US20230266005A1

US20230266005A1 - Double-skin liner for a gas turbine

Info

Publication number: US20230266005A1
Application number: US18/310,365
Authority: US
Inventors: Yousef Bagheri; Abbas Fakhr Tabatabaei; Elahe Yoosefi; Seyed Milad Mostafavi; Sana Sattarifar
Original assignee: Mapna Turbine Engineering And Manufacturing Co
Current assignee: Mapna Turbine Engineering And Manufacturing Co
Priority date: 2022-05-02
Filing date: 2023-05-01
Publication date: 2023-08-24
Also published as: WO2023214294A1

Abstract

A double-skin liner for a combustion chamber of a gas turbine. The double-skin liner includes an inner layer, an outer layer with an expansion gap provided on the outer layer, a gap covering element, a sealing element, a plurality of internal cooling holes provided on the inner layer, and a plurality of external cooling holes provided on the outer layer. When the inner layer expands due to temperature increase, a proximal section of the outer layer and a distal section of the outer layer distance from each other through lengthening the expansion gap.

Description

CROSS-REFERENCE TO RELATED APPLICATION

This application takes priority from pending U.S. Provisional Patent Application Ser. No. 63/337,174, filed on May 2, 2022, and entitled “DOUBLE SKIN LINER” which is incorporated herein by reference in its entirety.

TECHNICAL FIELD

The present disclosure generally relates to gas turbines and particularly relates to thermal expansion in liners of gas turbines. This disclosure specifically relates to a new structure for liners of gas turbines to eliminate the problems caused by thermal expansion in liners.

BACKGROUND

One of the most important problems in a gas turbine is the issue of controlling thermal expansion in hot gas pipeline components of the gas turbine. Reasons for the importance of this issue may include, but not limited to, thermal stresses due to mechanical constraints, leakage of cooling air, and possible vibrations of different parts. Therefore, geometry and structure of the components may be designed in such a way that they do not only provide sufficient strength but also allow expansion in the components to prevent high stresses.
Combustion chamber components, which are one of the most important parts of a gas turbine, are constantly exposed to hot gases and may be cooled by air with a lower temperature. Liner is one of these parts. One of the effective methods in liner cooling is the use of double skin liners. In such liners, the cooling air may enter the space between the two layers from the outside space and may be exposed to the inner layer which is in contact with the hot gas. In double skin liners, the outer layer may be in contact with the cooling air and the inner layer may be in contact with the hot gases from combustion. For this reason, the temperature of the inner layer is always higher than the temperature of the outer layer, and in some cases, this temperature difference may reach an average of 400 degrees Celsius.
This temperature difference may create limitations in the connection between the two layers of liner, and the connection of the two layers may be such as to maintain continuity in motion and strength, and at the same time may allow relative movement of the two layers due to different amounts of thermal expansion. Different methods and designs have been proposed to control the relative thermal expansion between these two layers but these methods and designs have some drawbacks. For example, they are not cost-effective. Furthermore, they are not such effective in controlling the relative thermal expansion between the two layers. There is, therefore, a need for a cost-effective double skin liner that is able to provide the necessary degrees of freedom for expansion of the inner layer and at the same time is able to maintain the strength of the liner structure.

