U.S. patent application number 15/506404 was filed with the patent office on 2018-08-09 for acoustic damping system for a combustor of a gas turbine engine.
The applicant listed for this patent is Siemens Aktiengesellschaft. Invention is credited to Matthias Hase, Rajesh Rajaram, Sachin Terdalkar.
Application Number | 20180224123 15/506404 |
Document ID | / |
Family ID | 51570898 |
Filed Date | 2018-08-09 |
United States Patent
Application |
20180224123 |
Kind Code |
A1 |
Hase; Matthias ; et
al. |
August 9, 2018 |
ACOUSTIC DAMPING SYSTEM FOR A COMBUSTOR OF A GAS TURBINE ENGINE
Abstract
An acoustically dampened gas turbine engine (10) having a gas
turbine engine combustor (12) with an acoustic damping resonator
system (10) is disclosed. The acoustic damping resonator system
(10) may be formed from one or more resonators (16) formed from a
resonator housing (18) positioned within the gas turbine engine
combustor (12) at an outer housing (20) forming a combustor basket
(22) and extending circumferentially within the combustor (12). In
at least one embodiment, the resonator housing (18) may include one
or more resonator chambers (24) that provide enhanced cooling with
reduced risk of cracking and other damage. The resonator housing
(18) may include resonator exhaust orifices (26) that are
positioned closer to an area of maximum temperature within the
combustor (12), thereby enabling the resonator (16) to reduce the
temperature gradient within the combustor (12). The resonator
housing (18) may be sized and configured to reduce stress found in
conventional systems by increasing distances between resonator
exhaust orifices (26) and between resonator inlet impingement
orifices (30), among others.
Inventors: |
Hase; Matthias; (Mulheim,
DE) ; Terdalkar; Sachin; (Oviedo, FL) ;
Rajaram; Rajesh; (Winter Park, FL) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Siemens Aktiengesellschaft |
|
|
|
|
|
Family ID: |
51570898 |
Appl. No.: |
15/506404 |
Filed: |
September 5, 2014 |
PCT Filed: |
September 5, 2014 |
PCT NO: |
PCT/US2014/054179 |
371 Date: |
February 24, 2017 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F23R 3/002 20130101;
F23R 2900/03044 20130101; F23M 20/005 20150115; F23R 2900/00014
20130101 |
International
Class: |
F23R 3/00 20060101
F23R003/00 |
Claims
1-16. (canceled)
17. An acoustic damping resonator system for a combustor of a
turbine engine, comprising: at least one resonator housing defining
at least one inner channel with an inner surface and an outer
surface on an opposite side of the at least one resonator housing
from the inner sur-face; at least one resonator chamber extending
radially outward from the at least one resonator housing, wherein
the at least one resonator chamber includes at least one resonator
inlet impingement orifice in an outer wall of the at least one
resonator chamber and at least one resonator exhaust orifice
extending through the at least one resonator housing; and wherein a
ratio of distance between the outer wall of the at least one
resonator chamber and the at least one resonator housing to a
diameter of the at least one resonator inlet impingement orifice is
between about seven and about four.
18. The acoustic damping resonator system of claim 17, wherein a
maximum internal resonator dimension extending linearly within the
at least one resonator chamber is increased less than 12 percent
while a footprint of the at least one resonator chamber has been
enlarged by between 40 percent and 100 percent relative to a
resonator chamber having a ratio of greater than eight of a
distance between the outer wall of a resonator chamber and a
resonator housing to a diameter of a resonator inlet impingement
orifice.
19. The acoustic damping resonator system of claim 18, wherein a
cross-sectional shape of outer sidewalls forming the at least one
resonator chamber forms a modified parallelogram in which a longest
diagonal direction has been reduced via truncated
intersections.
20. The acoustic damping resonator system of claim 18, wherein the
truncated intersections of the modified parallelogram are formed
with a first corner side at a first intersection and a second
corner side at a second intersection, wherein the first corner side
extends between first and second sidewalls forming the modified
parallelogram and wherein the second corner side extends between
third and fourth sidewalls forming the modified parallelogram.
21. The acoustic damping resonator system of claim 18, wherein a
cross-sectional shape of outer sidewalls forming the at least one
resonator chamber forms a modified triangle in which at least two
corners have been truncated with corner sides.
22. The acoustic damping resonator system of claim 21, wherein each
corner of the modified triangle has been truncated with at least
one corner side such that a first corner side extends between first
and second sidewalls, a second corner side extends between second
and third sidewalls and a third corner side extends between first
and third sidewalls.
23. The acoustic damping resonator system of claim 18, wherein a
cross-sectional shape of outer sidewalls forming the at least one
resonator chamber forms a modified rectangle in which at least two
corners have been truncated with corner sides.
