Systems and methods for assembling flow path members

Abstract

An assembly for a turbomachine and a method for assembling a plurality of flowpath members are presented. The assembly includes a plurality of flowpath members disposed adjacent to one another, each flowpath member having a forward surface, an aft surface, a pressure side surface, and a suction side surface. A seal channel is defined by the pressure side surface and the suction side surface of adjacent flowpath members. The seal channel has an open forward end proximate the forward surface and at least two aft ends proximate the aft surface. The assembly includes a plurality of seal layers disposed within the seal channel such that one or more seal layers extend from the open forward end to an aft end and one or more other seal layers extend from the open forward end to another aft end.

Description

Technical Field

[0001] This disclosure generally relates to systems and methods for assembling flow path components for turbines, and more particularly, to systems and methods for sealing flow path components (e.g., nozzles in a gas turbine). Background Technology

[0002] Turbines (such as industrial, aircraft, or marine gas turbines) generally consist of a compressor, a combustor, and a turbine in a sequential flow order. A turbine has multiple stages, each stage comprising a row of turbine nozzles and an adjacent row of turbine rotor blades (located downstream of the nozzles). The turbine nozzles are fixed within the turbine, and the turbine rotor blades rotate with the rotor shaft. The various turbine stages define the path of hot gas through the turbine.

[0003] During operation, the compressor supplies compressed air to the combustor. Within the combustion chamber or reaction zone defined in the combustor, the compressed air mixes with fuel and burns to produce a high-speed hot gas flow. The hot gas flows from the combustor through the turbine inlet into the turbine's hot gas path. As the hot gas flows through successive stages, the kinetic energy from the high-speed hot gas is transferred to multiple rows of turbine rotor blades, causing the rotor shaft to rotate and generating mechanical work.

[0004] The first-stage turbine nozzles and turbine rotor blades are positioned closest to the turbine inlet and are therefore exposed to the highest hot gas temperatures. The first-stage turbine nozzles include airfoils extending across the span between the inner and outer belts or shrouds. The inner and outer belts define the inner and outer flow boundaries of the hot gas path and are exposed to the hot gas. When assembling adjacent turbine nozzles, the resulting assembly may include small gaps between the shrouds of adjacent turbine nozzles, which can provide undesirable fluid leakage paths. Sealing off potential leakage paths between adjacent turbine nozzles, and performing this action in a manner that makes assembly efficient and reliable, has always been a challenge. Summary of the Invention

[0005] One aspect of this disclosure provides an assembly for a turbine. The assembly includes: a plurality of flow path members arranged adjacent to each other, each of the plurality of flow path members having a front surface, a rear surface, a pressure-side surface, and a suction-side surface; and a sealing channel defined by a pressure-side surface of a first flow path member and a suction-side surface of a second flow path member, extending from the front surfaces of the first and second flow path members to the rear surfaces, wherein the sealing channel has an open front end adjacent to the front surface and at least two rear ends adjacent to the rear surfaces of the first and second flow path members; and a plurality of sealing layers disposed within the sealing channel, such that one or more of the sealing layers extend from the open front end to one of the at least two rear ends, and one or more other sealing layers extend from the open front end to the other of the at least two rear ends.

[0006] In one aspect of this disclosure, a method is provided for assembling adjacent flow path members to form an assembly of a turbine. The method includes the steps of: arranging a plurality of flow path members adjacent to each other, each of the plurality of flow path members having a front surface, a rear surface, a pressure-side surface, and a suction-side surface, such that a sealing channel is defined by a pressure-side surface of a first flow path member and a suction-side surface of a second flow path member, the sealing channel extending from the front surface of the first and second flow path members to the rear surface, and the sealing channel having an open front end near the front surface and at least two rear ends near the rear surfaces of the first and second flow path members; inserting one or more sealing layers through the open front end into the sealing channel to arrange the one or more sealing layers to extend from the open front end to one of the at least two rear ends; and inserting one or more other sealing layers through the open front end into the sealing channel to arrange the one or more other sealing layers to extend from the open front end to the other of the at least two rear ends.

[0007] Technical Solution 1. A turbine component, comprising: Multiple flow path components are arranged adjacent to each other, and each of the multiple flow path components has a front surface, a rear surface, a pressure side surface and a suction side surface. A sealing channel is defined by a pressure-side surface of one of the plurality of flow path members and a suction-side surface of an adjacent flow path member, and extends from the front surface of the flow path members to the rear surface; wherein the sealing channel has an open front end adjacent to the front surface and at least two rear ends adjacent to the rear surface of the flow path members; and A plurality of sealing layers are disposed within the sealing channel such that one or more of the plurality of sealing layers extend from the open front end to one of the at least two rear ends, and one or more other sealing layers extend from the open front end to the other of the at least two rear ends.