SUMMARY

This summary is intended to provide an overview of the subject matter of the present disclosure, and is not intended to identify essential elements or key elements of the subject matter, nor is it intended to be used to determine the scope of the claimed implementations. The proper scope of the present disclosure may be ascertained from the claims set forth below in view of the detailed description below and the drawings.
In one general aspect, the present disclosure describes an exemplary double-skin liner for a combustion chamber of a gas turbine. In an exemplary embodiment, the double-skin liner may include an inner layer, an outer layer, a gap covering element, a sealing element, a plurality of internal cooling holes, and a plurality of external cooling holes.
In an exemplary embodiment, the inner layer may be cylindrical. In an exemplary embodiment, the outer layer may be cylindrical. In an exemplary embodiment, a first end of the inner layer may be fixedly attached to a first end of the outer layer. In an exemplary embodiment, a second end of the inner layer may be attached to a second end of the outer layer. In an exemplary embodiment, the inner layer and the outer layer may form a cooling gap between the inner layer and the outer layer.
In an exemplary embodiment, the outer layer may include a proximal section, a distal section, and an expansion gap. In an exemplary embodiment, the expansion gap may be provided on the outer layer between the proximal section and the distal section. In an exemplary embodiment, the expansion gap may include a 360-degree cylindrical gap.
In an exemplary embodiment, the gap covering element may be cylindrical. In an exemplary embodiment, the gap covering element may be attached to an outer surface of the outer layer. In an exemplary embodiment, a first end of the gap covering element may be fixedly attached to the distal section of the outer layer. In an exemplary embodiment, a second end of the gap covering element may be movably attached to the proximal section of the outer layer. In an exemplary embodiment, the gap covering element may be configured to prevent air communication between the cooling gap and an outer space of the outer layer through the expansion gap.
In an exemplary embodiment, the gap covering element may include a first flat section, a second flat section, and a curved section. In an exemplary embodiment, the first flat section may be at the first end of the gap covering element. In an exemplary embodiment, the first flat section may be fixedly attached to the distal section of the outer layer. In an exemplary embodiment, the second flat section may be at the second end of the gap covering element. In an exemplary embodiment, the second section may be movably disposed onto the proximal section of the outer layer. In an exemplary embodiment, the curved section may be attached between the first flat section and the second flat section.
In an exemplary embodiment, the sealing element may be attached to the outer surface of the outer layer. In an exemplary embodiment, the gap covering element may be disposed between the outer layer and the sealing element. In an exemplary embodiment, the sealing element may be configured to form a seal between the double-skin liner and a transition piece when a distal end of the double-skin liner is inserted into the transition piece.
In an exemplary embodiment, the plurality of internal cooling holes may be provided on the inner layer. In an exemplary embodiment, the plurality of internal cooling holes may be configured to provide air communication between an inner space of the inner layer and the cooling gap. In an exemplary embodiment, the plurality of external cooling holes may be provided on the outer layer. In an exemplary embodiment, the plurality of external cooling holes may be configured to provide air communication between the cooling gap and an outer space of the outer layer.
In an exemplary embodiment, the proximal section of the outer layer and the distal section of the outer layer may be configured to distance from each other through lengthening the expansion gap when the inner layer expands. In an exemplary embodiment, the plurality of internal cooling holes, the cooling gap, and the plurality of external cooling holes may be configured to provide cooling mechanism for the double-skin liner. In an exemplary embodiment, the second flat section may be configured to move along the proximal section of the outer layer when to the proximal section of the outer layer and the distal section of the outer layer distance from each other.
In one general aspect, the present disclosure describes also a turbine combustor including a combustor liner. In an exemplary embodiment, the combustor liner may include a hollow cylindrical shape. In an exemplary embodiment, the combustor liner may include an inner layer, an outer layer and a gap sealing element.
In an exemplary embodiment, the inner layer may include a hollow cylindrical shape that may be disposed about a central axis of the combustor liner. In an exemplary embodiment, the inner layer may include an upstream end and a downstream end with respect to combustion gas flow during operation.
In an exemplary embodiment, the outer layer may include a hollow cylindrical shape. In an exemplary embodiment, the outer layer may be disposed outside the inner layer in a radial direction surrounding the inner layer. In an exemplary embodiment, the outer layer may include a first section and a second section. In an exemplary embodiment, the first section may be upstream of the second section with respect to the combustion gas flow during operation.
In an exemplary embodiment, the first section of the outer layer may include an upstream end and a downstream end with respect to the combustion gas flow during operation. In an exemplary embodiment, the second section of the outer layer may include an upstream end and a downstream end with respect to the combustion gas flow during operation. In an exemplary embodiment, the upstream end of the first section of the outer layer may be attached to the upstream end of the inner layer. In an exemplary embodiment, the downstream end of the second section of the outer layer may be attached to the downstream end of the inner layer.
In an exemplary embodiment, the downstream end of the first section of the outer layer may be mounted adjacent the upstream end of the second section of the outer layer with a gap between the downstream end of the first section of the outer layer and the upstream end of the second section of the outer layer. In an exemplary embodiment, the gap may be configured at least equivalent to distance that the first section of the outer layer and the second section of the outer layer may be configured to expand due to the combustion gas.
In an exemplary embodiment, the gap sealing element may include a hollow cylindrical shape that may be disposed outside the gap in a radial direction surrounding the gap. In an exemplary embodiment, the gap sealing element may include an upstream end and a downstream end with respect to the combustion gas flow during operation. In an exemplary embodiment, the upstream end of the gap sealing element may be configured in contact with the first section of the outer layer.
In an exemplary embodiment, the downstream end of the gap sealing element may be configured in contact with the second section of the outer layer. In an exemplary embodiment, the gap sealing element may be configured to seal the gap and to disconnect air communication between the gap and an outside of the outer layer.
In an exemplary embodiment, the turbine combustor may include a transition piece. In an exemplary embodiment, the transition piece may be connected to the second section of the outer layer in a radial direction via a hula seal. In an exemplary embodiment, the transition piece may be configured to bring out the combustion gas.
In an exemplary embodiment, the upstream end of the first section of the outer layer may be welded to the upstream end of the inner layer. In an exemplary embodiment, the downstream end of the second section of the outer layer may be welded to the downstream end of the inner layer.
In an exemplary embodiment, the upstream end of the gap sealing element may be attached to the first section of the outer layer. In an exemplary embodiment, the downstream end of the gap sealing element may be configured in contact with the second section of the outer layer. In an exemplary embodiment, the downstream end of the gap sealing element may further be configured to be slidable on the second section of the outer layer. In an exemplary embodiment, the upstream end of the gap sealing element may be welded to the first section of the outer layer.
In an exemplary embodiment, the downstream end of the gap sealing element may be attached to the second section of the outer layer. In an exemplary embodiment, the upstream end of the gap sealing element may be configured in contact with the first section of the outer layer. In an exemplary embodiment, the upstream end of the gap sealing element may further be configured to be slidable on the first section of the outer layer. In an exemplary embodiment, the downstream end of the gap sealing element may be welded to the second section of the outer layer.

BRIEF DESCRIPTION OF THE DRAWINGS

The drawing figures depict one or more implementations in accord with the present teachings, by way of example only, not by way of limitation. In the figures, like reference numerals refer to the same or similar elements.

FIG. 1A illustrates a perspective view of an exemplary double-skin liner, consistent with one or more exemplary embodiments of the present disclosure.

FIG. 1B illustrates a side view of a double-skin liner of a gas turbine in a scenario in which the double-skin liner is attached to a transition piece, consistent with one or more exemplary embodiments of the present disclosure.