24. The acoustic damping resonator system of claim 23, wherein at
least two corners of the modified rectangle have been truncated
with at least one corner side.
25. The acoustic damping resonator system of claim 24, wherein each
corner of the modified rectangle have been truncated with at least
one corner side such that a first corner side extends between first
and second sidewalls, a second corner side extends between second
and third sidewalls, a third corner side extends between third and
fourth sidewalls and a fourth corner side extends between first and
fourth sidewalls.
26. The acoustic damping resonator system of claim 18, wherein at
least one corner on at least one sidewall forming the at least one
resonator chamber is curved.
27. The acoustic damping resonator system of claim 17, wherein the
at least one resonator exhaust orifice extending through the at
least one resonator housing is offset axially upstream to place the
at least one resonator exhaust orifice closer to an area of maximum
temperature within the combustor; wherein the at least one
resonator exhaust orifice comprises a plurality of resonator
exhaust orifices that are positioned closer to an upstream wall of
the at least one resonator chamber than a downstream wall of the at
least one resonator chamber; wherein the at least one resonator
inlet impingement orifice comprises a plurality of resonator inlet
impingement orifices that are offset from the plurality of
resonator exhaust orifices such that at least one of the plurality
of resonator inlet impingement orifices is radially aligned with
the at least one resonator housing in which the plurality of
resonator exhaust orifices are positioned such that cooling fluids
flowing into the at least one resonator chamber impinge on the at
least one resonator housing.
28. The acoustic damping resonator system of claim 27, wherein the
plurality of resonator exhaust orifices are separated from each
other a distance equal to at least one and one half times a
diameter of a smallest diameter of the plurality of resonator
exhaust orifices.
29. The acoustic damping resonator system of claim 27, wherein the
plurality of resonator inlet impingement orifices form half as many
rows as rows formed by the plurality of resonator exhaust orifices,
and wherein the rows formed by the plurality of resonator inlet
impingement orifices extend circumferentially and are aligned
radially between rows of the plurality of resonator exhaust
orifices beginning with a first upstream row of resonator exhaust
orifices and moving downstream.
30. The acoustic damping resonator system of claim 29, wherein the
plurality of resonator inlet impingement orifices form a first row
that has one fewer orifices than a first row of resonator exhaust
orifices and wherein the plurality of resonator inlet impingement
orifices form a second row downstream from the first row of
resonator inlet impingement orifices, whereby the second row of
resonator inlet impingement orifices has two fewer orifices than a
second row of resonator exhaust orifices.
31. The acoustic damping resonator system of claim 27, wherein the
plurality of inlet impingement orifices are separated from each
other a distance equal to at least one and one half times a
diameter of a smallest diameter of the plurality of inlet
impingement orifices.
32. The acoustic damping resonator system of claim 27, wherein the
outer wall is sized in thickness such that a ratio of a length of
the at least one resonator inlet impingement orifice extending
radially inward to a diameter of the at least one resonator inlet
impingement orifice is greater than one.
33. An acoustic damping resonator system for a combustor of a
turbine engine, comprising: at least one resonator housing defining
at least one inner channel with an inner surface and an outer
surface on an opposite side of the at least one resonator housing
from the inner surface; at least one resonator chamber extending
radially outward from the at least one resonator housing, wherein
the at least one resonator chamber includes at least one resonator
inlet impingement orifice in an outer wall of the at least one
resonator chamber and at least one resonator exhaust orifice
extending through the at least one resonator housing; wherein a
ratio of distance between the outer wall of the at least one
resonator chamber and the at least one resonator housing to a
diameter of the at least one resonator inlet impingement orifice is
between about seven and about four; wherein a maximum internal
resonator dimension extending linearly within the at least one
resonator chamber is increased less than 12 percent while a
footprint of the at least one resonator chamber has been enlarged
by between 40 percent and 100 percent relative to a resonator
chamber having a ratio of greater than eight of a distance between
the outer wall of a resonator chamber and a resonator housing to a
diameter of a resonator inlet impingement orifice; wherein the at
least one resonator exhaust orifice comprises a plurality of
resonator exhaust orifices that are positioned closer to an
upstream wall of the at least one resonator chamber than a
downstream wall of the at least one resonator chamber; and wherein
the at least one resonator inlet impingement orifice comprises a
plurality of resonator inlet impingement orifices that are offset
from the plurality of resonator exhaust orifices such that at least
one of the plurality of resonator inlet impingement orifices is
radially aligned with the at least one resonator housing in which
the plurality of resonator exhaust orifices are positioned such
that cooling fluids flowing into the at least one resonator chamber
impinge on the at least one resonator housing.
34. The acoustic damping resonator system of claim 33, wherein a
cross-sectional shape of outer sidewalls forming the at least one
resonator chamber forms a modified parallelogram in which a longest
diagonal direction has been reduced via truncated
intersections.
