FIELD OF THE INVENTION
[0001] The present disclosure relates in general to turbine systems, and more particularly
to cooling systems for turbine systems and in exemplary embodiments cooling systems
for combustors of turbine systems.
BACKGROUND OF THE INVENTION
[0002] Turbine systems are widely utilized in fields such as power generation. For example,
a conventional gas turbine system includes a compressor section, a combustor section,
and at least one turbine section. The compressor section is configured to compress
air as the air flows through the compressor section. The air is then flowed from the
compressor section to the combustor section, where it is mixed with fuel and combusted,
generating a hot gas flow. The hot gas flow is provided to the turbine section, which
utilizes the hot gas flow by extracting energy from it to power the compressor, an
electrical generator, and other various loads.
[0003] Temperature boundaries exist in many locations in turbine systems. For example, in
the combustor of a turbine system, the combustor liner and transition piece are examples
of components defining temperature boundaries. Compressed air flowing through a compressor
is typically flowed upstream in a flow passage past the outside surfaces of the combustor
liner and transition piece before entering a combustion zone defined by inner surfaces
of the combustor liner and transition piece. Due to combustion occurring in the combustion
zone, a temperature differential exists between the flow passage and the combustion
zone, and the air in the flow passage is utilized to cool the combustor liner and
transition piece.
[0004] Further in many cases, portions of the air flowing through the flow passage are diverted
through the combustor liner and/or transition piece into the combustion zone, to cool
the combustor liner and/or transition piece. It is generally desirable for this air
to create a film in the combustion zone adjacent to the inner surfaces of the combustor
liner and/or transition piece, such that the combustor liner and/or transition piece
are film cooled.
[0005] However, in many cases the air flowed through the combustor liner and/or transition
piece, and further in many other cases requiring film cooling of other suitable liners
disposed on temperature boundaries, there may be issues with film formation and resulting
film cooling. For example, in many cases, the air flowed through the liner may cause
recirculation or stagnation zones to form adjacent on the hot side of the liner. Hot
fluids flowing past the liner, such as the hot gas flow in the combustor zone, may
recirculate or stagnate within these zones, causing hot spots on the liner. The existence
of hot spots can lead to uneven thermal stresses in the liner. In many cases, the
thermal stresses can be of a cyclic nature due to system stops and starts, which can
lead to crack initiation.
[0006] Thus, cooling systems and methods for turbine systems are desired in the art. For
example, systems and methods that provide improved film cooling at temperature boundaries
in a turbine system would be advantageous. Further, systems and methods that reduce
or eliminate recirculation and stagnation on liners defining the temperature boundaries
would be advantageous.
BRIEF DESCRIPTION OF THE INVENTION
[0007] Aspects and advantages of the invention will be set forth in part in the following
description, or may be apparent from the description, or may be learned through practice
of the invention.
[0008] In one embodiment, a cooling system for a turbine system is disclosed. The cooling
system includes a liner defining a temperature boundary between a hot side and a cold
side. The liner includes a hot side surface and a cold side surface and defines a
hole extending between the hot side surface and the cold side surface. The hole defines
a peripheral edge. The cooling system further includes an insert. The insert includes
a tube extending through the hole, the tube including an outer surface. The outer
surface and the peripheral edge define a generally continuous peripheral gap therebetween.
The insert further includes a plate connected to the tube and disposed in the hot
side.
[0009] The plate extends outwardly from the tube such that working fluid flowing through
the gap is redirected by the plate to form a film proximate the hot side surface.
[0010] In another embodiment, a method for cooling a liner in a turbine system is disclosed.
The method includes flowing a working fluid through a generally continuous peripheral
gap defined in the liner between an outer surface of a tube disposed in a hole and
a peripheral edge of the hole. The method further includes redirecting the working
fluid flowed through the gap to form a film proximate a hot side surface of the liner.
[0011] These and other features, aspects and advantages of the present invention will become
better understood with reference to the following description and appended claims.
The accompanying drawings, which are incorporated in and constitute a part of this
specification, illustrate embodiments of the invention and, together with the description,
serve to explain the principles of the invention.
