METHOD AND SYSTEM FOR PROVIDING SEALING IN GAS TURBINES

Abstract

A gas turbine system is provided that includes a compressor section, a combustor assembly coupled to the compressor section, and a turbine section coupled to the compressor section. At least one of the combustor assembly and the turbine section includes a sealing sub-system for use in sealing between a first component and a second component. A first component defines a first seal member receiving region oriented between a higher-temperature gas region and a cooler-temperature gas region. A second component adjacent the first component defines a second seal member receiving region oriented adjacent the first seal member receiving region. The sealing system includes first and second end walls defined in at least one of the first and second seal member receiving regions. A seal member is oriented within the first and second seal member receiving regions, and includes at least a first layer defining at least a first resilient seal end portion that engages one of the first and second end walls.

Description

FEDERAL RESEARCH STATEMENT

The subject matter of this disclosure was made with Government support under Contract No. DE-FC26-05NT42643, awarded by the Department of Energy (DOE), and the Government has certain rights in the subject matter claimed herein.

BACKGROUND

The present disclosure relates generally to rotary machines, and, more specifically, to methods and systems for providing sealing between components within a gas turbine engine.

At least some known gas turbine engines include a plurality of seal assemblies that facilitate isolating a flow of combustion gases channeled along a fluid flow path (“hot gas path”) from cooler regions of the gas turbine located between an inner shell of the gas turbine engine and components directly exposed to the lower-pressure combustion gas flow, for example. At least some known seal assemblies extend between adjacent stationary components, such as stator segments, within a stage of the gas turbine engine to provide sealing between a high-pressure, lower-temperature area and a low-pressure, higher-temperature area. To further protect against ingestion of higher-temperature combustion gases into the cooler regions of the engine, in at least some known gas turbine engines, purge air is channeled into the cooler regions, at a pressure that is higher than a pressure of the combustion gas flow.

At least some known seal assemblies include an elongated substantially planar seal member that is inserted within adjacent elongated rectangular slots or seal member receiving regions defined within two adjacent components. Such seal members are sometimes referred to as “spline seals” and include side edge regions and end edge regions. In at least some known seal assemblies, the adjacent rectangular slots are longer in length than the seal member inserted within the slots, to accommodate manufacturing tolerances and minor part-to-part misalignments. In at least some known gas turbine engines that include such seal members, leakage of purge gases may occur around the end edge regions of the seal members, specifically between the end edge regions and the adjacent end regions of the elongated rectangular slots. As a result of the leakage, a larger volume of purge air may be needed to ensure that ingestion of combustion gases into the cooler regions is prevented, than would be needed if the leakage did not occur.

BRIEF DESCRIPTION

In one aspect, a method for providing a seal between components within a gas turbine is provided. The method includes inserting a seal member into a first seal member receiving region defined within a first component of a gas turbine, wherein the first seal member receiving region is oriented between a higher-temperature gas region and a cooler-temperature gas region. The method also includes inserting the seal member into a second recess defined within a second component of the gas turbine, wherein the second component is adjacent to the first component, and wherein at least one of the first and second seal member regions includes a first end wall and at least one of the first and second seal member regions includes a second end wall oriented substantially opposite the first end wall. The seal member includes at least a first layer defining at least a first seal end portion that engages one of the respective first and second end walls.

In still another aspect, a gas turbine system is provided. The gas turbine system includes a compressor section, a combustor assembly coupled to the compressor section, and a turbine section coupled to the compressor section. At least one of the combustor assembly and the turbine section includes a sealing sub-system for use in sealing between a first component and a second component. The sealing sub-system includes a first component defining a first seal member receiving region oriented between a higher-temperature gas region and a cooler-temperature gas region. The sealing sub-system also includes a second component adjacent the first component. The second component defines a second seal member receiving region oriented adjacent the first seal member receiving region, wherein at least one of the first and second seal member receiving regions includes a first end wall. At least one of the first and second seal member receiving regions also includes a second end wall oriented substantially opposite the first end wall. The sealing sub-system also includes a seal member oriented within the first and second seal member receiving regions, wherein the seal member includes at least a first layer defining at least a first resilient seal end portion that engages one of the first and second end walls.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic illustration of an exemplary gas turbine engine.

