liner outer wall
36 can be made with cobalt or a nickel alloy and may include a
thermal barrier coating. Liner inner and outer walls 34, 36 include
three-dimensional contours around the circumference of the inner
and outer walls 34, 36 and three-dimensional contours axially
through length of the combustion chamber 37 from the input to the
output. The three-dimensional contours are generally in a wavelike
pattern forming alternating regions of constriction and expansion
in combustion chamber 37. The contours around the circumference at
the input end of combustor 30 can be seen from the view shown in
FIG. 2. At the input end of combustor 30, the contours around the
circumference of liner walls 34, 36 form regions of expansion at
nozzles 32 and regions of constriction between nozzles 32. R.sub.IE
is the distance from engine center line 38 to liner inner wall 34
at a region of expansion. R.sub.OE is the distance from engine
center line to liner outer wall 36 at a region of expansion.
R.sub.IC is the distance from engine center line 38 to liner inner
wall 34 at a region of constriction. R.sub.OC is the distance from
engine center line to liner outer wall 36 at a region of
constriction. D.sub.E is the distance between liner inner wall 34
and liner outer wall 36 at a region of expansion
(R.sub.OE-R.sub.IE). D.sub.C is the distance between liner inner
wall 34 and liner outer wall 36 at a region of constriction
(R.sub.OC-R.sub.IC). The contours of liner inner wall 34 and liner
outer wall 36 generally minor each other, and can be of the size
that D.sub.C (the distance from liner inner wall 34 to liner outer
wall 36 at a region of constriction) is about 1/3 to about 3/5 of
D.sub.E (the distance from liner inner wall 34 to liner outer wall
36 at a region of expansion), but may be more or less depending on
the needs of the particular combustor.
[0015] Each nozzle 32 distributes compressed air and fuel into
combustor 30, between liner inner wall 34 and liner outer wall 36.
The air and fuel distributed is a mixture set for flame holding to
promote combustion within the combustion chamber 37. This
distribution by nozzles 32 results in very intense heat at each
discrete nozzle 32.
[0016] When exiting combustor 30, the combusted fuel and air
mixture enters turbine section 18 where it comes into contact with
first stage high pressure turbine ("HPT") vanes (see FIG. 1).
Circumferential variation in the temperature entering turbine 18
leads to variation in distress observed by static hardware in
turbine 18. Advanced distress of turbine hardware at a single
circumferential location can limit service life of the engine, or
time between overhauls. Thus, to maximize service life, a
circumferentially prescribed or uniform temperature profile is
desirable. Mixing of the air and fuel axially through the length of
combustor 30 from input to output can promote a more uniform
distribution of temperature (as well as pressure and species) at
the output of combustor 30. This uniform distribution of
temperature going into the turbine helps to ensure that the
progression of distress on turbine hardware is not dependent on
circumferential location.
[0017] The current invention controls the mixing by adding
three-dimensional contours circumferentially and axially through
the length of combustor 30 liner inner wall 34 and liner outer wall
36 to form alternating regions of constriction and expansion within
combustion chamber 37. In previous combustion chambers, mixing was
often done by adding dilution holes or jets to combustor liner
walls 34, 36. Dilution holes are holes in liner walls which allow
cooler air into the combustor to promote mixing. Dilution jets
propel air into the combustor at high velocity to promote mixing in
the combustor. The current invention further promotes mixing and
controls the flow in combustor 30 by adding three-dimensional
contours circumferentially and axially through the length of
combustor 30 liner inner wall 34 and liner outer wall 36 to form
alternating regions of constriction and expansion within combustion
chamber 37.
[0018] FIG. 3A is a cross-sectional view of a first embodiment of
the combustor of FIG. 2 above engine center line 38 from line A-A
(at nozzle 32) of FIG. 2. FIG. 3A includes nozzle 32,
three-dimensionally contoured liner inner wall 34a,
three-dimensionally contoured liner outer wall 36a, combustion
chamber 37, input end 40, output end 42, nozzle center line of flow
44, regions of expansion E and a region of constriction C.