[0008] Technical Solution 2. The component according to Technical Solution 1, characterized in that the sealing channel extends from the open front end and is divided into at least two rear sections terminating at the at least two rear ends.

[0009] Technical Solution 3. The component according to Technical Solution 2, characterized in that the at least two rear sections diverge at an angle of at least 1 degree.

[0010] Technical Solution 4. The component according to Technical Solution 3, characterized in that the angle is in the range of approximately 3 degrees to approximately 90 degrees.

[0011] Technical Solution 5. The component according to Technical Solution 2, characterized in that at least one of the at least two rear sections has a thickness smaller than the thickness of the sealing channel at the open front end.

[0012] Technical Solution 6. The component according to Technical Solution 1, characterized in that the plurality of sealing layers are substantially conformable to the sealing channel.

[0013] Technical Solution 7. The component according to Technical Solution 1, characterized in that the one or more sealing layers have a lower degree of plastic deformation than the plastic deformation of the one or more other sealing layers.

[0014] Technical Solution 8. The component according to Technical Solution 1, characterized in that the one or more sealing layers have higher oxidation resistance than the one or more other sealing layers.

[0015] Technical Solution 9. The component according to Technical Solution 1, characterized in that the one or more sealing layers have a thickness greater than the thickness of the one or more other sealing layers.

[0016] Technical Solution 10. The component according to Technical Solution 1, characterized in that each of the plurality of sealing layers has a thickness in the range of about 0.1 mm to about 1 mm.

[0017] Technical Solution 11. A method for assembling multiple flow path components, comprising: The plurality of flow path members are arranged adjacent to each other, each of the plurality of flow path members having a front surface, a rear surface, a pressure side surface, and a suction side surface, such that a sealing channel is defined by the pressure side surface of one of the plurality of flow path members and the suction side surface of an adjacent flow path member, the sealing channel extending from the front surface of the flow path member to the rear surface, and wherein the sealing channel has an open front end adjacent to the front surface and at least two rear ends adjacent to the rear surface of the flow path member; and Multiple sealing layers are disposed in the sealing channel through the following steps: One or more of the plurality of sealing layers are inserted into the sealing channel through the open front end to arrange the one or more sealing layers from the open front end to one of the at least two rear ends; and One or more other sealing layers of the plurality of layers are inserted into the sealing channel through the open front end to arrange the one or more other sealing layers to extend from the open front end to another of the at least two rear ends.

[0018] Technical Solution 12. The method according to Technical Solution 11, characterized in that the sealing channel extends from the open front end and is divided into at least two rear sections terminating at the at least two rear ends.

[0019] Technical Solution 13. The method according to Technical Solution 12, characterized in that the at least two rear sections diverge at an angle of at least 1 degree.

[0020] Technical Solution 14. The method according to Technical Solution 11, characterized in that the one or more sealing layers have a lower degree of plastic deformation than the plastic deformation of the one or more other sealing layers.

[0021] Technical Solution 15. The method according to Technical Solution 11, characterized in that the one or more sealing layers have higher oxidation resistance than the one or more other sealing layers.

[0022] Technical Solution 16. The component according to Technical Solution 11, characterized in that the one or more sealing layers have a thickness greater than the thickness of the one or more other sealing layers.

[0023] Technical Solution 17. The method according to Technical Solution 11, characterized in that the setting step includes continuously inserting the one or more sealing layers and the one or more other sealing layers.

[0024] These and other features, embodiments, and advantages of this disclosure can be more readily understood by referring to the detailed description below. Attached Figure Description

[0025] These and other features, aspects and advantages of this disclosure will become clearer when the following detailed description is read with reference to the accompanying drawings, wherein, throughout the drawings, the same characters denote the same parts, wherein: Figure 1 This is a schematic diagram of a gas turbine according to some embodiments of the present disclosure.

[0026] Figure 2 This is a cross-sectional side view of the turbine section of a gas turbine according to some embodiments of the present disclosure.

[0027] Figure 3 This is a perspective view of a stator assembly according to some embodiments of the present disclosure, including a plurality of turbine nozzles arranged adjacent to each other.

[0028] Figure 4 This is a perspective side view of the outer band of a turbine nozzle according to some embodiments of the present disclosure.

[0029] Figure 5 A schematic diagram of a sealing layer with discontinuities according to some embodiments of the present disclosure is shown.