FIG. 2 is a perspective view of an exemplary sealing system that may be used in the gas turbine engine shown in FIG. 1.

FIG. 3 is a side sectional view of the sealing system shown in FIG. 2.

FIG. 4 is an end sectional view of the sealing system shown in FIG. 3.

FIG. 5 is a side sectional view of an alternative sealing system that may be used in the gas turbine engine shown in FIG. 1.

FIG. 6 is a side sectional view of another alternative sealing system that may be used in the gas turbine engine shown in FIG. 1.

FIG. 7 is a side sectional view of yet another alternative sealing system that may be used in the gas turbine engine shown in FIG. 1.

FIG. 8 is a perspective view of yet another alternative sealing system that may be used in the gas turbine engine shown in FIG. 1.

DETAILED DESCRIPTION

As used herein, the terms “axial” and “axially” refer to directions and orientations extending substantially parallel to a longitudinal axis of a gas turbine engine. Moreover, the terms “radial” and “radially” refer to directions and orientations extending substantially perpendicular to the longitudinal axis of the gas turbine engine. In addition, as used herein, the terms “circumferential” and “circumferentially” refer to directions and orientations extending arcuately about the longitudinal axis of the gas turbine engine. It should also be appreciated that the term “fluid” as used herein includes any medium or material that flows, including, but not limited to, gas and air.

FIG. 1 is a schematic illustration of an exemplary gas turbine gas turbine engine 100. Gas turbine engine 100 includes a compressor assembly 102 and a combustor assembly 104. Gas turbine engine 100 also includes a turbine assembly 108 and a common compressor/turbine shaft 110 (sometimes referred to as a rotor 110), configured for rotation about an axis 106.

In operation, air flows through compressor assembly 102 such that compressed air is supplied to combustor assembly 104. Fuel is channeled to a combustion region and/or zone (not shown) that is defined within combustor assembly 104 wherein the fuel is mixed with the air and ignited. Combustion gases generated in combustor assembly 104 are channeled along a hot gas path 111 through turbine assembly 108 wherein gas stream thermal energy is converted to mechanical rotational energy.

FIG. 2 is an enlarged perspective view of an exemplary sealing system 200 that may be used in gas turbine gas turbine engine 100 (shown in FIG. 1). FIG. 3 is a side sectional elevational view of sealing system 200, and FIG. 4 is an end sectional view of sealing system 200. Sealing system 200 is used to provide sealing between a first static component 202 and an adjacent second static component 203. Seal member 204 extends along substantially the same direction as hot gas path 111.

In the exemplary embodiment, a seal region 206 is defined between an elongated slot or seal member receiving region 208 defined within component 202, and a corresponding slot or seal member receiving region 230 defined within component 203. A seal member 204 is captured (i.e., at least partially inserted) within slots 208 and 230.

In the exemplary embodiment, sealing system 200 includes a plurality of seal members, for example, seal members 209 and 213, in addition to seal member 204, wherein seal members 209 and 213 are received in slots or seal member receiving regions 207 and 211, respectively. The arrangement of slots 207, 208, and 211 is exemplary only. In an alternative embodiment, slots 207, 208 and 211 may be oriented in any configuration that enables sealing system 200 to function as described herein. Moreover, each seal member 204, 209 and/or 213 may have any configuration, including configurations that are different from each other, which enables sealing system 200 to function as described herein.

In the exemplary embodiment, seal member 204 is a multi-layer seal member that includes layers 210, 212, 214, 216, and 218. In one embodiment, at least one of layers 210-218 is a solid metal layer. Moreover, in one embodiment, at least one of layers 210-218 is a metal cloth layer. Alternatively, any of layers 210-218 may be fabricated from any material that enables system 200 to function as described herein. In the exemplary embodiment, layers 210-218 may be coupled to each other using any suitable fastening method that enables system 200 to function as described herein. While seal member 204 is described as having a multi-layer laminated construction, in alternative embodiments, seal member may have any number of layers that enables system 200 to function as described herein.