Dimensions R.sub.IE (from engine centerline 38 to liner inner wall
34a at a region of expansion), R.sub.OE (from engine centerline 38
to liner outer wall 36a at a region of expansion), R.sub.IC (from
engine centerline 38 to liner inner wall 34a at a region of
constriction), R.sub.OC (from engine centerline 38 to liner outer
wall 36a at a region of constriction), D.sub.E (between liner inner
wall 34a and liner outer wall 36a at a region of expansion,
R.sub.OE-R.sub.IE) and D.sub.C (between liner inner wall 34a and
liner outer wall 36a at a region of constriction,
R.sub.OC-R.sub.IC) for regions of expansion and constriction are
also shown.
[0019] An air and fuel mixture is injected into combustion chamber
37 at input end 40 by nozzle 32 at center line of flow 44. This
mixture is ignited and travels through combustor to output end 42.
As mentioned above, this results in very intense heat downstream of
each discrete nozzle 32. To help disburse this heat and control
overall mixing, liner inner wall 34a and outer wall 36a include
three-dimensional contours both circumferentially and axially
through the length of combustor 30 from input 40 to output 42 to
form alternating regions of constriction C and expansion E. These
alternating regions of constriction C and expansion E force
combustion gases to move circumferentially as well as axially after
being injected into combustion chamber 37.
[0020] Contoured liner inner wall 34a and liner outer wall 36a
illustrate contours axially through the length of combustor liner
at a cross-section where a nozzle 32 is located. Liner inner wall
34a and liner outer wall 36a form a region of expansion E at input
40. Moving axially toward output 42, liner inner wall 34a and liner
outer wall 36a form a region of constriction C, and then another
region of expansion E (in a wavelike pattern). Where the contours
bring liner walls together to form a region of constriction C,
inner liner wall 34a and outer liner wall 36a generally mirror each
other, and each liner wall (34a, 36a) can come toward the other
about 1/6 to about 1/10 of the distance of D.sub.E (the distance
between liner inner wall 34a and liner outer wall 36a at an
expansion region). This results in D.sub.C (the distance between
liner inner wall 34a and liner outer wall 36a at a constriction
region C) being about 1/3 to about 3/5 of D.sub.E.
[0021] When liner inner wall 34a and liner outer wall 36a go from
an expansion region E (at input 40) to a constriction region C,
some of the flow is forced to move circumferentially within
combustion chamber 37 toward circumferentially adjacent expansion
zones (such as expansion region E in FIG. 3B). This circumferential
flow draws the hot air and fuel mixture distributed by nozzle 32 to
areas not directly in front of a nozzle 32, promoting
redistribution of combustion gases in less hot areas (areas not
directly in front of a nozzle 32).
[0022] FIG. 3B is a cross-sectional view of a first embodiment of
the combustor of FIG. 2 above engine center line 38 from line B-B
(between nozzles) of FIG. 2. FIG. 3B includes three-dimensionally
contoured liner inner wall 34b, three-dimensionally contoured liner
outer wall 36b, combustion chamber 37, input end 40, output end 42,
and regions of constriction C and a region of expansion E. FIG. 3B
further includes dimensions R.sub.IE (from engine centerline 38 to
liner inner wall 34b at a region of expansion), R.sub.OE (from
engine centerline 38 to liner outer wall 36b at a region of
expansion), R.sub.IC (from engine centerline 38 to liner inner wall
34b at a region of constriction), R.sub.OC (from engine centerline
38 to liner outer wall 36b at a region of constriction), D.sub.E
(between liner inner wall 34b and liner outer wall 36b at a region
of expansion, R.sub.OE-R.sub.IE) and D.sub.C (between liner inner
wall 34b and liner outer wall 36b at a region of constriction,
R.sub.OC-R.sub.IC).