[0030] Figure 6 This is a perspective side view of the outer band of a turbine nozzle according to some embodiments of the present disclosure.

[0031] Figure 7 A flowchart illustrating a method for sealing adjacent turbine nozzles to form a stator assembly according to some embodiments of the present disclosure is shown.

[0032] It should be noted that the accompanying drawings of this disclosure are not drawn to scale. The drawings are intended to depict only typical aspects of this disclosure and therefore should not be considered as limiting the scope of this disclosure. Detailed Implementation

[0033] The embodiments provided herein pertain to systems and methods for sealing adjacent flow path members to form turbine assemblies. The systems (such as sealing layers) and methods for sealing as described herein advantageously provide improved simplicity and efficiency in installing sealing layers between flow path members and assembling assemblies, as well as desirable mechanical properties (such as creep resistance at high temperatures in the turbine, shear / torsional strength, and thermal shock resistance). As discussed in detail below, some embodiments relate to gas turbine assemblies (such as stator assemblies) comprising a plurality of flow path members (such as turbine nozzles) arranged adjacent to each other.

[0034] While exemplary embodiments of the invention will be described generally in the context of a stator assembly of a land-based power generation gas turbine for illustrative purposes, those skilled in the art will readily recognize that embodiments of the invention are applicable to any style or type of gas turbine, and are not limited to land-based power generation gas turbines, unless specifically stated in the claims.

[0035] In the following description and claims, unless the context clearly indicates otherwise, the singular forms “a,” “an,” and “the” include a plurality of referenced objects. As used herein, unless the context clearly indicates otherwise, the term “or” is not intended to be exclusive but refers to at least one of the referenced elements and includes instances of combinations of the referenced elements that may exist.

[0036] As used herein throughout the specification and all claims, approximate language may be applied to modify any permitted quantitative representation without causing a change in its underlying function. Therefore, values ​​modified with terms such as “approximately” and “substantially” are not limited to precise specified values. In some instances, approximate language may correspond to the precision of the instrument used to measure the value.

[0037] Unless otherwise specified, the technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this disclosure pertains. The terms “comprising,” “including,” and “having” are intended to be inclusive and mean that additional elements may be present in addition to those listed. As used herein, the terms “first,” “second,” etc., do not indicate any order, quantity, or importance, but rather are used to distinguish elements from one another. The terms “upstream” and “downstream” refer to the relative directions of fluid flow in a fluid passage. For example, “upstream” refers to the direction from which the fluid flows, and “downstream” refers to the direction to which the fluid flows. The term “radial” refers to a relative direction substantially perpendicular to the axial centerline of a specific component, and the term “axial” refers to a relative direction substantially parallel and / or coaxially aligned with the axial centerline of a specific component.

[0038] In some embodiments, reference Figure 1-2 The description includes an assembly of a gas turbine comprising a plurality of flow path components arranged adjacent to each other, and a method for sealing adjacent flow path components to form the assembly.

[0039] Now refer to the attached diagram, Figure 1The illustration is a schematic diagram of a gas turbine 10 that can be incorporated into various embodiments of the present disclosure. As shown, the gas turbine 10 generally includes a compressor section 12 having an inlet 14 located upstream of a compressor 16. The gas turbine 10 also includes a combustion section 18 having one or more burners 20 located downstream of the compressor 16, and a turbine section 22 including a turbine 24 (such as an expansion turbine) is located downstream of the combustion section 18. A shaft 26 extends axially through the compressor 16 to the turbine 24 along the axis 28 of the gas turbine 10.

[0040] Figure 2 A cross-sectional side view of a turbine 24, which may be incorporated into various embodiments of this disclosure, is provided. The turbine 24 may include multiple turbine stages. Figure 2 As shown, turbine 24 may include three turbine stages, including a first stage 30, a second stage 31, and a third stage 32. The total number of turbine stages may be more or less than three, and embodiments of this disclosure should not be limited to three turbine stages.

[0041] Each turbine stage (30, 31, 32) includes a corresponding stator assembly and a corresponding rotor assembly axially spaced along axis 28. Figure 1 Each stator assembly includes multiple turbine nozzles arranged circumferentially adjacent to each other to form a ring structure. Figure 2 The cross-sectional side view shows, in sequential flow order, the corresponding turbine nozzles 40, 41, and 42 of each stator assembly and the corresponding turbine rotor blades 50, 51, and 52 of each rotor assembly. A housing or casing 36 circumferentially surrounds the turbine nozzles (40, 41, and 42) and the turbine rotor blades (50, 51, and 52). During operation of the gas turbine 10, the turbine nozzles (40, 41, and 42) remain fixed relative to the turbine rotor blades (50, 51, and 52).