BRIEF DESCRIPTION OF THE DRAWINGS
[0012] A full and enabling disclosure of the present invention, including the best mode
thereof, directed to one of ordinary skill in the art, is set forth in the specification,
which makes reference to the appended figures, in which:
FIG. 1 is a schematic view of a gas turbine system according to one embodiment of
the present disclosure;
FIG. 2 is a cross-sectional view of several portions of a gas turbine system according
to one embodiment of the present disclosure;
FIG. 3 is a perspective exploded view of an insert and a liner according to one embodiment
of the present disclosure;
FIG. 4 is a cutaway perspective assembled view of the insert and liner of FIG. 3;
FIG. 5 is a cross-sectional view of the insert and liner of FIG. 4;
FIG. 6 is a cross-sectional view of an insert in a liner according to another embodiment
of the present disclosure;
FIG. 7 is a cutaway perspective view of an insert in a liner according to another
embodiment of the present disclosure;
FIG. 8 is a cross-sectional view of the insert and liner of FIG. 7;
FIG. 9 is a cutaway perspective view of an insert in a liner according to another
embodiment of the present disclosure; and
FIG. 10 is a cross-sectional view of the insert and liner of FIG. 9.
DETAILED DESCRIPTION OF THE INVENTION
[0013] Reference now will be made in detail to embodiments of the invention, one or more
examples of which are illustrated in the drawings. Each example is provided by way
of explanation of the invention, not limitation of the invention. In fact, it will
be apparent to those skilled in the art that various modifications and variations
can be made in the present invention without departing from the scope of the invention.
For instance, features illustrated or described as part of one embodiment can be used
with another embodiment to yield a still further embodiment. Thus, it is intended
that the present invention covers such modifications and variations as come within
the scope of the appended claims and their equivalents.
[0014] FIG. 1 is a schematic diagram of a gas turbine system 10. It should be understood
that the turbine system 10 of the present disclosure need not be a gas turbine system
10, but rather may be any suitable turbine system 10, such as a steam turbine system
or other suitable system. The gas turbine system 10 may include a compressor section
12, a combustor section 14 which may include a plurality of combustors 15 as discussed
below, and a turbine section 16. The compressor section 12 and turbine section 16
may be coupled by a shaft 18. The shaft 18 may be a single shaft or a plurality of
shaft segments coupled together to form shaft 18. The shaft 18 may further be coupled
to a generator or other suitable energy storage device, or may be connected directly
to, for example, an electrical grid. Exhaust gases from the system 10 may be exhausted
into the atmosphere, flowed to a steam turbine or other suitable system, or recycled
through a heat recovery steam generator.
[0015] Referring to FIG. 2, a simplified drawing of several portions of a gas turbine system
10 is illustrated. The gas turbine system 10 as shown in FIG. 2 comprises a compressor
section 12 for pressurizing a working fluid that is flowing through the system 10.
The working fluid is typically air, but may be any suitable liquid or gas. Pressurized
working fluid discharged from the compressor section 12 flows into a combustor section
14, which may include a plurality of combustors 15 (only one of which is illustrated
in FIG. 2) disposed in an annular array about an axis of the system 10. The working
fluid entering the combustor section 14 is mixed with fuel, such as natural gas or
another suitable liquid or gas, and combusted. Hot gases of combustion flow from each
combustor 15 to a turbine section 16 to drive the system 10 and generate power.
[0016] A combustor 15 in the gas turbine 10 may include a variety of components for mixing
and combusting the working fluid and fuel. For example, the combustor 15 may include
a casing 21, such as a compressor discharge casing 21. A variety of sleeves may be
at least partially disposed in the casing 21. For example, a combustor liner 22 may
generally define a combustion zone 24 therein. Combustion of the working fluid, fuel,
and optional oxidizer may generally occur in the combustion zone 24. The resulting
hot gases of combustion may flow downstream in direction 28 through the combustion
liner 22 into a transition piece 26 which further defines the combustion zone, and
then flow through the transition piece 26 and into the turbine section 16.
[0017] An impingement sleeve 32 and flow sleeve 34 may generally circumferentially surround
combustor liner 22 and transition piece 26, as shown. A flow passage 26 surrounding
the combustor liner 22 and transition piece 26, through which working fluid may flow
in an upstream direction 28, may thus further be defined be the impingement sleeve
32 and flow sleeve 34. Thus, the flow passage 26 may be defined between the sleeve
comprising the impingement sleeve 32 and flow sleeve 34 and the sleeve comprising
the combustor liner 22 and transition piece 26. As such, the working fluid flows through
the flow passage 26 in the upstream direction, enters the combustor 15 and is combusted
with the fuel as discussed, and the resulting hot gas flows through the combustion
zone 24 in the downstream direction 28.