35. The acoustic damping resonator system of claim 33, wherein a
cross-sectional shape of outer sidewalls forming the at least one
resonator chamber forms a modified triangle in which at least two
corners have been truncated with corner sides.
36. The acoustic damping resonator system of claim 33, wherein a
cross-sectional shape of outer sidewalls forming the at least one
resonator chamber forms a modified rectangle in which at least two
corners have been truncated with corner sides.
Description
FIELD OF THE INVENTION
[0001] The present invention relates in general to gas turbine
engines and, more particularly, to acoustic damping systems for
damping dynamics in combustors in gas turbine engines.
BACKGROUND OF THE INVENTION
[0002] Gas turbine engines typically include a plurality of
combustor baskets positioned downstream from a compressor and
upstream from a turbine assembly. During operation, longitudinal
mode dynamics often occurs in the combustor baskets. The
longitudinal mode dynamics usually originates at the inlet of the
air flow path in a combustor basket and travels downstream to the
turbine inlet. The dynamics restrict the tuning flexibility of the
gas turbine engine in order to operate at lower emissions, which is
an ever increasing requirement for newer gas turbines.
[0003] Resonators have been incorporated into combustors to damp
the longitudinal mode dynamics. The resonators have been sized and
configured to address specific acoustic tunes. Resonators with
various configurations have been employed. Typically, the
resonators are positioned within the combustors in the area of
highest heat release to be most effective. It is in this position
where the resonators are exposed to significant temperatures and
thermal gradients. Early configurations including welding
resonators directly to the combustor, but often failed due to
formation of cracks caused by residual stress, leading to high
repair costs. Other solutions have been used with limited success
because of cracking and significant repair costs. Thus, a need
exists for a more efficient, less costly solution to damp
longitudinal mode dynamics.
SUMMARY OF THE INVENTION
[0004] An acoustically dampened gas turbine engine having a gas
turbine engine combustor with an acoustic damping resonator system
is disclosed. The acoustic damping resonator system may be formed
from one or more resonators formed from a resonator housing
positioned within the gas turbine engine combustor at an outer
housing forming a combustor basket and extending circumferentially
within the combustor. In at least one embodiment, the resonator
housing may include one or more resonator chambers that provide
enhanced cooling with reduced risk of cracking and other damage.
The resonator housing may include resonator exhaust orifices that
are positioned closer to an area of maximum temperature within the
combustor, thereby enabling the resonator to reduce the temperature
gradient within the combustor. The resonator housing may be sized
and configured to reduce stress found in conventional systems by
increasing distances between resonator exhaust orifices and between
resonator inlet impingement orifices, among others.
[0005] In at least one embodiment, the acoustic damping resonator
system for a combustor of a turbine engine may include one or more
resonator housings defining one or more inner channels with an
inner surface and an outer surface on an opposite side of the
resonator housing from the inner surface. The acoustic damping
resonator system may include one or more resonator chambers
extending radially outward from the resonator housing. The
resonator chamber may include one or more resonator inlet
impingement orifices in an outer wall of the resonator chamber and
one or more resonator exhaust orifices extending through the
resonator housing. The resonator exhaust orifice extending through
the resonator housing may be offset axially upstream to place the
resonator exhaust orifice closer to an area of maximum temperature
within the combustor.
[0006] The resonator exhaust orifice may include a plurality of
resonator exhaust orifices that are positioned closer to an
upstream wall of the resonator chamber than a downstream wall of
the resonator chamber. The plurality of resonator exhaust orifices
may be separated from each other a distance equal to at least one
and one half times a diameter of a smallest diameter of the
plurality of resonator exhaust orifices. In another embodiment, the
plurality of resonator exhaust orifices may be separated from each
other a distance equal to at least two times a diameter of a
smallest diameter of the plurality of resonator exhaust orifices.
The plurality of resonator exhaust orifices may be collected into a
pattern of an inverted triangle with a point of the triangle
pointed downstream. In another embodiment, the plurality of
resonator exhaust orifices are collected into a pattern of a
rectangle.
[0007] The resonator inlet impingement orifice may include a
plurality of resonator inlet impingement orifices that are offset
from the plurality of resonator exhaust orifices such that one or
more of the plurality of resonator inlet impingement orifices are
radially aligned with the resonator housing in which the plurality
of resonator exhaust orifices are positioned such that cooling
fluids flowing into the resonator chamber impinge on the resonator
housing. The plurality of resonator inlet impingement orifices may
form half as many rows as rows formed by the plurality of resonator
exhaust orifices. The rows formed by the plurality of resonator
inlet impingement orifices may extend circumferentially and may be
aligned radially between rows of the plurality of resonator exhaust
orifices beginning with a first upstream row of resonator exhaust
orifices and moving downstream. The plurality of resonator inlet
impingement orifices may form a first row that has one fewer
orifices than a first row of resonator exhaust orifices. The
plurality of resonator inlet impingement orifices may form a second
row downstream from the first row of resonator inlet impingement
orifices, whereby the second row of resonator inlet impingement
orifices may have two fewer orifices than a second row of resonator
exhaust orifices. The second row of inlet impingement orifices may
skip a position in a middle of the second row of resonator exhaust
orifices.