In the exemplary embodiment, seal member 204 includes a layer 220 with seal end portions 222 and 224. In the exemplary embodiment, layer 220 is fabricated from any suitable material that enables system 200 to function as described herein. Specifically, layer 220 is fabricated from a sufficiently strong and flexible material that enables seal end portions 222 and 224 to resiliently bend to maintain contact with end walls 226 and 228 of slot 208, and corresponding end walls (not shown) within slot 230 (shown in FIG. 4).

In the exemplary embodiment, seal member 204 includes both seal end portion 224 and seal end portion 222 (shown in broken lines). In an alternative embodiment, seal member 204 may have only one of seal end portions 224 and 222. For example, in an alternative embodiment, seal end portion 222 may be omitted. In addition, in the exemplary embodiment, seal end portions 222 and 224 both extend from the same layer, for example, layer 220. In an alternative embodiment (not shown), seal end portions 222 and 224 may extend from different ones of layers 210, 212, 214, 216, 218, and 220.

In the exemplary embodiment, seal end portion 224 is sized and oriented at an angle α with respect to a substantially planar web portion 223 of layer 220. Seal end portion 222 is sized and oriented at an angle β, with respect to portion 223. In the exemplary embodiment, α and β have the same value. In an alternative embodiment, each of α and β may have any value that enables sealing system 200 to function as described herein. After insertion of seal member 204 into slot 208, end edges 225 and 227 of seal end portions 222 and 224 are maintained in contact with end walls 226 and 228, respectively. In the exemplary embodiment, seal end portions 222 and 224 extend integrally from substantially planar web portion 223. In an alternative embodiment, seal end portions 222 and 224 are initially fabricated as discrete components that are subsequently coupled to substantially planar web portion 223 using any suitable attachment method that enables system 200 to function as described herein.

In one embodiment, to facilitate assembly of system 200, seal member 204 is initially fabricated with seal end portions 222 and 224 temporarily deflected to positions 232 and 234 (illustrated in broken lines in FIG. 3) and temporarily secured in position, for example via a temperature-sensitive adhesive 236, such that seal member 204 has an initial overall length L that is shorter than a length M of slot 208, to facilitate insertion of seal member 204 into slot 208. During turbine engine operation, adhesive 236 is exposed to elevated temperatures that cause adhesive 236 to melt, enabling deployment of seal end portions 222 and 224 to their extended positions, as illustrated in FIG. 3.

As illustrated in FIG. 4, seal member 204 provides a seal that extends between adjacent components 202 and 203. More specifically, seal member 204 spans a gap 205 defined between components 202 and 203. In the exemplary embodiment, a pressure in a cooler-temperature gas region 240 is higher than a pressure in a hot gas path region 242 that is exposed to combustion gases. Accordingly, because of the pressure differential between regions 240 and 242, during operation of gas turbine engine 100 (shown in FIG. 1), seal member 204 is pressed against bottom walls 244 and 246 of slots 208 and 230, respectively. By configuring seal end portions 222 and 224 to be resiliently flexible to maintain contact with end walls 226 and 228, sealing system 200 facilitates reducing or preventing leakage around ends of seal member 204.

Seal member 204 is described and shown in FIGS. 2-4 as being received in a pair of adjacent slots 208 and 230 within adjacent turbine components 202 and 203, wherein each of slots 208 and 230 receives and encircles a side of seal member 204. At least some known gas turbine engines 100 (shown in FIG. 1), also include sealing systems that do not incorporate fully defined recesses such as slots 208 and 230. For example, FIG. 8 illustrates an alternative sealing system 280 that may be used in gas turbine engine 100, with seal member 204 (shown in FIGS. 2-4). In the exemplary embodiment, sealing system 280 includes a plurality of shroud blocks 250 (of which two are shown in FIG. 8) that are arranged circumferentially within a gas turbine engine 100, with a seal member 204 oriented between each adjacent pair of shroud blocks 250.