[0018] The combustor 15 may further include a fuel nozzle 40 or a plurality of fuel nozzles
40. Fuel may be supplied to the fuel nozzles 40 by one or more manifolds (not shown).
As discussed below, the fuel nozzle 40 or fuel nozzles 40 may supply the fuel and,
optionally, working fluid to the combustion zone 24 for combustion.
[0019] In exemplary embodiments, various holes may be defined in the combustor liner 22
and/or transition piece 26. These holes allow for working fluid flowing past the combustor
liner 22 and/or transition piece 26 to be diverted into the combustion zone 24, typically
for cooling purposes. Dilution holes 42 are one example of such holes. Dilution holes
42 are defined in the combustor liner 22, as shown.
[0020] FIGS. 3 through 10 illustrate various embodiments of a cooling system 50 for a turbine
system 10 according to the present disclosure. The system 50 includes a liner 60.
The liner 60 defines a temperature boundary between a hot side 62 and a cold side
64, and includes a hot side surface 66 and a cold side surface 68. The temperature
in the hot side 62 is relatively hotter than the temperature in the cold side 64.
The liner 60 is disposed on and defines the temperature boundary, so the hot size
surface 66 of the liner 60 faces the hot side 62 and the cold side surface 68 of the
liner 60 faces the cold side 64.
[0021] One or more holes 70 may be defined in the liner 60. Each hole 70 may extend between
the hot side surface 66 and the cold side surface 68. A peripheral edge 72 may be
defined by the hole 70 in the liner 60. The peripheral edge 72 may define an outer
boundary of the hole 70. A hole according to the present disclosure may have any suitable
shape and size. For example, in some embodiments, a hole may have a generally circular
or oval cross-sectional shape. In other embodiments, a hole may have a generally rectangular,
triangular, or other suitable polygonal shape.
[0022] One exemplary embodiment of a liner 60 is a combustor liner 22. As discussed above,
the combustor liner 22 defines a temperature boundary between a hot side 62, such
as a combustion zone 24, and a cold side surface 64, such as a flow passage 36. One
or more holes 70, such as dilution holes 42, are defined in the combustor liner 22.
It should be understood, however, that the present disclosure is not limited to combustor
liners 22 as liners 60. Rather, any suitable liner defining a temperature boundary,
such as a transition piece 26 or other suitable liner component, is within the scope
and spirit of the present disclosure.
[0023] A cooling system 50 according to the present disclosure further includes one or more
inserts 80. Each insert 80 is disposed in a hole 70 in a liner 60, and facilitates
film cooling of the liner 60 adjacent to the hole 70. In particular, the use of an
insert 80 in a hole 70 in a liner 60 reduces recirculation and stagnation adjacent
to the hole 70. The insert 80 directs working fluid 82 flowing through the hole 70,
such as a portion of the working fluid 84 as discussed below, to form a film proximate
the liner 60, which facilitates film cooling. Thus, the use of a cooling system 50
according to the present disclosure may advantageously reduce the existence of hot
spots and resulting uneven thermal stresses in liners 60. This may further advantageously
reduce the formation of cracks in the liner 60, especially adjacent to the holes 70
in which inserts 80 are disposed.
[0024] As shown in FIGS. 3 through 10, an insert 80 according to the present disclosure
includes a tube 90. The tube 90 may include an inner surface 92, and includes an outer
surface 94. In embodiments wherein the tube 90 includes an inner surface 92, the inner
surface 92 may define an interior 96 of the tube 90. The interior 96 may be generally
hollow as shown, thus allowing working fluid 82 to flow therethrough. In other embodiments,
the tube 90 may be generally solid, such that no inner surface 92 can be defined.
The tube 90 may have any suitable cross-sectional shape and size. For example, in
some embodiments, the tube 90 may be cylindrical, and thus have a generally circular
or oval cross-sectional shape. In other embodiments, a hole may have a generally rectangular,
triangular, or other suitable polygonal shape. As shown, the tube 90 of an insert
80 extends through a hole 70 in a liner 60. When positioned in the hole 70, the outer
surface 94 of the tube 90 and the peripheral edge 72 of the hole 70 define a gap 98
therebetween. The gap 98 is a generally continuous peripheral gap that extends peripherally
around the entire tube 90, and thus peripherally about the entire outer surface 94,
as well as peripherally around the entire peripheral edge 72. As discussed, some of
the working fluid 82 flowing through the flow passage 26 may flow through the hole
70. As shown, due to the insert 80 being positioned in the hole 70, while some of
this working fluid 82 may flow through the interior 96 of the tube 90, a portion 84
of the working fluid 82 may flow between the hole 70 and the outer surface 94 of the
tube 90, and thus through the peripheral gap 98. As discussed below, this portion
84 of the working fluid 82 may, after flowing through the peripheral gap 98, be redirected
to form a film proximate the hot side surface 66.