[0008] The plurality of inlet impingement orifices may be separated
from each other a distance equal to at least one and one half times
a diameter of a smallest diameter of the plurality of inlet
impingement orifices. The plurality of inlet impingement orifices
may be separated from each other a distance equal to at least two
times a diameter of a smallest diameter of the plurality of inlet
impingement orifices. A ratio of distance between the outer wall of
the resonator chamber and the resonator housing and a diameter of
the resonator inlet impingement orifice may be between about seven
and about four. The outer wall may be sized in thickness such that
a ratio of a length of the at least one resonator inlet impingement
orifice extending radially inward to a diameter of the at least one
resonator inlet impingement orifice is greater than one. In another
embodiment, an acoustic damping resonator system for a combustor of
a turbine engine may include one or more resonator housings
defining at least one inner channel with an inner surface and an
outer surface on an opposite side of the resonator housing from the
inner surface. The an acoustic damping resonator system may include
one or more resonator chambers extending radially outward from the
resonator housing, whereby the resonator chamber includes at least
one resonator inlet impingement orifice in an outer wall of the
resonator chamber and resonator exhaust orifice extending through
the resonator housing.
[0009] The acoustic damping resonator system may include a ratio of
distance between the outer wall of the resonator chamber and the
resonator housing to a diameter of the resonator inlet impingement
orifice between about seven and about four. As such, the footprint
of the resonator chamber is expanded. A maximum internal resonator
dimension extending linearly within the at least one resonator
chamber may be increased less than 12 percent while a footprint of
the resonator chamber has been enlarged by between 40 percent and
100 percent relative to a resonator chamber having a ratio of
greater than eight of a distance between the outer wall of a
resonator chamber and a resonator housing to a diameter of a
resonator inlet impingement orifice.
[0010] The acoustic damping resonator system may include resonator
chambers having numerous different shapes configured to prevent a
maximum internal resonator dimension extending linearly within the
resonator chamber from being enlarged beyond a point at which the
resonator chamber has a target cutoff frequency that is greater
than an actual damping frequency. In at least one embodiment, a
cross-sectional shape of outer sidewalls forming the resonator
chamber forms a modified parallelogram in which a longest diagonal
direction has been reduced via truncated intersections. The
truncated intersections of the modified parallelogram may be formed
with a first corner side at a first intersection and a second
corner side at a second intersection, whereby the first corner side
may extend between first and second sidewalls forming the modified
parallelogram and wherein the second corner side may extend between
third and fourth sidewalls forming the modified parallelogram. In
another embodiment, a cross-sectional shape of outer sidewalls
forming the resonator chamber may form a modified triangle in which
at least two corners have been truncated with corner sides. In yet
another embodiment, each corner of the modified triangle may have
been truncated with at least one corner side such that a first
corner side may extend between first and second sidewalls, a second
corner side may extend between second and third sidewalls and a
third corner side may extend between first and third sidewalls.
[0011] In another embodiment, a cross-sectional shape of outer
sidewalls forming the resonator chamber may form a modified
rectangle in which at least two corners have been truncated with
corner sides. At least two corners of the modified rectangle may
have been truncated with at least one corner side. Each corner of
the modified rectangle may have been truncated with at least one
corner side such that a first corner side may extend between first
and second sidewalls, a second corner side may extend between
second and third sidewalls, a third corner side may extend between
third and fourth sidewalls and a fourth corner side may extend
between first and fourth sidewalls. In at least one embodiment, at
least one corner on at least one sidewall forming the resonator
chamber may be curved.
[0012] These and other advantages and objects will become apparent
upon review of the detailed description of the invention set forth
below.
BRIEF DESCRIPTION OF THE DRAWINGS
[0013] The accompanying drawings, which are incorporated in and
form a part of the specification, illustrate embodiments of the
presently disclosed invention and, together with the description,
disclose the principles of the invention.
[0014] FIG. 1 is partial cross-sectional side view of a combustors
positioned within gas turbine engines.
[0015] FIG. 2 is a cross-sectional side view of a combustor in the
gas turbine engine taken as section line 2-2 in FIG. 1.
[0016] FIG. 3 is a perspective view of a combustor liner with an
acoustic damping resonator system.
[0017] FIG. 4 is a schematic diagram of a combustor in the gas
turbine engine with a conventional resonator.