[0042] During operation, such as in Figure 1 and Figure 2 As shown in the diagram, compressed air 38 from compressor 16 is supplied to combustor 20, where it is mixed with and combusted with fuel to provide a hot combustion gas stream that flows from combustor 20 to turbine 24 in flow path 25. At least a portion of the compressed air 38 can be used as a cooling medium for cooling various components of turbine 24.

[0043] Figure 3 This shows that it can be combined with, for example Figure 2The diagram shows a perspective view of a stator assembly 100 comprising a plurality of turbine nozzles 110, as can be incorporated into various embodiments of the present disclosure, within the turbine 24. The turbine nozzles 110 may correspond to or be mounted in conjunction with any of the turbine nozzles (40, 41, or 42). In some embodiments, the turbine nozzles 110 correspond to the turbine nozzles 40 of the first stage 30 (which may also be referred to in the industry as first-stage nozzles or S1N).

[0044] like Figure 3 As shown, each turbine nozzle 110 includes: an inner band 200; an outer band 300 radially spaced from the inner band 200; and an airfoil 400 extending across the span from the inner band 200 to the outer band 300. The airfoil 400, inner band 200, and outer band 300 of the turbine nozzle 110 are typically manufactured as a single piece from a homogeneous base material (however, these components may undergo different machining, processing, and coating processes). As shown, adjacent turbine nozzles 110 are mounted in the stator assembly 100 to form a circular structure. In this circular structure, the outer band 300 and inner band 200 of adjacent turbine nozzles 110 form a solid outer ring 120 and a solid inner ring 130 (parts of the solid outer ring 120 and solid inner ring 130 are within...). Figure 3 (as shown in the image).

[0045] Each inner zone 200 includes a gas-side surface 202 and a back-side surface 204, the back-side surface 204 being oriented radially inward from the gas-side surface 202. Each outer zone 300 includes a gas-side surface 302 and a back-side surface 304, the back-side surface 304 being oriented radially outward from the gas-side surface 302. Figure 3 As shown, the gas-side surface 302 of the outer belt 300 and the gas-side surface 202 of the inner belt 200 define inner and outer radial flow boundaries for the hot combustion gas flow from the combustor 20 through the turbine 24 at high speed. When the plurality of turbine nozzles 110 are assembled in the stator assembly 100, the inner belt 200 and the outer belt 300, defining inner and outer radial flow boundaries for the hot combustion gas flow, should not allow leakage through adjacent inner belts 200 and outer belts 300 or between adjacent inner belts 200 and outer belts 300. Similarly, other components in the turbine flow path may be assembled with adjacent components, creating undesirable leakage paths without reliable seals. For example, when sealing is required, shields, covers, spacers, near-flow path seals (NFPS), and other components (which define the desired flow path and are assembled in multiple pieces in some turbines) may have similar seams between adjacent components.

[0046] Figure 4 A cross-sectional view of the outer band 300 of the turbine nozzle 110 is shown. Figure 3 ). refer to Figure 4 The outer casing 300 has a front surface 312, a rear surface 314, a pressure-side surface 316, and a suction-side surface 318 (in... Figure 4 (Not visible in the middle). The front surface 312 may be defined by a surface 300 perpendicular to the flow path 25 of the gas turbine 10. Figure 1 When the stator assembly 100 is assembled in the gas turbine 10, the front surface 312 may face the installer. The rear surface 314 may be defined by a surface of the outer belt 300 perpendicular to the flow path 25, and is located at a more downstream position in the flow path 25 compared to the front surface 312. When the stator assembly 100 is assembled in the gas turbine 10, the rear surface 314 faces away from the installer. The pressure-side surface 316 may be defined by a surface of the outer belt 300 perpendicular to the axis 28 and facing the adjacent turbine nozzle. The suction-side surface 318 may be defined by a surface of the outer belt 300 perpendicular to the axis 28 and facing the adjacent turbine nozzle.

[0047] The outer band 300 has a length measured along the general direction of the flow path 25, from the foremost feature of the front surface 312 to the rearmost feature of the rear surface 314. Note that this body length includes protruding surface features that may not be considered indispensable to the outer band 300. The body length can be defined as the distance along a line parallel to axis 28 from the foremost portion of the theoretically planar front surface (extending from the leading edge of the back surface 304 to the leading edge of the gas-side surface 302) to the rearmost portion of the theoretically planar rear surface (extending from the trailing edge of the back surface 304 to the trailing edge of the gas-side surface 302). The outer band 300 has a body height substantially perpendicular to the body length. The body height can be measured from the back surface 304 of the outer band 300 to the gas-side surface 302.