[0025] As further shown in FIGS. 3 through 10, a insert 80 according to the present disclosure
further includes a plate 100, also known as a first plate 100. The plate 100 is connected
to the tube 90, such as to the outer surface 94 thereof. For example, the plate 100
may be welded to the tube 90, mechanically connected to the tube 90 such as through
screws, rivets, nut-bolt combinations, etc., or formed with the tube 90 as a singular
component. In exemplary embodiments, the plate 100 extends around the entire periphery
of the tube 90, and is connected to an entire peripheral portion of the outer surface
94. When the insert 80 is positioned extending through the hole 70, the plate 100
is disposed in the hot side 62 of the liner 60.
[0026] The plate 100 may extend generally outwardly from tube 90, such as from the outer
surface 94 away from the inner surface 92. For example, the plate 100 may extend generally
transverse to and outwardly from the tube 90. In embodiments wherein the tube 90 is
generally cylindrical, and thus has a circular or oval cross-section, the plate 100
may extend radially outward from the tube 90. Alternatively, the plate 100 may extend
from the tube 90 at any suitable angle to the transverse or radial direction.
[0027] As shown, the plate 100 may redirect a portion 84 of the working fluid 82 flowing
through the hole 70. The portion 84 that flows through the peripheral gap 98 may contact
or flow proximate to the plate 100. Due to the positioning of the plate 100, the plate
100 may cause the portion 84 of the working fluid 82 to turn and flow between the
plate 100 and the hot side surface 66 of the liner 60. This redirection in flow results
in a film of working fluid 82, which includes the portion 84, being formed and flowing
proximate the hot side surface 66. Such redirection of the portion 84 of the working
fluid 82 by the plate thus facilitates formation of a film of working fluid 82 quickly
and proximate the associated hole 70, and thus advantageously reduce the existence
of hot spots and resulting uneven thermal stresses in liners 60, particularly proximate
holes 70.
[0028] In some embodiments, as shown in FIGS. 3 through 6, an insert 80 according to the
present disclosure further includes a second plate 102. The second plate 102 may be
connected to the tube 90, such as to the outer surface 94 thereof. For example, the
second plate 102 may be welded to the tube 90, mechanically connected to the tube
90 such as through screws, rivets, nut-bolt combinations, etc., or formed with the
tube 90 as a singular component. In exemplary embodiments, the second plate 102 extends
around the entire periphery of the tube 90, and is connected to an entire peripheral
portion of the outer surface 94. When the insert 80 is positioned extending through
the hole 70, the second plate 102 is disposed in the cold side 64 of the liner 60.
[0029] The second plate 102 may extend generally outwardly from tube 90, such as from the
outer surface 94 away from the inner surface 92. For example, the second plate 102
may extend generally transverse to and outwardly from the tube 90. In embodiments
wherein the tube 90 is generally cylindrical, and thus has a circular or oval cross-section,
the second plate 102 may extend radially outward from the tube 90. Alternatively,
the second plate 102 may extend from the tube 90 at any suitable angle to the transverse
or radial direction.
[0030] As shown, the plate 100 may capture and direct working fluid 82 towards the hole
70. The working fluid 82 may thus flow between the second plate 102 and the cold side
surface 68 of the liner. A portion 84 of the working fluid 82 may flow through the
hole 70, and specifically through the peripheral gap 98 as discussed above, and then
be redirected to form a film as discussed.
[0031] An insert 80 according to the present disclosure may be connected to a liner 60 using
any suitable connection methods or apparatus. In some embodiments, as shown in FIGS.
3 through 6, for example, one or more studs 110 may be utilized to connect the insert
80 to the liner 60. In exemplary embodiments, as shown, the studs 110 may extend between
the second plate 102 and the cold side surface 68. In other embodiments, studs 110
may extend between the first plate 100 and the hot side surface 66. Any number of
studs 110 may be utilized, in any suitable pattern that suitably connects the insert
80 to the liner 60. For example, eight studs 110 may be arranged in a generally annular
array, as shown in FIG. 3. Alternatively, one, two, three, four, five, six, seven,
nine, ten or more studs 110 may be utilized, and/or the studs 110 may have any suitable
arrangement. Each stud 110 may have any suitable shape and or size. The studs 110
may be welded, mechanically connected or formed as a unitary component with the insert
80 and/or the liner 60.