[0018] FIG. 5 is a cross-sectional side view of a resonator of the
acoustic damping resonator system shown together with a
conventional resonator with a larger height taken along section
line 5-5 in FIG. 3.
[0019] FIG. 6 is a perspective, cross-sectional view of resonator
chamber of the acoustic damping resonator system taken along
section line 6-6 in FIG. 3.
[0020] FIG. 7 is a perspective, cross-sectional view of another
embodiment of the resonator chamber of the acoustic damping
resonator system taken along section line 6-6 in FIG. 3.
[0021] FIG. 8 is a cross-sectional side view of resonator chamber
of the acoustic damping resonator system showing a reduced sized
recirculation zone adjacent to and downstream of a resonator
chamber, whereby a high heat transfer starting at a reattachment
point is positioned closer to the resonator than in conventional
systems taken along section line 5-5 in FIG. 3.
[0022] FIG. 9 is a cross-sectional side view of a conventional
resonator chamber.
[0023] FIG. 10 is a cross-sectional side view of a resonator
chamber of the acoustic damping resonator system taken along
section line 5-5 in FIG. 3.
[0024] FIG. 11 is a cross-sectional side view of a conventional
resonator chamber.
[0025] FIG. 12 is a cross-sectional side view of a resonator
chamber of the acoustic damping resonator system taken along
section line 5-5 in FIG. 3.
[0026] FIG. 13 is a cross-sectional side view of another embodiment
of a resonator chamber of the acoustic damping resonator system
taken along section line 5-5 in FIG. 3.
[0027] FIG. 14 is a cross-sectional side view of yet another
embodiment of a resonator chamber of the acoustic damping resonator
system taken along section line 5-5 in FIG. 3.
[0028] FIG. 15 is a cross-sectional top view of a conventional
resonator chamber.
[0029] FIG. 16 is a cross-sectional top view of an embodiment of
the resonator chamber of the acoustic damping resonator system
taken along section line 6-6 in FIG. 3.
[0030] FIG. 17 is a cross-sectional top view of another embodiment
of the resonator chamber of the acoustic damping resonator system
taken along section line 6-6 in FIG. 3.
[0031] FIG. 18 is a cross-sectional top view of an embodiment of
the resonator chamber of the acoustic damping resonator system
taken along section line 6-6 in FIG. 3.
[0032] FIG. 19 is a cross-sectional top view of a conventional
resonator chamber.
[0033] FIG. 20 is a cross-sectional top view of another embodiment
of the resonator chamber of the acoustic damping resonator system
taken along section line 6-6 in FIG. 3.
[0034] FIG. 21 is a cross-sectional top view of yet another
embodiment of the resonator chamber of the acoustic damping
resonator system taken along section line 6-6 in FIG. 3.
[0035] FIG. 22 is a cross-sectional top view of another embodiment
of the resonator chamber of the acoustic damping resonator system
taken along section line 6-6 in FIG. 3.
[0036] FIG. 23 is a cross-sectional top view of still another
embodiment of the resonator chamber of the acoustic damping
resonator system taken along section line 6-6 in FIG. 3.
[0037] FIG. 24 is a cross-sectional top view of another embodiment
of the resonator chamber of the acoustic damping resonator system
taken along section line 6-6 in FIG. 3.
[0038] FIG. 25 is a cross-sectional top view of a conventional
resonator chamber.
[0039] FIG. 26 is a cross-sectional top view of another
conventional resonator chamber.
[0040] FIG. 27 is a cross-sectional top view of an embodiment of
the resonator chamber of the acoustic damping resonator system
taken along section line 6-6 in FIG. 3.
[0041] FIG. 28 is a cross-sectional top view of another embodiment
of the resonator chamber of the acoustic damping resonator system
taken along section line 6-6 in FIG. 3.
[0042] FIG. 29 is a cross-sectional top view of yet another
embodiment of the resonator chamber of the acoustic damping
resonator system taken along section line 6-6 in FIG. 3.
[0043] FIG. 30 is a cross-sectional top view of another embodiment
of the resonator chamber of the acoustic damping resonator system
taken along section line 6-6 in FIG. 3.
[0044] FIG. 31 is a cross-sectional top view of still another
embodiment of the resonator chamber of the acoustic damping
resonator system taken along section line 6-6 in FIG. 3.
[0045] FIG. 32 is a cross-sectional top view of another embodiment
of the resonator chamber of the acoustic damping resonator system
taken along section line 6-6 in FIG. 3.
[0046] FIG. 33 is a cross-sectional top view of another embodiment
of the resonator chamber of the acoustic damping resonator system
taken along section line 6-6 in FIG. 3.