[0023] Contoured liner inner wall 34b and liner outer wall 36b
illustrate contours axially through the length of combustor liner
at a cross-section between where nozzles 32 are located. As can be
seen in FIG. 3B, cross-sections between nozzles 32 at input 40 of
combustion chamber 37 start with a region of constriction C,
followed by a region of expansion E, and then another region of
constriction C. As in FIG. 3B, inner liner wall 34b and outer liner
wall 36b generally minor each other, and each liner wall (34b, 36b)
can be come toward the other about 1/6 to about 1/10 of the
distance of D.sub.E (the distance between liner inner wall 34b and
liner outer wall 36b at an expansion region E). This results in
D.sub.C (the distance between liner inner wall 34b and liner outer
wall 36b at a constriction region C) being about 1/3 to about 3/5
of D.sub.E. The zones of constriction and expansion in FIG. 3B also
work to force a circumferential flow of the gases within combustion
chamber 37, thereby promoting mixing and a more even distribution
of temperature, pressure and species in combustor 30 as gases move
from input 40 to output 42.
[0024] The cross-sections in FIG. 3A and in FIG. 3B are
circumferentially next to each other and work together to promote
mixing. As can be seen from FIGS. 3A-3B, when the inner and outer
liner walls of FIG. 3A form a region of constriction, the inner and
outer liner walls of FIG. 3B form a region of expansion (and vice
versa). For example, at combustor 30 input 40, FIG. 3A liner walls
34a, 36a form a region of expansion and FIG. 3B liner walls 34b,
36b form a region of constriction. When liner walls in a
cross-section go from forming a region of expansion to a region of
constriction, the combustion gases will not all be able to travel
axially, and some will be forced to travel circumferentially due to
the constriction. For example, in FIG. 3A at input 40 liner walls
34a, 36a form a region of expansion, and at the midpoint between
input 40 and output 42 liner walls 34a, 36a form a region of
constriction. As combustion gases travel axially from the zone of
expansion to the zone of constriction, some of the gases will be
forced to move circumferentially to the region of expansion shown
in FIG. 3B at the midpoint between input 40 and output 42. Then as
the region of expansion formed by liner walls 34b, 36b in FIG. 3B
goes into a region of constriction near output 42, combustion gases
are forced to move circumferentially again to a region of expansion
in a neighboring cross-section. This circumferential flow controls
mixing and can result in a more even or a prescribed distribution
of temperature, pressure and species in combustor 30 as the air and
fuel mixture moves axially between input 40 and output 42.
Contoured liner walls 34, 36 can also include dilution holes and/or
dilution jets (discussed in relation to FIG. 2) to further promote
mixing in and aid in cooling combustor 30.
[0025] The size and placement of contours on liner inner walls 34
and liner outer walls 36 are shown for example purposes only and
may be varied according to combustor needs. Generally, the scale of
contours is proportional to the combustor velocity, the velocity at
which the fuel and air mixture is distributed from nozzles 32. For
example, in a combustor where nozzle 32 distributes air and fuel
into combustor 30 at a low velocity (about 0.1 mach), contours
which form regions of constriction would have to be larger to
promote mixing and control the flow direction (for example, D.sub.C
can be about 1/3 of D.sub.E) than if nozzle 32 has a higher
velocity. If nozzle 32 distributes air and fuel at a high velocity
(about 0.3 mach) contours could be smaller (for example, D.sub.C
can be about 3/5 of D.sub.E).
[0026] FIG. 4A illustrates a cross-section of a second embodiment
of the combustor of FIG. 2 from line A-A of FIG. 2, having a
three-dimensionally contoured liner, with the combustor having a
variation in volume from input 40 to output 42, specifically a
decrease in volume. Combustor 30 includes nozzle 32;
three-dimensionally contoured liner inner wall 34';
three-dimensionally contoured liner outer wall 36'; combustion
chamber 37; input end 40; output end 42; nozzle center line of flow
44; axial zones F, G and H; and dimensions D.sub.FE (from inner
liner wall 34' to outer liner wall 36' at expansion region E in
zone F), D.sub.GC (from inner liner wall 34' to outer liner wall
36' at constriction region C in zone G), and D.sub.HE (from inner
liner wall 34' to outer liner wall 36' at expansion region E in
zone H).
[0027] FIG. 4B illustrates a cross-section of a second embodiment
of the combustor of FIG. 2 from line B-B (between nozzles) of FIG.