FIG. 2A illustrates a detailed section view of a double-skin liner in a scenario in which a distal end of the double-skin liner is inserted into a transition piece, consistent with one or more exemplary embodiments of the present disclosure.

FIG. 2B illustrates a detailed section view of a double-skin liner, consistent with one or more exemplary embodiments of the present disclosure.

FIG. 2C illustrates a side view of a double-skin liner, consistent with one or more exemplary embodiments of the present disclosure.

FIG. 2D illustrates a section perspective view of a double-skin liner, consistent with one or more exemplary embodiments of the present disclosure.

FIG. 3A illustrates a perspective view of a gap covering element, consistent with one or more exemplary embodiments of the present disclosure.

FIG. 3B illustrates a perspective section view of a gap covering element, consistent with one or more exemplary embodiments of the present disclosure.

FIG. 3C illustrates a section view of a gap covering element, consistent with one or more exemplary embodiments of the present disclosure.

FIG. 4 illustrates a partial schematic illustration of a turbine combustor with a conventional combustor liner and a transition piece, consistent with one or more exemplary embodiments of the present disclosure.

FIG. 5 illustrates a partial but more detailed schematic illustration of a combustor liner and a transition piece interface region, consistent with one or more exemplary embodiments of the present disclosure.

FIG. 6 illustrates a simplified, partial section of a portion of a combustor liner with a gap and a gap sealing element configured between the combustor liner and a hula seal, consistent with one or more exemplary embodiments of the present disclosure.

FIG. 7 illustrates a simplified, partial section of a combustor liner with a plurality of an inner layer holes and a plurality of an outer layer holes, consistent with one or more exemplary embodiments of the present disclosure.