In the exemplary embodiment, shroud block 250 includes a flange 254 and an overlying flange 266. Flanges 254 and 266 are separated by a distance H. At least a portion 262 of flange 254 is not covered by flange 266. Shroud block 250 also includes a flange 256 bounded by at least an end wall 258, and at least partially covered by a flange 268. In the exemplary embodiment, a similar end wall (not shown) is provided at an opposite end of flange 256. As previously described, seal members 204 (shown in FIGS. 2-4) are oriented between each pair of adjacent shroud blocks 250. For example, a seal member 204 (not shown in FIG. 8) may be oriented between adjacent shroud blocks 250, such that it is supported by flanges 256 and 256, and bounded at its ends by end wall 258 and a corresponding opposed end wall (not shown). In addition, the seal member 204 is also maintained in position by flanges 268 and 266. Accordingly, flanges 254 and 266 define a first seal member receiving region 270, and flanges 256, 268, end wall 258 and an opposite end wall (not shown) define a second seal member receiving region 272. In the exemplary embodiment, seal member receiving region 272 includes end wall 258 and an opposite end wall, while seal member region 270 does not include end walls. In an alternative embodiment, each seal member region 270 and 272 may include any number of end walls that enables sealing system 280 to function as described herein. For example, in an alternative embodiment, seal member region 272 may include end wall 258, while seal member region 270 may include an end wall (not shown) oriented at an end of flange 254 that is adjacent an end of flange 256 that is opposite to end wall 258.

Seal end portions 222 and 224 are shown in FIGS. 2-4 as substantially planar, upwardly-angled elements. In alternative embodiments, other seal end portion configurations are provided. For example, FIG. 5 is a side sectional view of an alternative exemplary sealing system 300 wherein a seal member 306 is received within a slot 304 in a static component 302. Seal member 306 is also inserted into a corresponding slot defined on an adjacent static component (not shown). In the exemplary embodiment, seal member 306 is multi-layered, and includes a central seal layer 308. Upper layers 310 and 312 are coupled to central seal layer 308, as are lower layers 314 and 316. In the exemplary embodiment, any of layers 308-316 may be fabricated from any suitable material that enables sealing system 300 to function as described herein. Moreover, layers 308-316 may be coupled to each other using any suitable fastening method that enables system 300 to function as described herein. While seal member 306 is described as having a multi-layer laminated construction, in alternative embodiments, seal member 306 may include any number of layers that enables system 300 to function as described herein.

Seal member 306 includes seal end portions 318 and 322 that extend from a substantially planar web portion 328 of layer 308. In the exemplary embodiment, each of seal end portions 318 and 322 has a “W”-shaped configuration. Moreover, seal end portions 318 and 322 are sized and configured to be resiliently flexible, such that after insertion of seal member 306 into slot 304, seal end portion 318 is maintained in contact with an end wall 320 of slot 304, and seal end portion 322 is maintained in contact with an end wall 324 of slot 304. Furthermore, after insertion of seal member 306 into slot 304, one or both of seal end portions 318 and 322 is slightly compressed to provide a seal between seal end portions 318 and 322 and respective end walls 320 and 324. Accordingly, sealing system 300 facilitates reducing or preventing leakage around ends of seal member 306.

As described with respect to the embodiment of FIGS. 2-4, in one embodiment, prior to assembly of system 300, seal end portions 318 and/or 322 may be compressed or otherwise deflected, and temporarily fastened in deflected positions, for example using a temperature-sensitive adhesive (not shown). Compression of seal end portions 318 and/or 322 facilitates insertion of seal member 306 into slot 304, and into a corresponding slot (not shown) in an adjacent component (not shown). After assembly, seal member 306 is exposed to engine operation temperatures that cause the adhesive to melt, facilitating subsequent deployment of seal end portions 318 and/or 322.