[0032] In other embodiments, as shown in FIGS. 7 and 8, one or more ribs 120 may connect
the insert 80 and liner 60. Ribs 120 may be utilized in embodiments including or not
including a second plate 102. For example, in some embodiments as shown, each rib
120 may extend between and connect the tube 90, such as the outer surface 94 thereof,
and the cold side surface 68. Any number of ribs 120 may be utilized, in any suitable
pattern that suitably connects the insert 80 to the liner 60. For example, four ribs
120 may be arranged in a generally annular array, or alternatively, one, two, three,
five, six, seven, eight, nine, ten or more ribs 120 may be utilized, and/or the ribs
120 may have any suitable arrangement. Each ribs 120 may have any suitable shape and
or size. For example, in some embodiments, a rib 120 may be generally curvilinear
as shown. In other embodiments, a rib 120 may be generally linear, and/or may have
various linear and/or curvilinear portions. The ribs 120 may be welded, mechanically
connected or formed as a unitary component with the insert 80 and/or the liner 60.
[0033] In some embodiments, as shown in FIGS. 6, 9 and 10, one or more spacers 130 may be
included in the insert 80. The spacers 130 may position the insert 80 within the hole
70, and may in some embodiments further connect the insert 80 to the liner 60. For
example, as shown in FIGS. 9 and 10, the spacers 130 may connect the insert 80 to
the liner 60. Each spacer 130 may extend between and connect the peripheral edge 72
of the hole 70 and the outer surface 94 of the tube 90. Any number of spacers 130
may be utilized, in any suitable pattern that suitably connects the insert 80 to the
liner 60. For example, four spacer 130 may be arranged in a generally annular array,
or alternatively, one, two, three, five, six, seven, eight, nine, ten or more spacers
130 may be utilized, and/or the spacers 130 may have any suitable arrangement. Each
spacer 130 may have any suitable shape and or size. The spacers 130 may be welded,
mechanically connected or formed as a unitary component with the insert 80, such as
the outer surface 94 of the tube 90, and/or the liner 60, such as the peripheral edge
72 of the hole 70. Further, one or more holes 132 may be defined in each spacer 130.
Holes 132 are particularly necessary in embodiments wherein the spacers 130 connect
the insert 80 to the liner 60, in order to provide and maintain the continuous peripheral
gap 98 between the hole 70 and the tube 90.
[0034] In other embodiments, as shown in FIG. 6, the spacers 130 may not connect the insert
80 to the liner 60, and may rather simply maintain the position of the tube 90 within
the hole 70. As discussed above, the spacers 130 in these embodiments may have any
suitable shape and size, and any suitable number of spacers 130 in any suitable pattern
may be utilized. The spacers 130 may be connected, such as welded, mechanically connected
or formed as a unitary component with, either the insert 80, such as the outer surface
94 of the tube 90, as shown or the liner 60, such as the peripheral edge 72 of the
hole 70. The spacers 130 may not be connected to the other of the insert 80 and the
liner 60, thus maintaining the continuous peripheral gap 98 while serving to position
the tube 90 within the hole 70.
[0035] The present disclosure is further directed to methods for cooling a liner 60 in a
turbine system 10. The method may include, for example, flowing a working fluid 82,
such as a portion 84 thereof, through a generally continuous peripheral gap 98 defined
in the liner 60 between an outer surface 94 of a tube 90 disposed in a hole 70 and
a peripheral edge 72 of the hole 70. The method may further include, for example,
redirecting the working fluid 82, such as the portion 84 thereof, flowed through the
gap 98 to form a film proximate a hot side surface 66 of the liner 60.
[0036] This written description uses examples to disclose the invention, including the best
mode, and also to enable any person skilled in the art to practice the invention,
including making and using any devices or systems and performing any incorporated
methods. The patentable scope of the invention is defined by the claims, and may include
other examples that occur to those skilled in the art. Such other examples are intended
to be within the scope of the claims if they include structural elements that do not
differ from the literal language of the claims, or if they include equivalent structural
elements with insubstantial differences from the literal languages of the claims.