DETAILED DESCRIPTION

In the following detailed description, numerous specific details are set forth by way of examples in order to provide a thorough understanding of the relevant teachings. However, it should be apparent that the present teachings may be practiced without such details. In other instances, well known methods, procedures, components, and/or circuitry have been described at a relatively high-level, without detail, in order to avoid unnecessarily obscuring aspects of the present teachings.
The following detailed description is presented to enable a person skilled in the art to make and use the methods and devices disclosed in exemplary embodiments of the present disclosure. For purposes of explanation, specific nomenclature is set forth to provide a thorough understanding of the present disclosure. However, it will be apparent to one skilled in the art that these specific details are not required to practice the disclosed exemplary embodiments. Descriptions of specific exemplary embodiments are provided only as representative examples. Various modifications to the exemplary implementations will be readily apparent to one skilled in the art, and the general principles defined herein may be applied to other implementations and applications without departing from the scope of the present disclosure. The present disclosure is not intended to be limited to the implementations shown, but is to be accorded the widest possible scope consistent with the principles and features disclosed herein.
Herein is disclosed a double-skin liner for a combustion chamber of a gas turbine. An exemplary double-skin liner may include an inner layer and an outer layer. Distal ends of the inner layer and the outer layer are attached to each other and proximal ends of the inner layer and the outer layer are also attached to each other. The outer layer includes a 360-degree expansion gap provided on the outer layer which divides the outer layer to a proximal section and a distal section. When the inner layer is expanded due to an increase in a temperature of the inner layer, the proximal section and the distal section of the outer layer distance from each other and the 360-degree expansion gap lengthens. Therefore, by providing the 360-degree expansion gap, when the inner layer is expanded due to an increase in a temperature of the inner layer, the proximal section and the distal section of the outer layer can easily distance from each other without imposing any distortion to the outer layer.
FIG. 1A shows a perspective view of a double-skin liner 100, consistent with one or more exemplary embodiments of the present disclosure. FIG. 1B shows a side view of double-skin liner 100 of a gas turbine in a scenario in which double-skin liner 100 is attached to a transition piece 110, consistent with one or more exemplary embodiments of the present disclosure. As shown in FIG. 1B, in an exemplary embodiment, a distal end 101 of double-skin liner 100 may be inserted into transition piece 110.
FIG. 2A shows a detailed section view of double-skin liner 100 in a scenario in which distal end 101 of double-skin liner 100 is inserted into transition piece 110, consistent with one or more exemplary embodiments of the present disclosure. FIG. 2B shows a detailed section view of double-skin liner 100, consistent with one or more exemplary embodiments of the present disclosure. FIG. 2C shows a side view of double-skin liner 100, consistent with one or more exemplary embodiments of the present disclosure. FIG. 2D shows a section perspective view of double-skin liner 100, consistent with one or more exemplary embodiments of the present disclosure. As shown in FIG. 2A, FIG. 2B, FIG. 2C, and FIG. 2D, in an exemplary embodiment, double-skin liner 100 may include an inner layer 104 and an outer layer 106.
In an exemplary embodiment, a first end 142 of inner layer 104 may be fixedly attached to a first end 162 of outer layer 106. In an exemplary embodiment, when first end 142 of inner layer 104 is fixedly attached to first end 162 of outer layer 106, it may mean that first end 142 of inner layer 104 is attached to first end 162 of outer layer 106 in such a way that any relative movement between first end 142 of inner layer 104 and first end 162 of outer layer 106 is prevented. In an exemplary embodiment, a second end 144 of inner layer 104 may be fixedly attached to a second end 164 of outer layer 106. In an exemplary embodiment, when second end 144 of inner layer 104 is fixedly attached to second end 164 of outer layer 106, it may mean that second end 144 of inner layer 104 is attached to second end 164 of outer layer 106 in such a way that any relative movement between second end 144 of inner layer 104 and second end 164 of outer layer 106 is prevented.
As further shown in FIG. 2A, FIG. 2B, FIG. 2C, and FIG. 2D, in an exemplary embodiment, inner layer 104 and outer layer 106 may form a cooling gap 210 between inner layer 104 and outer layer 106. In an exemplary embodiment, cooling gap 210 may be a cylindrical gap between inner layer 104 and outer layer 106. As shown in FIG. 2B, in an exemplary embodiment, outer layer 106 may include a proximal section 162 and a distal section 164. In an exemplary embodiment, outer layer 106 may further include an expansion gap 166. In an exemplary embodiment, expansion gap 166 may be provided between proximal section 162 and distal section 164 of outer layer 106. In an exemplary embodiment, expansion gap 166 may be a 360-degree gap. In an exemplary embodiment, when expansion gap 166 is a 360-degree gap, it may mean that expansion gap 16 is a cylindrical gap provided on outer layer 106 that may separate proximal section 162 of outer layer 106 from distal section 164 of outer layer 106. In an exemplary embodiment, when inner layer 104 is expanded due to a temperature increase in inner layer 104, proximal section 162 of outer layer 106 and distal section 164 of outer layer may be distanced from each other due to expansion gap 166 provided between proximal section 162 of outer layer 106 and distal section 164 of outer layer. In an exemplary embodiment, when inner layer 104 is expanded due to a temperature increase in inner layer 104, expansion gap 166 may lengthen and proximal section 162 of outer layer 106 and distal section 164 of outer layer may be distanced from each other.
As further shown in FIG. 2B and FIG. 2D, in an exemplary embodiment, double-skin liner 100 may further include a gap covering element 202. FIG. 3A shows a perspective view of gap covering element 202, consistent with one or more exemplary embodiments of the present disclosure. FIG. 3B shows a perspective section view of gap covering element 202, consistent with one or more exemplary embodiments of the present disclosure. FIG. 3C shows a section view of gap covering element 202, consistent with one or more exemplary embodiments of the present disclosure. As shown in FIG. 3A, in an exemplary embodiment, gap covering element 202 may be a cylindrical element. In an exemplary embodiment, gap covering element 202 may be attached to an outer surface 166 of outer layer 106. In an exemplary embodiment, a first end 222 of gap covering element 202 may be fixedly attached to distal section 164 of outer layer 106. In an exemplary embodiment, when first end 222 of gap covering element 202 is fixedly attached to distal section 164 of outer layer 106, it may mean that when first end 222 of gap covering element 202 is attached to distal section 164 of outer layer 106 in such a way that any relative movement between gap covering element 202 and distal section 164 of outer layer 106 is prevented. In an exemplary embodiment, a second end 224 of gap covering element 202 may be movably attached to proximal section 162 of outer layer 106. In an exemplary embodiment, when second end 224 of gap covering element 202 is movably attached to proximal section 162 of outer layer 106, it may mean that second end 224 of gap covering element 202 is attached to proximal section 162 of outer layer 106 in such a way that second end 224 of gap covering element 202 is able to move relative to proximal section 162 of outer layer 106. In an exemplary embodiment, gap covering element 202 may be configured to prevent air communication between cooling gap 210 and an outer space of outer layer 106 through expansion gap 166. In an exemplary embodiment, as shown in FIG. 2D, when first end 222 of gap covering element 202 is attached to distal section 164 of outer layer 106 and second end 224 of gap covering element 202 is attached to proximal section 162 of outer layer 106, gap covering element 202 may cover expansion gap 166 and, consequently, air communication between cooling gap 210 and an outer space of outer layer 106 through expansion gap 166 may be prevented.