In the exemplary embodiment, a gas pressure of a purge gas in a region 330 is higher than a gas pressure in a region 332. Accordingly, because of the pressure differential between regions 330 and 332 present during turbine operation, seal member 306 is pressed against bottom wall 334 of slot 304 and against a bottom wall of a corresponding slot in an adjacent component (not shown). Seal end portions 318 and 322 facilitate the prevention of leakage of purge gas around seal member 306.

FIG. 6 is a side sectional view of another alternative exemplary sealing system 400. A seal member 406 is inserted within a slot 404 in a static component 402, and within a corresponding slot in an adjacent component (not shown). In the exemplary embodiment, seal member 406 is multi-layered and includes seal layer 408 and layers 410, 412, and 414. Moreover, any of layers 408-414 may be fabricated from any suitable material that enables system 400 to function as described herein. Seal layer 408 includes a substantially planar web portion 409 from which seal end portions 416 and 420 extend. Moreover, layers 408-416 may be coupled to each other using any suitable fastening method that enables system 400 to function as described herein. While seal member 406 is described as having a multi-layer laminated construction, in alternative embodiments, seal member 406 may include any number of layers that enables system 400 to function as described herein.

In the exemplary embodiment, seal end portions 416 and 420 are arcuate in cross-section, and are configured to be resiliently flexible, such that after insertion of seal member 406, seal end portion 416 is maintained in contact with an end wall 418 of slot 404, and seal end portion 420 is maintained in contact with an end wall 422 of slot 404. Furthermore, after insertion of seal member 406 into slot 404, one or both of seal end portions 416 and 420 is slightly compressed to provide a seal between seal end portions 416 and 420 and respective end walls 418 and 422.

As described with respect to the embodiment of FIGS. 2-4, in one embodiment, prior to assembly of system 400, one or both of seal end portions 416 and 420 may be compressed or otherwise deflected and temporarily fastened in deflected positions, for example using a temperature-sensitive adhesive (not shown). Compression of seal end portions 416 and 420 facilitates insertion of seal member 406 into slot 404 and into a corresponding slot in an adjacent component (not shown). After assembly, seal member 406 is exposed to engine operation temperatures that cause the adhesive to melt, facilitating subsequent deployment of seal end portions 416 and 420.

In the exemplary embodiment, a purge gas pressure in a region 430 is higher than a gas pressure in a region 432. Accordingly, because of the pressure differential between regions 430 and 432 during turbine operation, seal member 406 is maintained against bottom wall 434 of slot 404 and against a bottom wall of a corresponding slot in an adjacent component (not shown). Seal end portions 416 and 420 facilitate the prevention of purge gas leakage around seal member 406.

FIG. 7 is a side sectional view of another alternative exemplary sealing system 500. Seal member 506 is received within a slot 504 in a static component 502. Seal member 506 is also received within a corresponding slot in an adjacent static component (not shown). In the exemplary embodiment, seal member 506 is multi-layered, and includes seal layers 508 and 510, oriented between layers 512 and 514, and layers 516 and 518. Furthermore, layers 508-518 may be coupled together using any suitable fastening method that enables system 500 to function as described herein. Moreover, in the exemplary embodiment, any of layers 508-518 may be fabricated from any suitable material that enables system 500 to function as described herein. While seal member 506 is described as having a multi-layer laminated construction, in alternative embodiments, seal member 506 may include any number of layers that enables system 500 to function as described herein.

Seal end portions 520 and 526 extend from of layer 508. Seal end portions 522 and 528 extend from a substantially planar web portion 521 of layer 510. In the exemplary embodiment, seal end portions 520, 522, 526, and 528 are arcuate in cross-section, and are sized and configured to be resiliently flexible, such that after insertion of seal member 506 into slot 504, at least one of seal end portions 520, 522, 526, and 528 is slightly compressed to provide a seal between seal end portions 520 and/or 522 and end wall 524, and between seal end portions 526 and/or 528 and end wall 536, respectively.