DETAILED DESCRIPTION OF THE INVENTION
[0047] As shown in FIGS. 1-3, 5-8, 10, 12-14, 16-18, 20-24 and
27-33, an acoustically dampened gas turbine engine 10 having a gas
turbine engine combustor 12 with an acoustic damping resonator
system 14 is disclosed. The acoustic damping resonator system 14
may be formed from one or more resonators 16 formed from a
resonator housing 18 positioned within the gas turbine engine
combustor 12 at an outer housing 20 forming a combustor basket 22
and extending circumferentially within the combustor 12. In at
least one embodiment, the resonator housing 18 may include one or
more resonator chambers 24 that provide enhanced cooling with
reduced risk of cracking and other damage. The resonator housing 18
may include resonator exhaust orifices 26 that may be positioned
closer to an area of maximum temperature 28 within the combustor
12, thereby enabling the resonator 16 to reduce the temperature
gradient within the combustor 12. The resonator housing 18 may be
sized and configured to reduce stress found in conventional systems
by increasing distances between resonator exhaust orifices 26 and
between resonator inlet impingement orifices 30, among others.
[0048] In at least one embodiment, the acoustic damping resonator
system 14 for a combustor 12 of a turbine engine 10 may include one
or more resonator housings 18. The resonator housing 18 may extend
for a portion of or entire around a combustor 12, as shown in FIGS.
2 and 3. In at least one embodiment, the resonator housing 18 may
define one or more inner channels 32, as shown in FIGS. 2, 3 and 5,
with an inner surface 34 and an outer surface 36 on an opposite
side of the resonator housing 18 from the inner surface 34. In at
least one embodiment, the resonator housing 18 may be generally
cylindrical, thereby forming a ring with a single inner channel 32
therein.
[0049] The acoustic damping resonator system 14 may include one or
more resonator chambers 24 extending radially outward from the
resonator housing 18. The resonator chamber 24 may have any
appropriate shape. In at least one embodiment, as shown in FIGS.
16-18, 22-24, 27, 32 and 33, the resonator chamber 24 may be shaped
as a quadrilateral with a somewhat triangular shape, a rectangular
shape, as shown in FIGS. 20-21 and 31, or other appropriate shape.
As shown in FIGS. 12-14, the resonator chamber 24 may be formed
from an outer wall 38 that may be supported by one or more
sidewalls 40, such as upstream sidewall 42 and downstream sidewall
44. The resonator chamber 24 may include one or more resonator
inlet impingement orifices 30 in the outer wall 38 of the resonator
chamber 24 and one or more resonator exhaust orifices 26 extending
through the resonator housing 18. The resonator exhaust orifice 26
extending through the resonator housing 18 may be offset axially
upstream to place the resonator exhaust orifice 26 closer to an
area of maximum temperature within the combustor 12.
[0050] In at least one embodiment, as shown in FIG. 12, the
resonator 16 may be shifted further in the upstream direction
relative to the resonator housing 18 such that the resonator 16 is
closer to an area of maximum temperature within the combustor 12.
In at least one embodiment, as shown in FIG. 14, the acoustic
damping resonator system 14 may include a plurality of resonator
exhaust orifices 26 that are positioned closer to an upstream wall
42 of the resonator chamber 24 than a downstream wall 44 of the
resonator chamber 24. As shown in FIGS. 6, 7, 17, 18 and 21, the
resonator exhaust orifices 26 may be spaced further apart from each
other than in conventional systems, as shown in FIGS. 15 and 19 to
reduce the likelihood of cracking in the resonator housing 18. The
plurality of resonator exhaust orifices 26 may be separated from
each other a distance equal to at least one and one half times a
diameter of a smallest diameter of the plurality of resonator
exhaust orifices 26. In another embodiment, the resonator exhaust
orifices 26 may be separated from each other a distance equal to at
least two times a diameter of a smallest diameter of the resonator
exhaust orifices 26. In at least one embodiment, the resonator
exhaust orifices 26 may be collected into a pattern having a shape
of a quadrilateral with a somewhat triangular shape as shown in
FIGS. 16-18 and 22-24, which may also be described as being an
inverted triangle with a point of the triangle pointed downstream,
a rectangular shape, as shown in FIGS. 20-21, or other appropriate
shape.
