US20130298564A1

US20130298564A1 - Cooling system and method for turbine system

Info

Publication number: US20130298564A1
Application number: US13/470,556
Authority: US
Inventors: Krishna Kant Agarwal
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 2012-05-14
Filing date: 2012-05-14
Publication date: 2013-11-14
Also published as: CN103422990A; EP2664748A2; JP2013238389A; RU2013121277A

Abstract

A cooling system and a method for cooling a liner in a turbine system are 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. 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.

Description

FIELD OF THE INVENTION

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

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.
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.
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.
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.
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

Aspects and advantages of the invention will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the invention.
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. 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.
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.
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

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

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 or spirit 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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.
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.

Claims

What is claimed is:

1. A cooling system for a turbine system, comprising:

a liner defining a temperature boundary between a hot side and a cold side, the liner comprising a hot side surface and a cold side surface and defining a hole extending between the hot side surface and the cold side surface, the hole defining a peripheral edge; and

an insert comprising:

a tube extending through the hole, the tube comprising an outer surface, the outer surface and the peripheral edge defining a generally continuous peripheral gap therebetween; and

a plate connected to the tube and disposed in the hot side, the plate extending 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.

2. The cooling system of claim 1, wherein the tube is a generally cylindrical tube, and wherein the plate extends generally radially outward from the outer surface of the tube.

3. The cooling system of claim 1, wherein the plate is a first plate, further comprising a second plate connected to the tube and disposed in the cold side, the second plate extending generally outwardly from the tube such that working fluid flows between the second plate and the cold side surface into the gap.

4. The cooling system of claim 3, further comprising a plurality of studs each extending between the second plate and the cold side surface.

5. The cooling system of claim 1, further comprising a plurality of ribs disposed in the cold side, each of the plurality of ribs connecting the tube and the cold side surface.

6. The cooling system of claim 1, further comprising a plurality of spacers each extending through the gap, each of the plurality of spacers positioning the tube within the hole.

7. The cooling system of claim 6, wherein each of the plurality of spacers is connected to the outer surface of the tube.

8. The cooling system of claim 6, wherein each of the plurality of spacers is connected to the outer surface of the tube and to the peripheral edge, and wherein each of the plurality of spacers further defines a hole therethrough.

9. The cooling system of claim 1, wherein the liner is a combustor liner and the hole is a dilution hole.

10. A combustor for a turbine system, the combustor comprising:

a combustor liner defining a temperature boundary between a combustion zone and a flow passage, the liner comprising a hot side surface and a cold side surface and defining a dilution hole extending between the hot side surface and the cold side surface, the dilution hole defining a peripheral edge; and

an insert comprising:

a tube extending through the dilution hole, the tube comprising an outer surface, the outer surface and the peripheral edge defining a generally continuous peripheral gap therebetween; and

a plate connected to the tube and disposed in the combustion zone, the plate extending 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.

11. The combustor of claim 10, wherein the tube is a generally cylindrical tube, and wherein the plate extends generally radially outward from the outer surface of the tube.

12. The combustor of claim 10, wherein the plate is a first plate, further comprising a second plate connected to the tube and disposed in the flow passage, the second plate extending outwardly from the tube such that working fluid flows between the second plate and the cold side surface into the gap.

13. The combustor of claim 12, further comprising a plurality of studs each extending between the second plate and the cold side surface.

14. The combustor of claim 10, further comprising a plurality of ribs disposed in the flow passage, each of the plurality of ribs connecting the tube and the cold side surface.

15. The combustor of claim 10, further comprising a plurality of spacers each extending through the gap, each of the plurality of spacers positioning the tube within the dilution hole.

16. The combustor of claim 15, wherein each of the plurality of spacers is connected to the outer surface of the tube.

17. The combustor of claim 15, wherein each of the plurality of spacers is connected to the outer surface of the tube and to the peripheral edge, and wherein each of the plurality of spacers further defines a hole therethrough.

18. The combustor of claim 10, wherein the turbine system is a gas turbine system.

19. A method for cooling a liner in a turbine system, the method comprising:

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;

redirecting the working fluid flowed through the gap to form a film proximate a hot side surface of the liner.

20. The method of claim 19, wherein the working fluid is redirected by a plate connected to the tube and extending outwardly from the tube.