[0048] Figure 4 The outer strip 300 is shown in the side view, while the adjacent outer strip (of the adjacent turbine nozzle) that would otherwise obscure the features of the pressure-side surface 316 is not shown. A portion of the sealing channel 320 and multiple sealing layers 350 are shown because they will appear after installation. In some embodiments, the adjacent outer strip is positioned close to the pressure-side surface 316 prior to the installation of the multiple sealing layers 350.

[0049] like Figure 4 As illustrated, the outer belt 300 includes a portion of a sealing channel 320 on its pressure-side surface 316. The sealing channel 320 is partially defined by a recess in the pressure-side surface 316 of the outer belt 300. The sealing channel 320 is further defined by an adjacent suction-side surface of the outer belt 300 (not shown in the figure). Figure 4 (as shown in the diagram) (it is configured to be adjacent to the pressure-side surface 316 of the outer belt 300) Figure 3Similar and complementary recesses (i.e., another portion of the sealing channel 320) define the outer belt 300. Similarly, the outer belt 300 will have complementary recesses (not shown) on its suction-side surface 318 to define another sealing channel with the pressure-side surface of the adjacent outer belt (which is configured to be adjacent to the suction-side surface 318 of the outer belt 300). The sealing channel 320 extends along a direction from the front surface (e.g., 312) of the outer belt 300 and the adjacent outer belt to the rear surface (e.g., 314). The sealing channel 320 has an open front end 322 adjacent to the front surface 312 and at least two rear ends 324 and 326 adjacent to the rear surface 314 of the outer belt 300. The open front end 322 may be open to the back surface 304 of the outer belt 300 and is adjacent to the front surface 312. The open front end 322 provides an opening through which a plurality of sealing layers 350 are inserted into the sealing channel 320. Figure 4 The sealing channel 320 is described by referring to partial features of the portion shown. The sealing channel 320 is further defined by similar and complementary recesses in the suction-side surface (not shown) of the adjacent outer belt (which is arranged adjacent to the pressure-side surface 316 of the outer belt 300). These similar and complementary portions of the sealing channel on the adjacent outer belt complete the sealing channel 320.

[0050] As shown in the illustrated embodiment, the sealing channel 320 extends substantially along both the body length and body height of the outer strip 300. In this context, "substantially along" means that the sealing channel 320 traverses a large portion of the body length and a large portion of the body height. In one embodiment, the sealing channel 320 extends along at least 85% of the body length and at least 85% of the body height.

[0051] refer to Figure 4 The sealing channel 320 has a front portion 330 and a rear portion 340. The front portion 330 extends from the open front end 322 to the rear portion 340, and the rear portion 340 extends continuously from the front portion 330 to the rear surface 314. The front portion 330 includes a vertical portion 332 that extends from the open front end 322 to a connecting portion 334. The front portion 330 also includes a transverse portion 336 that extends from the connecting portion 334 to the rear portion 340. In one embodiment, the connecting portion 334 may be curved (e.g., Figure 4As shown in the diagram, the lateral portion 336 has a radius of curvature ranging from, for example, approximately 0.5 inches to approximately 2.5 inches. The lateral portion 336 is substantially parallel to one or both of the planes defined by two or more edges of the back surface 304 and the gas-side surface 302 of the outer belt 300. In this context, substantially parallel means that a large portion of the lateral portion 336 is at an angle of less than 20 degrees from at least one of the reference planes. The lateral portion 336 and the vertical portion 332 are similarly substantially perpendicular to each other and substantially perpendicular to their respective reference planes. In this context, substantially perpendicular means that a large portion of the lateral portion 336 is at an angle of 75-105 degrees (90 degrees + / - 15 degrees) relative to a large portion of the vertical portion 332 and / or the rear surface plane. Similarly, substantially perpendicular means that the vertical portion 332 is at an angle of 75-105 degrees relative to a large portion of the lateral portion 336. A connecting portion 334 extends between the lateral portion 336 and the vertical portion 332, connecting the lateral portion 336 to the vertical portion 332. In some embodiments, as shown in the figure, the connecting portion 334 is an arc-shaped channel between the horizontal portion 336 and the vertical portion 332.