As described with respect to the embodiment of FIGS. 2-4, in one embodiment, prior to assembly of system 500, at least one of seal end portions 520, 522, 526, and/or 528 is compressed or otherwise deflected and temporarily fastened in a deflected position, for example using a temperature-sensitive adhesive (not shown). Compression of seal end portions 520, 522, 526, and/or 528 facilitates insertion of seal member 506 into slot 504. After assembly, seal member 506 is exposed to engine operation temperatures that cause the adhesive to melt, facilitating subsequent deployment of seal end portions 520, 522, 526, and/or 528.

In the exemplary embodiment, a purge gas pressure in a region 530 is higher than a gas pressure in a region 532. Accordingly, because of the pressure differential between regions 530 and 532, during turbine operation seal member 506 is maintained against bottom wall 534 of slot 504 and against a bottom wall of a corresponding slot in an adjacent component (not shown). Seal end portions 520, 522, 526, and/or 528 facilitate the prevention of purge gas leakage around seal member 506.

In the embodiments of FIGS. 2, 5-7, seal members 204, 306, 406, and 506 are each illustrated with seal end portions 222 and 224 (shown in FIG. 2), 318 and 322 (shown in FIG. 5), 416 and 420 (shown in FIG. 6), and 520, 522, 526, and 528 (shown in FIG. 7), wherein the seal end portions in each embodiment have the same cross-sectional configuration. In an alternative embodiment, the seal member end portions may have any configuration, including different configurations at opposite ends of a single seal member, that enables the sealing systems to function as described herein. For example, in an alternative embodiment (not shown), a seal member may include a curved seal end portion at one end and a “W”-shaped seal end portion at an opposite end.

The subject matter described herein provides several advantages over known methods of sealing between static components in a gas turbine engine. For example, the sealing systems described herein facilitate maintaining a pressure boundary within a gas turbine engine between a higher-temperature combustion gas path and a cooler-temperature gas region, such as between an inner shell of a turbine and turbine components directly exposed to combustion gases. The sealing systems described herein also facilitate reducing or preventing of leakage around end regions of an elongated substantially planar (“spline”) seal member. The system systems described herein also facilitate assembly of turbine components by facilitating the temporary securement of seal end portions in deflected orientations, to facilitate insertion of the seal members into slots defined in adjacent turbine components. Moreover, the sealing systems described herein facilitates preventing excess outflow of high pressure purge through gaps defined between adjacent components within a gas turbine engine and into the hot gas path, towards facilitating an increase in turbine efficiency.

Exemplary embodiments of a method and a system for providing sealing between static components of a gas turbine engine are described above in detail. The method and system are not limited to the specific embodiments described herein, but rather, components of systems and/or steps of the methods may be utilized independently and separately from other components and/or steps described herein. For example, the method may also be used in combination with other rotary machine systems and methods, and are not limited to practice only with gas turbine engines as described herein. Rather, the exemplary embodiment can be implemented and utilized in connection with many other rotary machine applications.

Although specific features of various embodiments of the claimed subject matter may be shown in some drawings and not in others, this is for convenience only. In accordance with the principles of the subject matter described herein, any feature of a drawing may be referenced and/or claimed in combination with any feature of any other drawing.

This written description uses examples to disclose the claimed subject matter, including the best mode, and also to enable any person skilled in the art to practice the subject matter described herein, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the subject matter described herein 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 have 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 language of the claims.

While the claimed subject matter has been described in terms of various specific embodiments, those skilled in the art will recognize that the subject matter can be practiced with modification within the spirit and scope of the claims.