2. FIG. 4B includes three-dimensionally contoured liner inner wall
34'; three-dimensionally contoured liner outer wall 36'; combustion
chamber 37; input end 40; output end 42; axial zones F, G, and H;
and distance measurements D.sub.FC (from inner liner wall 34' to
outer liner wall 36' at constriction region C in zone F), D.sub.GE
(from inner liner wall 34' to outer liner wall 36' at expansion
region E in zone G), and D.sub.HC (from inner liner wall 34' to
outer liner wall 36' at constriction region C in zone H).
[0028] Combustor 30, contoured liner inner walls 34' and contoured
liner outer walls 36' work much the same way as discussed in
relation to FIGS. 3A-3B, moving flow circumferentially and mixing
combustion gases from input 40 to output 42. However, in this
embodiment, the combustion chamber 37 experiences a decrease in
volume from input 40 to output 42 (as shown through cross-sections
F, G, H losing area from input 40 to output 42). Therefore, the
distance measurements between liner inner wall 34' and liner outer
wall 36' for areas of expansion E are largest in zone F (D.sub.FE
in FIG. 4A), smaller in zone G (D.sub.GE in FIG. 4B), and smallest
in zone H (D.sub.HE in FIG. 4A).
[0029] As the cross-sectional area (and total overall volume) of
combustion chamber 37 decreases from input 40 to output 42, this
decrease in area would increase the velocity of the combustion
gases. As mentioned above, the scale of contours to form regions of
constriction C is approximately inversely proportional to the
velocity of the combustion gases. Smaller contours (meaning the
distance D.sub.C between inner liner wall 34' and outer liner wall
36' is larger in regions of constriction C) can promote mixing when
velocity is higher, whereas larger contours (meaning the distance
D.sub.C between inner liner wall 34' and outer liner wall 36' is
smaller in regions of constriction C) are necessary to promote the
same levels of mixing when velocity is lower. Therefore, as the
velocity increases from input 40 to output 42 due to the decrease
in combustion chamber 37 volume or the addition of dilution and
cooling air, the contours forming constriction regions C on liner
inner wall 34' and liner outer wall 36' can decrease while still
promoting the same levels of mixing. In some combustors, axially
through the length from input 40 to output 42 of combustor 30, the
contours may diminish to zero or to small values as that might be
needed for controlling the flow into the HPT vane (making
dimensions D.sub.E and D.sub.C about equal).
[0030] In summary, the current invention adds three-dimensional
contouring of inner and outer liner walls in a combustor to form
alternating regions of constriction and expansion both
circumferentially and axially to better control flow coming out of
the combustor into the turbine. By controlling flow to promote
mixing, an even or prescribed distribution of temperature, pressure
and species at the output of the combustor can be achieved. This
can prolong engine life by preventing the advanced distress of
turbine hardware due to hot spots flowing out of the combustor and
into the turbine. This mixing can also promote more efficient
combustion in the combustor. The three-dimensional contours may
allow for the elimination of some or all dilution holes and/or
dilution jets in the combustor liner (previously used to promote
mixing).
[0031] While the invention has been discussed mainly in reference
to promoting and controlling mixing as a means to achieve an even
distribution of temperature, pressure and species at the output of
the combustor, the three-dimensionally contoured liner could be
used in situations where an even distribution is not desired. The
three-dimensional wavelike contours forming regions of constriction
and expansion can be placed throughout the combustor liner inner
wall and liner outer wall to control flow and/or promote mixing in
any way desired. While this invention has been discussed mainly in
reference to liner inner and liner outer walls each having
three-dimensional contours, controlling of the flow and/or mixing
can also be done by having three-dimensional contours only on liner
inner wall or liner outer wall.
[0032] While the invention has been described with reference to an
exemplary embodiment(s), it will be understood by those skilled in
the art that various changes may be made and equivalents may be
substituted for elements thereof without departing from the scope
of the invention. In addition, many modifications may be made to
adapt a particular situation or material to the teachings of the
invention without departing from the essential scope thereof.
Therefore, it is intended that the invention not be limited to the
particular embodiment(s) disclosed, but that the invention will
include all embodiments falling within the scope of the appended
claims.
* * * * *