[0052] In some embodiments, as shown, the rear portion 340 is divided into two rear sections: a first rear section 344 extending from the transverse portion 336 to the first rear end 324 and a second rear section 346 extending from the transverse portion 336 to the second rear end 326. The first and second rear sections (344, 346) may terminate at a closed end or include an open end. As shown, the first rear section 344 extends substantially parallel to and continuously with the transverse portion 336. That is, the first rear section 344 extends substantially along the length of the body. The second rear section 346 extends continuously with the transverse portion 336 and diverges together with the first rear section 344. The first rear section 344 and the second rear section 346 diverge at an angle of at least 1 degree. In some embodiments, the divergence angle is in the range of approximately 3 degrees to approximately 90 degrees. In some embodiments, the divergence angle is in the range of approximately 10 degrees to approximately 70 degrees. In some embodiments, for example, the second rear section 346 may be as follows: Figure 4 The portion shown is curved and has a convex surface 348 facing the first rear section 344. The curved second rear section 346 may have a radius of curvature in the range of, for example, about 0.5 inches to about 2.5 inches.

[0053] In some embodiments, the sealing channel 320 defined between the outer strap 300 and an adjacent outer strap may have a uniform thickness throughout its length. The thickness of the sealing channel 320 may be defined as the width of the recess, and in Figure 4The symbol is 'd'. In some embodiments, the first and second rear sections (344, 346) of the front portion 330 and the rear portion 340 may have different thicknesses. In some embodiments, at least one of the first rear section 344 or the second rear section 346 has a thickness equal to that of the front portion 330. In some embodiments, at least one of the first rear section 344 or the second rear section 346 has a thickness less than that of the front portion 330. Moreover, the first rear section 344 and the second rear section 346 may have the same or different thicknesses. Furthermore, the sealing channel 320 does not need to have a uniform depth along its entire length in the adjacent pressure-side surface 316 and suction-side surface of the outer belt.

[0054] As previously implied, the plurality of sealing layers 350 can be inserted through the open front end 322, travel through the vertical portion 332, the connecting portion 334 and the transverse portion 336, and be guided to the first rear section 344 and the second rear section 346 to terminate at the corresponding first and second rear ends 324 and 326. Figure 4 Only a portion of the sealing channel 320 is shown; when this portion is installed between the outer belt 300 and an adjacent outer belt, it guides and positions multiple sealing layers 350. Similar and complementary portions of the sealing channels on adjacent outer belts will complete the sealing channel 320.

[0055] exist Figure 4 In the diagram, a plurality of sealing layers 350 are shown in their mounting configuration. The plurality of sealing layers 350 are disposed within a sealing channel 320 such that one or more sealing layers 352 of the plurality of sealing layers 350 extend from an open front end 322 to a first rear end 324, and one or more other sealing layers 354 of the plurality of sealing layers 350 extend from the open front end 322 to a second rear end 326. In some embodiments, the plurality of sealing layers 350 are substantially adapted to the sealing channel 320. That is, one or more sealing layers 352 are adapted to a portion of the sealing channel 320 extending from the open front end 322 to the first rear end 324, and one or more other sealing layers 354 are adapted to another portion of the sealing channel 320 extending from the open front end 322 to the second rear end 326.

[0056] The sealing layers in the plurality of sealing layers 350 may be gaskets or laminated sealant sheets. For example, each sealing layer may comprise a thin rectangular body (e.g., a strip, sheet, or foil of a material (such as an alloy with a desired width, length, and thickness). Suitable materials for the plurality of sealing layers 350 may be selected based on their elastic properties, temperature tolerance, and other physical characteristics compatible with the environment in the turbine flow path 25. Some examples of suitable materials include, but are not limited to, cobalt-based alloys (such as Haynes® 188 alloy or Haynes® 25 alloy).

[0057] Individual sealing layers among the plurality of sealing layers 350 may be the same or different in their thickness, length, and material, or may combine the same or different desired properties (such as elastic properties, flexibility, yield strength, oxidation resistance, or sealing properties) to facilitate lamination, insertion, and retention. The elastic properties of the sealing layers may depend in part on the material and thickness of the sealing layers. In some embodiments, individual sealing layers among the plurality of sealing layers 350 comprise the same or different materials. In some embodiments, individual sealing layers among the plurality of sealing layers 350 have the same or different thicknesses. For example, depending on the desired elastic properties of the individual sealing layer, each sealing layer among the plurality of sealing layers 350 may have a thickness ranging from about 0.1 mm to about 1 mm. In some embodiments, each sealing layer has a thickness ranging from about 0.2 mm to about 0.6 mm. In some embodiments, one or more sealing layers 352 have a thickness greater than the thickness of one or more other sealing layers 354. In some embodiments, the thickness of the sealing layers among the plurality of sealing layers 350 may vary along their length.