Claims

1. A method for providing a seal between components within a gas turbine, said method comprising:

inserting a seal member into a first seal member receiving region defined within a first component of a gas turbine, wherein the first seal member receiving region is oriented between a higher-temperature gas region and a cooler-temperature gas region; and

inserting the seal member into a second recess defined within a second component of the gas turbine, wherein the second component is adjacent to the first component, and wherein at least one of the first and second seal member regions includes a first end wall and at least one of the first and second seal member regions includes a second end wall oriented substantially opposite the first end wall,

wherein the seal member includes at least a first layer defining at least a first seal end portion that engages one of the respective first and second end walls.

2. The method in accordance with claim 1, wherein said method further comprises defining the seal member to include a second seal end portion that engages another of the first and second end walls.

3. The method in accordance with claim 2, wherein defining the seal member to include a second seal end portion further comprises defining the seal member to include first and second seal end portions that have similar cross-sectional configurations.

4. The method in accordance with claim 2, wherein defining the seal member to include a second seal end portion further comprises defining the seal member to include first and second seal end portions that have different cross-sectional configurations.

5. The method in accordance with claim 1, wherein said method further comprises fabricating the seal member as a laminated seal member that includes at least a second layer coupled to the first layer.

6. The method in accordance with claim 1, wherein said method further comprises defining the first seal end portion as a planar member extending at an angle relative to a planar web portion of the first layer.

7. The method in accordance with claim 1, wherein said method further comprises defining the first seal end portion as a web extending from a planar web portion of the first layer, wherein the web includes a “W”-shaped cross-sectional configuration.

8. The method in accordance with claim 1, wherein said method further comprises defining the first seal end portion as a web extending from a planar web portion of the first layer, wherein the web includes a curved cross-sectional configuration.

9. The method in accordance with claim 1, wherein said method further comprises defining the seal member to include at least two layers, wherein each of the at least two layers includes at least one seal end portion.

10. The method in accordance with claim 9, wherein defining the seal member to include at least two layers further comprises defining each of the at least two layers to include first and second seal end portions having similar cross-sectional configurations.

11. A gas turbine system, said system comprising:

a compressor section;

a combustor assembly coupled to said compressor section; and

a turbine section coupled to said compressor section, wherein at least one of said combustor assembly and said turbine section includes a sealing sub-system for use in sealing between a first component and a second component, said sealing sub-system comprises:

a first component defining a first seal member receiving region oriented between a higher-temperature gas region and a cooler-temperature gas region;

a second component adjacent said first component, said second component defining a second seal member receiving region oriented adjacent said first seal member receiving region, wherein at least one of said first and second seal member receiving regions includes a first end wall, and at least one of said first and second seal member receiving regions includes a second end wall oriented substantially opposite said first end wall; and

a seal member oriented within said first and second seal member receiving regions, wherein said seal member includes at least a first layer defining at least a first resilient seal end portion that engages one of said first and second end walls.

12. The gas turbine system in accordance with claim 11, wherein said seal member includes a second seal end portion that engages another of said first and second end walls.

13. The gas turbine system in accordance with claim 12, wherein said first and second portions include similar cross-sectional configurations.

14. The gas turbine system in accordance with claim 12, wherein said first and second seal end portions include different cross-sectional configurations.

15. The gas turbine system in accordance with claim 11, wherein said seal member is a laminated seal member that includes at least a second layer coupled to the first layer.

16. The gas turbine system in accordance with claim 11, wherein said first seal end portion comprises a planar member extending at an angle relative to a planar web portion of said first layer.

17. The gas turbine system in accordance with claim 11, wherein said first seal end portion comprises a web extending from a planar web portion of said first layer, wherein said web includes a “W”-shaped cross-sectional configuration.

18. The gas turbine system in accordance with claim 11, wherein said first seal end portion comprises a web extending from a planar web portion of said first layer, wherein said web includes a curved cross-sectional configuration.

19. The gas turbine system in accordance with claim 11, wherein said seal member comprises at least two layers, wherein each of said at least two layers includes at least one seal end portion.

20. The gas turbine system in accordance with claim 19, wherein each of said at least two layers comprises first and second seal end portions having similar cross-sectional configurations.