As shown in FIG. 3B and FIG. 3C, in an exemplary embodiment, gap covering element 202 may include a first flat section 302, a second flat section 304, and a curved section 306. In an exemplary embodiment, first flat section 302 may be at first end 222 of gap covering element 202. In an exemplary embodiment, first flat section 302 may be fixedly attached to distal section 164 of outer layer 106. In an exemplary embodiment, when first flat section 302 is fixedly attached to distal section 164 of outer layer 106, it may mean that first flat section 302 is attached to distal section 164 of outer layer 106 in such a way that any relative movement between first flat section 302 and distal section 164 of outer layer 106 is prevented. In an exemplary embodiment, second flat section 304 may be at second end 224 of gap covering element 202. In an exemplary embodiment, second flat section 304 may be movably disposed onto proximal section 162 of outer layer 106. In an exemplary embodiment, when second flat section 304 is movably disposed onto proximal section 162 of outer layer 106, it may mean that second flat section 304 is disposed onto proximal section 162 of outer layer 106 in such a way that second flat section 304 keeps the contact with proximal section 162 of outer layer 106 but second flat section 304 is able to move relative to proximal section 162 of outer layer 106. In an exemplary embodiment, curved section 306 may be attached between first flat section 302 and second flat section 304. In an exemplary embodiment, when inner layer 104 is expanded due to an increase in the temperature of inner layer 104 and proximal section 162 of outer layer 106 and distal section 164 of outer layer are distanced from each other, second flat section 304 may move along proximal section 162 of outer layer 106. In an exemplary embodiment, movement of second flat section 304 along proximal section 162 of outer layer 106 may allow proximal section 162 of outer layer 106 and distal section 164 of outer layer to distance from each other while air communication between cooling gap 210 and the outer space of outer layer 106 through expansion gap 166 is still prevented.
As further show in FIG. 1A, FIG. 1B, FIG. 2A and FIG. 2B, in an exemplary embodiment, double-skin liner 100 may further include a sealing element 108. In an exemplary embodiment, sealing element 108 may be attached to outer surface 166 of outer layer 106. In an exemplary embodiment, gap covering element 202 may be disposed between outer layer 106 and sealing element 108. In an exemplary embodiment, sealing element 108 may be configured to seal between double-skin liner 100 and transition piece 102 when distal end 101 of double-skin liner 100 is inserted into transition piece 110.
As shown in FIG. 2D, double-skin liner 100 may further include a plurality of internal cooling holes 148. In an exemplary embodiment, plurality of internal cooling holes 148 may be provided on inner layer 104. In an exemplary embodiment, plurality of internal cooling holes 148 may be configured to provide air communication or air flow between an inner space of inner layer 104 and cooling gap 210. That is, the existence of plurality of internal cooling holes 148 may allow for air flow. In an exemplary embodiment, air may be able go from the inner space of inner layer 104 to cooling gap 210 or go from cooling gap 210 to the inner space of inner layer 104 through plurality of internal cooling holes 148 so air communication or air flow may be provided between the inner space of inner layer 104 and cooling gap 210.
As further shown in FIG. 2D, double-skin liner 100 may further include a plurality of external cooling holes 168. In an exemplary embodiment, plurality of external cooling holes 168 may be provided on outer layer 106. In an exemplary embodiment, plurality of external cooling holes 168 may be configured to provide air communication between cooling gap 210 and an outer space of outer layer 106. In an exemplary embodiment, air may be able go from the outer space of outer layer 106 to cooling gap 210 or go from cooling gap 210 to the outer space of outer layer 106 through plurality of external cooling holes 168 so air communication or air flow may be provided between the outer space of outer layer 106 and cooling gap 210.
In an exemplary embodiment, plurality of internal cooling holes 148, cooling gap 210, and plurality of external holes 168 may be configured to provide cooling mechanism for double-skin liner 100. In an exemplary embodiment, as discussed above, air may be able to flow between the inner space of inner layer 104 and cooling gap 210 and also may be able to communicate between cooling gap 210 and the outer space of outer layer 106. Hence, air may be able to communicate between the inner space of inner layer 104 and the outer space of outer layer 106. In an exemplary embodiment, the air communication between the inner space of inner layer 104 and the outer space of outer layer 106 may help decreasing the temperature of double-skin liner 100 due to convection heat transfer and, therefore, a cooling mechanism may be provided for double-skin liner 100.
FIG. 4 illustrates a partial schematic illustration of a turbine combustor 400 with a conventional combustor liner 402 and a transition piece 404, consistent with one or more exemplary embodiments of the present disclosure. In an exemplary embodiment, turbine combustor 400 includes combustor liner 402 and transition piece 404. In an exemplary embodiment, combustor liner 402 may have substantially hollow cylindrical shape. In an exemplary embodiment, transition piece 404 may be connected to combustor liner 402 in a radial direction. In an exemplary embodiment, transition piece 404 may be adapted to bring out combustion gas.
FIG. 5 illustrates a partial but more detailed schematic illustration of combustor liner 402 and transition piece 404 interface region, consistent with one or more exemplary embodiments of the present disclosure. In an exemplary embodiment, combustor liner 402 includes an inner layer 500. In an exemplary embodiment, inner layer 500 may have a hollow cylindrical shape. In an exemplary embodiment, inner layer 200 may be disposed about a central axis of combustor liner 502.
In an exemplary embodiment, combustor liner 402 further includes an outer layer 502. In an exemplary embodiment, outer layer 502 may have a hollow cylindrical shape. In an exemplary embodiment, outer layer 502 may be disposed about a central axis of combustor liner 402. In an exemplary embodiment, outer layer 502 may be disposed outside inner layer 500 in a radial direction that may surround inner layer 500.
FIG. 7 illustrates a simplified, partial section of combustor liner 402 with a plurality of inner layer holes 7010 and a plurality of outer layer holes 7012, consistent with one or more exemplary embodiments of the present disclosure. In an exemplary embodiment, inner layer 500 includes an upstream end 702 and a downstream end 704. In an exemplary embodiment, upstream end 702 of inner layer 500 may be upstream of downstream end 704 of inner layer 500 with respect to a combustion gas flow during operation.
In an exemplary embodiment, outer layer 502 includes a first section 706 and a second section 708. In an exemplary embodiment, first section 706 of outer layer 502 may be upstream of second section 708 of outer layer 502 with respect to an exemplary combustion gas flow during operation. In an exemplary embodiment, first section 706 of outer layer 502 includes an upstream end 7062 and a downstream end 7064. In an exemplary embodiment, upstream end 7062 of first section 706 of outer layer 502 may be upstream of downstream end 7064 of first section 706 of outer layer 502 with respect to an exemplary combustion gas flow during operation. In an exemplary embodiment, second section 708 of outer layer 502 includes an upstream end 7082 and a downstream end 7084. In an exemplary embodiment, upstream end 7082 of second section 708 of outer layer 502 may be upstream of downstream end 7084 of second section 708 of outer layer 502 with respect to an exemplary combustion gas flow during operation.
In an exemplary embodiment, upstream end 7062 of first section 706 of outer layer 502 may be attached to upstream end 702 of inner layer 500. As used herein, upstream end 7062 of first section 706 of outer layer 502 may be welded to upstream end 702 of inner layer 500. In an exemplary embodiment, downstream end 7084 of second section 708 of outer layer 502 may be attached to downstream end 704 of inner layer 500. As used herein, downstream end 7084 of second section 708 of outer layer 502 may be welded to downstream end 704 of inner layer 500.
In an exemplary embodiment, outer layer 502 may be disposed outside inner layer 500 in a radial direction that may surround inner layer 500 and an air channel 704 may be configured between outer layer 502 and inner layer 500. In other words, outer layer 502 may be positioned circumferentially around inner layer 500 with air channel 704 between outer layer 502 and inner layer 500.
In an exemplary embodiment, a first inner layer diameter at upstream end 702 of inner layer 500 may be more/less than a second inner layer diameter at downstream end 704 of inner layer 200. In an exemplary embodiment, a first outer layer diameter at upstream end 7062 of first section 706 of outer layer 502 may be more/less than a second outer layer diameter at downstream end 7084 of second section 708 of outer layer 502. As used herein, a first combustor liner diameter at an upstream end of combustor liner 402 may be less than a second combustor liner diameter at a downstream end of combustor liner 402.
In an exemplary embodiment, inner layer 500 further includes plurality of inner layer holes 7010. In an exemplary embodiment, air channel 704 may be connected in air communication with an inside of inner layer 500 via plurality of inner layer holes 7010. In an exemplary embodiment, outer layer 502 further includes plurality of outer layer holes 7012. In an exemplary embodiment, an outside of outer layer 502 may be connected in air communication with air channel 604 via plurality of outer layer holes 7012.