1. A cooling system (50) for a turbine system (10), comprising:
a liner (60) defining a temperature boundary between a hot side (62) and a cold side
(64), the liner (60) comprising a hot side surface (66) and a cold side surface (68)
and defining a hole (70) extending between the hot side surface (66) and the cold
side surface (68), the hole (70) defining a peripheral edge (72); and
an insert (80) comprising:
a tube (90) extending through the hole (70), the tube (90) comprising an outer surface
(94), the outer surface (94) and the peripheral edge (72) defining a generally continuous
peripheral gap (98) therebetween; and
a plate (100) connected to the tube (90) and disposed in the hot side (62), the plate
(100) extending outwardly from the tube (90) such that working fluid (82) flowing
through the gap (98) is redirected by the plate (100) to form a film proximate the
hot side surface (66).
2. The cooling system (50) of claim 1, wherein the tube (90) is a generally cylindrical
tube (90), and wherein the plate (100) extends generally radially outward from the
outer surface (94) of the tube (90).
3. The cooling system (50) of either of claim 1 or 2, wherein the plate (100) is a first
plate (100), further comprising a second plate (102) connected to the tube (90) and
disposed in the cold side (64), the second plate (102) extending generally outwardly
from the tube (90) such that working fluid (82) flows between the second plate (102)
and the cold side surface (68) into the gap (98).
4. The cooling system (50) of claim 3, further comprising a plurality of studs (110)
each extending between the second plate (102) and the cold side surface (68).
5. The cooling system (50) of any of claims 1 to 4, further comprising a plurality of
ribs (120) disposed in the cold side (64), each of the plurality of ribs (120) connecting
the tube (90) and the cold side surface (68).
6. The cooling system (50) of any of claims 1 to 5, further comprising a plurality of
spacers (130) each extending through the gap (98), each of the plurality of spacers
(130) positioning the tube (90) within the hole (70).
7. The cooling system (50) of claim 6, wherein each of the plurality of spacers (130)
is connected to the outer surface (94) of the tube (90).
8. The cooling system (50) of either of claim 6 or 7, wherein each of the plurality of
spacers (130) is connected to the outer surface (94) of the tube (90) and to the peripheral
edge (72), and wherein each of the plurality of spacers (130) further defines a hole
(132) therethrough.
9. The cooling system (50) of any of claims 1-8, wherein the liner (60) is a combustor
liner (22) and the hole (70) is a dilution hole (42).
10. A combustor (15) for a turbine system (10), the combustor (15) comprising:
a combustor liner (22) defining a temperature boundary between a combustion zone (24)
and a flow passage (36), the liner (60) comprising a hot side surface (66) and a cold
side surface (68) and defining a dilution hole (42) extending between the hot side
surface (66) and the cold side surface (68), the dilution hole (42) defining a peripheral
edge (72); and
an insert (80) comprising:
a tube (90) extending through the dilution hole (42), the tube (90) comprising an
outer surface (94), the outer surface (94) and the peripheral edge (72) defining a
generally continuous peripheral gap (98) therebetween; and
a plate (100) connected to the tube (90) and disposed in the combustion zone (24),
the plate (100) extending outwardly from the tube (90) such that working fluid (82)
flowing through the gap (98) is redirected by the plate (100) to form a film proximate
the hot side surface (66).
11. The combustor (15) of claim 10, wherein the tube (90) is a generally cylindrical tube
(90), and wherein the plate (100) extends generally radially outward from the outer
surface (94) of the tube (90).
12. The combustor (15) of either of claim 10 or 11, wherein the plate (100) is a first
plate (100), further comprising a second plate (102) connected to the tube (90) and
disposed in the flow passage (36), the second plate (102) extending outwardly from
the tube (90) such that working fluid (82) flows between the second plate (102) and
the cold side surface (68) into the gap (98).
13. The combustor (15) of any of claims 10 to 12, further comprising a plurality of ribs
(120) disposed in the flow passage (36), each of the plurality of ribs (120) connecting
the tube (90) and the cold side surface (68).
14. The combustor (15) of any of claims 10 to 13, further comprising a plurality of spacers
(130) each extending through the gap (98), each of the plurality of spacers (130)
positioning the tube (90) within the dilution hole (42).
15. A method for cooling a liner (60) in a turbine system (10), the method comprising:
flowing a working fluid (82) through a generally continuous peripheral gap (98) defined
in the liner (60) between an outer surface (94) of a tube (90) disposed in a hole
(70) and a peripheral edge of the hole (72);
redirecting the working fluid (82) flowed through the gap (98) to form a film proximate
a hot side surface (66) of the liner (60).