[0051] As shown in FIGS. 22-24 and 33, the acoustic damping
resonator system 14 may include one or more resonator inlet
impingement orifices 30 that are offset from the plurality of
resonator exhaust orifices 26 such that at least one of the
plurality of resonator inlet impingement orifices 30 is radially
aligned with the resonator housing 16 in which the plurality of
resonator exhaust orifices 26 are positioned such that cooling
fluids flowing into the resonator chamber 24 impinge on the
resonator housing 16. As shown in FIGS. 23-24 and 33, the resonator
inlet impingement orifices 30 may form fewer rows 46 as rows 48
formed by the plurality of resonator exhaust orifices 26. In
another embodiment, as shown in FIGS. 23-24, the resonator inlet
impingement orifices 30 may form half as many rows 46 as rows 48
formed by the plurality of resonator exhaust orifices 26. The rows
46 formed by the plurality of resonator inlet impingement orifices
30 may extend circumferentially and may be aligned radially between
rows 48 of the plurality of resonator exhaust orifices 26 beginning
with a first upstream row 50 of resonator exhaust orifices 26 and
moving downstream. The rows 46 formed by the plurality of resonator
inlet impingement orifices 30 may be positioned closer to an
upstream sidewall 42 than a downstream sidewall 44 to increase
efficiency. In at least one embodiment, the plurality of resonator
inlet impingement orifices 30 may form a first row 52 that has one
fewer orifices 30 than a first row 50 of resonator exhaust orifices
50. As shown in FIG. 24, the plurality of resonator inlet
impingement orifices 30 may form a second row 54 downstream from
the first row 52 of resonator inlet impingement orifices 30,
whereby the second row 54 of resonator inlet impingement orifices
30 has at least two fewer orifices 30 than a second row 56 of
resonator exhaust orifices 26. As shown in FIG. 24, the second row
54 of inlet impingement orifices 30 may skip a position in a middle
of the second row 56 of resonator exhaust orifices 26.
[0052] In another embodiment, as shown in FIG. 33, the plurality of
resonator inlet impingement orifices 30 may form a second row 54
downstream from the first row 52 of resonator inlet impingement
orifices 30, whereby the second row 54 of resonator inlet
impingement orifices 30 has at least one additional orifice 30 than
a first row 52 of resonator inlet impingement orifices 30. The
second row 56 of resonator exhaust orifices 26 may also include at
least one additional resonator exhaust orifice 26 compared to a
first row 50 of resonator exhaust orifices 26. A third row 58 of
the resonator inlet impingement orifices 30 may have at least one
less orifice 30 than a second row 54 of resonator inlet impingement
orifices 30. A third row 59 of the resonator exhaust orifices 26
may have at least one less orifice 26 than a second row 56 of
resonator exhaust orifices 26. The remaining rows of resonator
inlet impingement orifices 30 and resonator exhaust orifices 26 may
reduce in number moving downstream towards the downstream sidewall
44.
[0053] In at least one embodiment, the plurality of inlet
impingement orifices 30 may be separated from each other a distance
equal to at least one and one half times a diameter of a smallest
diameter of the plurality of inlet impingement orifices 30. In
another embodiment, the plurality of inlet impingement orifices 30
may be separated from each other a distance equal to at least two
times a diameter of a smallest diameter of the plurality of inlet
impingement orifices 30.
[0054] In at least one embodiment, as shown in FIGS. 5, 8, 27-32,
the resonator chamber 24 may be configured to increase cooling of
the resonator housing 18 and the combustor 12 without increasing
the amount of cooling air needed. In particular, the resonator
chamber 24 may be reconfigured to extend for a larger distance
axially with a smaller radial height, thereby keeping the volume
within the resonator chamber 24 relatively unchanged in comparison
to conventional systems but exposing a larger amount of surface
area of the resonator housing 18 to cooling fluids. In addition,
the resonator chamber 24 may extend further radially upstream than
conventional systems, which enables the upstream sidewall 42 of the
resonator chamber 24, resonator exhaust orifices 26 or resonator
inlet impingement orifices 30, or any combination thereof, to be
shifted upstream and closer to an area of maximum temperature 28
within the combustor 12. In at least one embodiment, a ratio of
distance between the outer wall 38 of the resonator chamber 24 and
the resonator housing 18 to a diameter of the resonator inlet
impingement orifice 30 may be between about seven and about four.
In another embodiment, the ratio of distance between the outer wall
38 of the resonator chamber 24 and the resonator housing 18 to the
diameter of the resonator inlet impingement orifice 30 is about 6.5
in the middle of the resonator 16. By decreasing the height of the
resonator chamber 24, resonator 16 experiences improved cold side
cooling downstream, in relation to the cold side flow direction, of
the resonators 16 because of formation of a smaller recirculation
zone adjacent to the sidewall 40 than in conventional systems. As
such, a smaller low heat transfer region develops adjacent the
recirculation zone. Instead, the high heat transfer at the
reattachment point develops closer to the resonator 16 than in
conventional systems.
[0055] The outer wall 38 of the resonator chamber 24 may be
configured to enhance the flow of cooling fluids through the
resonator inlet impingement orifices 30 and enhance the impingement
of cooling fluids on the resonator housing 18 within the resonator
chamber 24. In at least one embodiment, as shown in FIG. 10, the
outer wall 38 of the resonator chamber 24 may be thicker than
conventional systems, as shown in FIG. 9, to increase the
effectiveness of the resonator inlet impingement orifices 30. In at
least one embodiment, the outer wall 38 may be sized in thickness
such that a ratio of a length of the at least one resonator inlet
impingement orifice 30 extending radially inward to a diameter of
the resonator inlet impingement orifice 30 is greater than about
0.75. In another embodiment, the outer wall 38 may be sized in
thickness such that a ratio of a length of the at least one
resonator inlet impingement orifice 30 extending radially inward to
a diameter of the resonator inlet impingement orifice 30 is greater
than about one.