In an exemplary embodiment, a portion of compressed air may be used to cool combustor liner 402. In an exemplary embodiment, outer layer 502 may be in contact with an exemplary compressed air and inner layer 500 may be in contact with an exemplary combustion gas. In other words, an exemplary compressed air may flow from an exemplary outside of outer layer 502 into air channel 604 to cool inner layer 500. In an exemplary embodiment, an exemplary compressed air may flow from air channel 604 to an exemplary inside of inner layer 500 to get out with an exemplary combustion gas.
FIG. 6 illustrates a simplified, partial section of a portion of combustor liner 402 with a gap 600 and a gap sealing element 602 configured between combustor liner 402 and a hula seal 504, consistent with one or more exemplary embodiments of the present disclosure. In an exemplary embodiment, downstream end 7064 of first section 706 of outer layer 502 may be mounted adjacent upstream end 7082 of second section 708 of outer layer 502. In other words, gap 600 may be configured between downstream end 7064 of first section 706 of outer layer 502 and upstream end 7082 of second section 708 of outer layer 502. In an exemplary embodiment, 360-degree round gap 600 may be configured at least equivalent to distance that first section 706 of outer layer 502 and second section 708 of outer layer 502 may be configured to expand due to an exemplary combustion gas.
In an exemplary embodiment, combustor liner 402 further includes gap sealing element 602. In an exemplary embodiment, gap sealing element 602 may have a hollow cylindrical shape. As used herein, metal gap sealing element 602 may have a hollow convex cylindrical shape. In an exemplary embodiment, gap sealing element 602 may be disposed outside gap 600 in a radial direction that may surround gap 600. In an exemplary embodiment, gap sealing element 602 may be configured to seal gap 600 and to disconnect air communication between gap 600 and an exemplary outside of outer layer 502. In an exemplary embodiment, gap sealing element 602 may be further configured as an interface between first section 706 of outer layer 502 and second section 708 of outer layer 502.
In an exemplary embodiment, gap sealing element 602 includes an upstream end 6022 and a downstream end 6024. In an exemplary embodiment, upstream end 6022 of gap sealing element 602 may be upstream of downstream end 6024 of gap sealing element 602 with respect to an exemplary combustion gas flow during operation. In an exemplary embodiment, upstream end 6022 of gap sealing element 602 may be configured in contact with first section 706 of outer layer 502 and downstream end 6024 of gap sealing element 602 may be configured in contact with second section 708 of outer layer 502.
In an exemplary embodiment, upstream end 6022 of gap sealing element 602 may be attached to first section 706 of outer layer 502 and downstream end 6024 of gap sealing element 602 may be configured in contact with second section 708 of outer layer 502. As used herein, upstream end 6022 of gap sealing element 602 may be welded to first section 706 of outer layer 502 and downstream end 6024 of gap sealing element 602 may be configured to be slidable on second section 708 of outer layer 502 without losing outer layer 502 solidarity.
In another exemplary embodiment, downstream end 6024 of gap sealing element 602 may be attached to second section 708 of outer layer 502 and upstream end 6022 of gap sealing element 602 may be configured in contact with first section 706 of outer layer 502. As used herein, downstream end 6024 of gap sealing element 602 may be welded to second section 708 of outer layer 502 and upstream end 6022 of gap sealing element 602 may be configured to be slidable on first section 706 of outer layer 502 without losing outer layer 502 solidarity.
In an exemplary embodiment, hula seal 504 may be configured as an interface between combustor liner 402 and transition piece 404. In other words, transition piece 404 may be connected to combustor liner 402 in a radial direction via hula seal 504. As used herein, transition piece 404 may be connected to second section 708 of outer layer 502 in a radial direction via hula seal 504. In an exemplary embodiment, gap sealing element 602 may be configured between combustor liner 402 and hula seal 504. As used herein, gap sealing element 602 may be configured between and in contact with hula seal 504 and outer layer 502.
In an exemplary embodiment, by using the disclosed double skin liner proposed in this disclosure and replacing it with liners used in gas turbines, the problems caused by the thermal expansion of the liners in gas turbines can be solved or minimized. In an exemplary embodiment, risks may be caused by increased stress on the parts significantly reduced cooling air leakage, as well as possible vibrations, may be decreased as well. In an exemplary embodiment, the use of the disclosed double skin liner proposed in this disclosure may be provided a very good possibility for sealing different parts and proper management of cooling air.
While the foregoing has described what may be considered to be the best mode and/or other examples, it is understood that various modifications may be made therein and that the subject matter disclosed herein may be implemented in various forms and examples, and that the teachings may be applied in numerous applications, only some of which have been described herein. It is intended by the following claims to claim any and all applications, modifications and variations that fall within the true scope of the present teachings.
Unless otherwise stated, all measurements, values, ratings, positions, magnitudes, sizes, and other specifications that are set forth in this specification, including in the claims that follow, are approximate, not exact. They are intended to have a reasonable range that is consistent with the functions to which they relate and with what is customary in the art to which they pertain.
The scope of protection is limited solely by the claims that now follow. That scope is intended and should be interpreted to be as broad as is consistent with the ordinary meaning of the language that is used in the claims when interpreted in light of this specification and the prosecution history that follows and to encompass all structural and functional equivalents. Notwithstanding, none of the claims are intended to embrace subject matter that fails to satisfy the requirement of Sections 101, 102, or 103 of the Patent Act, nor should they be interpreted in such a way. Any unintended embracement of such subject matter is hereby disclaimed.
Except as stated immediately above, nothing that has been stated or illustrated is intended or should be interpreted to cause a dedication of any component, step, feature, object, benefit, advantage, or equivalent to the public, regardless of whether it is or is not recited in the claims.
It will be understood that the terms and expressions used herein have the ordinary meaning as is accorded to such terms and expressions with respect to their corresponding respective spaces of inquiry and study except where specific meanings have otherwise been set forth herein. Relational terms such as first and second and the like may be used solely to distinguish one entity or action from another without necessarily requiring or implying any actual such relationship or order between such entities or actions. The terms “comprises,” “comprising,” or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. An element proceeded by “a” or “an” does not, without further constraints, preclude the existence of additional identical elements in the process, method, article, or apparatus that comprises the element.
The Abstract of the Disclosure is provided to allow the reader to quickly ascertain the nature of the technical disclosure. It is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims. In addition, in the foregoing Detailed Description, it can be seen that various features are grouped together in various implementations. This is for purposes of streamlining the disclosure, and is not to be interpreted as reflecting an intention that the claimed implementations require more features than are expressly recited in each claim. Rather, as the following claims reflect, inventive subject matter lies in less than all features of a single disclosed implementation. Thus, the following claims are hereby incorporated into the Detailed Description, with each claim standing on its own as a separately claimed subject matter.
While various implementations have been described, the description is intended to be exemplary, rather than limiting and it will be apparent to those of ordinary skill in the art that many more implementations and implementations are possible that are within the scope of the implementations. Although many possible combinations of features are shown in the accompanying figures and discussed in this detailed description, many other combinations of the disclosed features are possible. Any feature of any implementation may be used in combination with or substituted for any other feature or element in any other implementation unless specifically restricted. Therefore, it will be understood that any of the features shown and/or discussed in the present disclosure may be implemented together in any suitable combination. Accordingly, the implementations are not to be restricted except in light of the attached claims and their equivalents. Also, various modifications and changes may be made within the scope of the attached claims.