[0058] In some embodiments, the plurality of sealing layers 350 may be large enough to conform to, for example, during insertion. Figure 4 The flexibility of the curved path of the sealing channel 320 shown. Ideally, one or more additional sealing layers 354 should have less flexibility compared to one or more sealing layers 352. For example, one or more additional sealing layers 354 may have sufficient flexibility to be inserted into the second rear section 346 (this may depend on the radius of curvature of the second rear section 346). In some embodiments, one or more sealing layers 352 have a lower degree of plastic deformation than one or more additional sealing layers 354. These characteristics allow one or more additional sealing layers 354 to be inserted into the second rear section 346 of the sealing channel 320.

[0059] Furthermore, it is equally desirable that one or more sealing layers 352 have different oxidation resistances than one or more other sealing layers 354, depending on their location within the gas turbine. The oxidation resistance of a sealing layer may depend in part on the material of the sealing layer. In some embodiments, one or more sealing layers 352 have higher oxidation resistance than one or more other sealing layers 354.

[0060] The number of sealing layers in the first rear section 344 and the second rear section 346 may depend on various parameters (such as the thickness of the sealing layers, the flexibility of the sealing layers, the thickness of the first rear section 344 and the second rear section 346, and the thickness of the front portion 330, etc.). In some embodiments, the total thickness of the plurality of sealing layers 350 (the portions of the plurality of sealing layers 350 disposed in the front portion 330) matches the thickness of the front portion 330. In some embodiments, the total thickness of one or more sealing layers 352 (the portions of one or more sealing layers 352 disposed in the first rear section 344) matches the thickness of the first rear section 344. In some embodiments, the total thickness of one or more other sealing layers 354 (the portions of one or more other sealing layers 354 disposed in the second rear section 346) matches the thickness of the second rear section 346.

[0061] In some embodiments, one or more sealing layers 352 have a discontinuity at a location such that, when installed in a sealing channel 320, the discontinuity is located in a transverse portion 336 of the sealing channel 320. As used herein, the term "discontinuity" refers to an interruption in the general physical structure or configuration of the sealing layer. A discontinuity may include a change in the surface structure of the sealing layer. For example, a discontinuity may be a gap, cut, bump, or external feature added to the surface of the sealing layer. For example, in Figure 5 The diagram shows a sealing layer 352, which has protrusions 355 on its surface 351. In some embodiments, the interruption is located at a portion of the sealing layer (disposed in the sealing channel) near the rear portion 340 (wherein the sealing channel 320 is divided into a first rear section 344 and a second rear section 346). Furthermore, in some embodiments, the sealing layer with the interruption is the topmost sealing layer of one or more sealing layers 152 inserted into the first rear section 144. This interruption helps guide subsequent sealing layers inserted into the sealing channel 320 to the second rear section 346 when one or more other sealing layers 354 are disposed. For example, Figure 6 The following view is shown: When the sealing layer 354 is inserted into the sealing channel 320, the protrusions 355 on the surface 351 of the sealing layer 352, which are pre-placed in the sealing channel, help guide the sealing layer 354 into the second rear section 346.

[0062] One or more sealing layers 352 and one or more other sealing layers 354 may be connected to each other for retention. In some embodiments, multiple sealing layers 350 may be connected at their front ends (these front ends are located near the open front end 322 of the sealing channel 320). Multiple sealing layers 350 may be connected, for example, by welding before and after insertion into the sealing channel 320. For example, the front ends of multiple sealing layers 350 may be connected after insertion. Other shapes, configurations, attachments between sealing layers, the number of sealing layers, and the shaping of one or both ends of the sealing layers may also be desirable for specific embodiments and retention of multiple sealing layers.

[0063] Figure 7 A method 500 is illustrated as follows: assembling a plurality of flow path components (such as turbine nozzles 110) to form an assembly (such as a turbine stator assembly 100 as shown in the previous figures). In step 510, method 500 includes arranging the plurality of flow path components (such as turbine nozzles 110) adjacent to each other. In some embodiments, the plurality of turbine nozzles 110 are arranged circumferentially about axis 28. Figure 1 In step 520, method 500 includes setting a plurality of sealing layers 350 into a sealing channel 320. Details of the sealing channel 320 have been previously described. In step 520, setting the plurality of sealing layers 350 is performed by inserting the plurality of sealing layers 350 into the sealing channel through an open front end 322.