[0056] In at least one embodiment, as shown in FIGS. 5, 8, 27-32,
the acoustic damping resonator system 14 may be configured such
that the footprint of the resonator chamber 24 may be enlarged
relative to conventional resonators, yet prevent a maximum internal
resonator dimension 60 extending linearly within the resonator
chamber 24 from being enlarged beyond a point at which the
resonator chamber 24 has a target cutoff frequency that is greater
than an actual damping frequency. The shape of the resonator 16 may
be adapted such that the maximum internal resonator dimension 60 is
not increased in the same relation as the resonator footprint. With
the adapted resonator shape, a shift of the cut off frequency to
higher frequencies is enabled, which ensures reliable damping in
the designed frequency range of the resonator 16. As such, the
acoustic damping resonator system 14 may be formed from a resonator
housing 18 with a one or more resonator chambers 24 as described
above. A ratio of a distance between the outer wall 38 of the
resonator chamber 24 and the resonator housing 18 to a diameter of
the resonator inlet impingement orifice 30 may be between about
seven and about four. As shown in FIGS. 29-31, a maximum internal
resonator dimension 60 extending linearly within the resonator
chamber 24 may be increased less than 12 percent while a footprint
of the resonator chamber 24 on the resonator housing 18 may have
been enlarged by between 40 percent and 100 percent relative to a
resonator chamber 24 having a ratio of greater than eight of a
distance between the outer wall 38 of a resonator chamber 24 and a
resonator housing 18 to a diameter of a resonator inlet impingement
orifice 30. The resonator chamber 24 may have been enlarged and
sized, as set forth above.
[0057] The acoustic damping resonator system 14 may include
resonator chambers 24 having numerous different shapes configured
to prevent a maximum internal resonator dimension 60 extending
linearly within the resonator chamber 24 from being enlarged beyond
a point at which the resonator chamber 24 has a target cutoff
frequency that is greater than an actual damping frequency. In at
least one embodiment, a cross-sectional shape of outer sidewalls 40
forming the resonator chamber 24 may form a modified parallelogram
66, as shown in FIG. 30, in which a maximum internal resonator
dimension 60 has been reduced via truncated intersections 64. The
truncated intersections 64 of the modified parallelogram 66 may be
formed with a first corner side 68 at a first intersection 70 and a
second corner side 72 at a second intersection 74. The first corner
side 68 may extend between first and second sidewalls 76, 78
forming the modified parallelogram 66. The second corner side 72
may extend between third and fourth sidewalls 80, 82 forming the
modified parallelogram 66.
[0058] In another embodiment, as shown in FIG. 29, a
cross-sectional shape of outer sidewalls 40 forming the resonator
chamber 24 may form a modified triangle 84 in which at least two
corners 86 have been truncated with corner sides 88. In at least
one embodiment, each corner of the modified triangle 84 may be
truncated with at least one corner side 88 such that a first corner
side 68 may extend between first and second sidewalls 76, 78, a
second corner side 72 may extend between second and third sidewalls
78, 80 and a third corner side 90 may extend between first and
third sidewalls 76, 80.
[0059] In yet another embodiment, as shown in FIG. 31, a
cross-sectional shape of outer sidewalls 40 forming the resonator
chamber 24 may form a modified rectangle 92 in which at least two
corners 86 have been truncated with corner sides 88. At least two
corners 86 of the modified rectangle 92 may have been truncated
with one or more corner sides 88. In at least one embodiment, each
corner 86 of the modified rectangle 92 may have been truncated with
at least one corner side 88 such that a first corner side 68 may
extend between first and second sidewalls 76, 78, a second corner
side 72 may extend between second and third sidewalls 78, 80, a
third corner side 90 may extend between third and fourth sidewalls
80, 82 and a fourth corner side 94 may extend between first and
fourth sidewalls 76, 82. In at least one embodiment, the modified
rectangle 92 may have equal length sides and be a square.
[0060] As shown in FIG. 32, one or more corners 86 on one or more
sidewalls 40 forming the resonator chamber 24 may be curved. In at
least one embodiment, each corner 86 on each sidewall 40 forming
the resonator chamber 24 may be curved.
[0061] The foregoing is provided for purposes of illustrating,
explaining, and describing embodiments of this invention.
Modifications and adaptations to these embodiments will be apparent
to those skilled in the art and may be made without departing from
the scope or spirit of this invention or the following claims.
* * * * *