Claims

What is claimed is:

1- A double-skin liner for a combustion chamber of a gas turbine, the double-skin liner comprising:

an inner layer, the inner layer being cylindrical;

an outer layer, the outer layer being cylindrical, a first end of the inner layer fixedly attached to a first end of the outer layer, a second end of the inner layer fixedly attached to a second end of the outer layer, the inner layer and the outer layer forming a cooling gap between the inner layer and the outer layer, the outer layer comprising:

a proximal section;

a distal section; and

an expansion gap provided on the outer layer between the proximal section and the distal section, the expansion gap comprising a 360-degree cylindrical gap;

a gap covering element, the gap covering element being cylindrical, the gap covering element attached to an outer surface of the outer layer, a first end of the gap covering element fixedly attached to the distal section of the outer layer, a second end of the gap covering element movably attached to the proximal section of the outer layer, the gap covering element configured to prevent air flow between the cooling gap and an outer space of the outer layer through the expansion gap, the gap covering element comprising:

a first flat section at the first end of the gap covering element, the first flat section fixedly attached to the distal section of the outer layer;

a second flat section at the second end of the gap covering element, the second section movably disposed onto the proximal section of the outer layer; and

a curved section attached between the first flat section and the second flat section;

a sealing element, the sealing element attached to the outer surface of the outer layer, the gap covering element disposed between the outer layer and the sealing element, the sealing element configured to form a seal between the double-skin liner and a transition piece when a distal end of the double-skin liner is inserted into the transition piece;

a plurality of internal cooling holes provided on the inner layer, the plurality of internal cooling holes configured to provide air communication between an inner space of the inner layer and the cooling gap; and

a plurality of external cooling holes provided on the outer layer, the plurality of external cooling holes configured to provide air communication between the cooling gap and an outer space of the outer layer,

wherein:

the proximal section of the outer layer and the distal section of the outer layer are configured to extend a distance from each other by lengthening the expansion gap responsive to expansion of the inner layer;

the plurality of internal cooling holes, the cooling gap, and the plurality of external cooling holes are configured to provide cooling mechanism for the double-skin liner by (how); and

the second flat section is configured to move along the proximal section of the outer layer responsive to the proximal section of the outer layer and the distal section of the outer layer distancing from each other.

2- A double-skin liner for a combustion chamber of a gas turbine, the double-skin liner comprising:

an inner layer; and

an outer layer, a first end of the inner layer fixedly attached to a first end of the outer layer, a second end of the inner layer fixedly attached to a second end of the outer layer, the inner layer and the outer layer forming a cooling gap between the inner layer and the outer layer, the outer layer comprising:

a proximal section;

a distal section; and

an expansion gap provided on the outer layer between the proximal section and the distal section,

wherein the proximal section of the outer layer and the distal section of the outer layer are configured to distance from each other through lengthening the expansion gap responsive to expansion of the inner layer.

3- The double-skin liner of claim 2, further comprising a gap covering element, the gap covering element attached to an outer surface of the outer layer, a first end of the gap covering element fixedly attached to the distal section of the outer layer, a second end of the gap covering element movably attached to the proximal section of the outer layer, the gap covering element configured to prevent air communication between the cooling gap and an outer space of the outer layer through the expansion gap.

4- The double-skin liner of claim 3, further comprising a sealing element, the sealing element attached to the outer surface of the outer layer, the gap covering element disposed between the outer layer and the sealing element, the sealing element configured to form a seal between the double-skin liner and a transition piece when a distal end of the double-skin liner is inserted into the transition piece.

5- The double-skin liner of claim 4, further comprising:

a plurality of external cooling holes provided on the outer layer, the plurality of external cooling holes configured to provide air communication between the cooling gap and the outer space of the outer layer,

wherein the plurality of internal cooling holes, the cooling gap, and the plurality of external cooling holes are configured to provide cooling mechanism for the double-skin liner.

6- The double-skin liner of claim 5, wherein the gap covering element comprises:

a curved section attached between the first flat section and the second flat section,

wherein the second flat section is configured to move along the proximal section of the outer layer responsive to the proximal section of the outer layer and the distal section of the outer layer distancing from each other.

7- A turbine combustor comprising a combustor liner, the combustor liner having a hollow cylindrical shape, the combustor liner comprising:

an inner layer comprising a hollow cylindrical shape disposed about a central axis of the combustor liner, the inner layer comprising an upstream end and a downstream end with respect to combustion gas flow during operation;

an outer layer with a hollow cylindrical shape, the outer layer disposed outside the inner layer in a radial direction surrounding the inner layer, the outer layer comprising a first section and a second section wherein the first section is upstream of the second section with respect to the combustion gas flow during operation, the first section of the outer layer comprising an upstream end and a downstream end with respect to the combustion gas flow during operation, the second section of the outer layer comprising an upstream end and a downstream end with respect to the combustion gas flow during operation, the upstream end of the first section of the outer layer attached to the upstream end of the inner layer, the downstream end of the second section of the outer layer attached to the downstream end of the inner layer;

wherein the downstream end of the first section of the outer layer is mounted adjacent the upstream end of the second section of the outer layer with a gap between the downstream end of the first section of the outer layer and the upstream end of the second section of the outer layer, the gap configured at least equivalent to distance that the first section of the outer layer and the second section of the outer layer are configured to expand due to the combustion gas; and

a gap sealing element with a hollow cylindrical shape disposed outside the gap in a radial direction surrounding the gap, the gap sealing element comprising an upstream end and a downstream end with respect to the combustion gas flow during operation, the upstream end of the gap sealing element configured in contact with the first section of the outer layer, the downstream end of the gap sealing element configured in contact with the second section of the outer layer, the gap sealing element configured to seal the gap and to disconnect air communication between the gap and an outside of the outer layer.

8- The turbine combustor of claim 7, further comprising:

a transition piece connected to the second section of the outer layer in a radial direction via a hula seal, the transition piece configured to bring out the combustion gas.

9- The turbine combustor of claim 7, wherein the upstream end of the first section of the outer layer is welded to the upstream end of the inner layer.

10- The turbine combustor of claim 7, wherein the downstream end of the second section of the outer layer is welded to the downstream end of the inner layer.

11- The turbine combustor of claim 7, wherein the upstream end of the gap sealing element is attached to the first section of the outer layer, the downstream end of the gap sealing element configured in contact with the second section of the outer layer, the downstream end of the gap sealing element further configured to be slidable on the second section of the outer layer.

12- The turbine combustor of claim 11, wherein the upstream end of the gap sealing element is welded to the first section of the outer layer.

13- The turbine combustor of claim 7, wherein the downstream end of the gap sealing element is attached to the second section of the outer layer, the upstream end of the gap sealing element is configured to be in contact with the first section of the outer layer, the upstream end of the gap sealing element further configured to be slidable on the first section of the outer layer.

14- The turbine combustor of claim 13, wherein the downstream end of the gap sealing element is welded to the second section of the outer layer.