[0064] Step 520 includes a sub-step 530: inserting one or more sealing layers 352 of the plurality of sealing layers 350 into the sealing channel 320 through the open front end 322, so as to arrange the one or more sealing layers 352 extending from the open front end 322 to the first rear end 324. Step 520 also includes another sub-step 540: inserting one or more other sealing layers 354 of the plurality of sealing layers 350 into the sealing channel 320 through the open front end 322, so as to arrange the one or more other sealing layers 354 extending from the open front end 322 to the second rear end 326.

[0065] In some embodiments, step 520 of setting includes sequentially inserting one or more sealing layers 352 and one or more other sealing layers 354. In some embodiments, the sub-step 530 of inserting one or more sealing layers 352 is performed prior to the sub-step 540 of inserting one or more other sealing layers 354. In some embodiments, each of the plurality of sealing layers 350 may be inserted one at a time. For example, method 500 first includes inserting one of the plurality of sealing layers 350 through an open front end 322, moving it through a front portion 330, moving it through a first rear section 344, until the inserted end of the sealing layer reaches a first rear end 324 of the sealing channel 320. Method 500 may include repeating the step of inserting a sealing layer at least once or more, depending on the desired number of sealing layers inserted into the first rear section 344. Continuing with the example, after several sealing layers 352 are inserted into the first rear end 344, a sealing layer 354 is then inserted through the open front end 322, moving through the front portion 330 and through the second rear section 346 until the inserted end of the sealing layer 354 reaches the second rear end 326 of the sealing channel 320. In some embodiments, in this step, the sealing layer 354 can be guided into the second rear section 346 (after the front portion 330 has been traveled) by using a discontinuity in the sealing layer 352 pre-inserted into the first rear section 344. The discontinuity in the pre-inserted sealing layer 352 can guide a subsequent sealing layer (i.e., sealing layer 354) into the second rear section 346 (e.g., ...). Figure 6 (as shown in the figure). In some embodiments, method 500 further includes inserting an additional sealing layer from one or more other sealing layers 354 into the sealing channel 320.

[0066] Multiple sealing layers 350 substantially seal off possible leakage paths between two adjacent outer bands. A substantially complete seal reduces the total possible leakage path between the outer bands by at least 85% compared to the leakage path between the outer bands without a seal. A substantially complete outer band seal reduces the leakage path between the outer bands of adjacent turbine nozzles by at least 99%. In some embodiments, the method may further include joining the multiple sealing layers 350 at their front ends (located at open front ends 322) after insertion. This helps to securely hold the multiple sealing layers 350 in place during operation of the gas turbine (where the multiple sealing layers 350 are mounted). A similar process can be achieved between the inner band of the turbine nozzle and other flow path components (which are mounted in segments and leave seams when sealing is required).

[0067] In conventional sealing arrangements, when multiple turbine nozzles are circumferentially assembled adjacent to each other in a stator assembly, several rigid seals (such as rigid seal sheets) are joined end-to-end to be installed along a curved sealing channel between the outer bands of the turbine nozzles. Several disadvantages exist with using these straight seals, including a complex assembly process and the possibility of several joints disengaging at different times during operation. Furthermore, these rigid seals cannot be easily removed without disassembling the stator assembly, and there is a risk of small seals (such as stopper seals) detaching. In contrast to these conventional arrangements, embodiments of this disclosure provide a simple and improved installation of flexible seals between flow path components of the turbine. Adjacent flow path components are designed to define openings at the open front ends of the sealing channel between them to receive and remove the flexible sealing layer. This provides ease of installing the sealing layer and removing it from the curved sealing channel without disassembling the stator assembly. The use of a flexible sealing layer advantageously (i) reduces the number of rigid seals inserted into the sealing channel along the length of the seal (i.e., the number of pieces), and (ii) reduces the possibility of leakage paths between flow path components (such as the outer band) that were not considered during manufacturing. Additionally, the distance between the turbine's flow path and the bottom side of the sealing channel of the flow path component can be reduced by bending the sealing channel. (Several) The use of a flexible sealing layer makes the bent sealing channel sealable, and thus allows for bent sealing channels in the flow path components (such as the inner and outer bands of the turbine nozzle). The reduction in the distance between the flow path and the bottom side of the sealing channel of the flow path component allows for minimizing the demand for purge air to cool it.

[0068] The foregoing figures illustrate some operational processes associated with several embodiments of the present disclosure. It should be noted that in some alternative implementations, depending on the actions involved, the described actions may not occur in the described order, or may actually be performed substantially simultaneously or in reverse order.

[0069] While only certain features of the invention have been illustrated and described herein, many modifications and alterations will occur to those skilled in the art. Therefore, it will be understood that the appended claims are intended to cover all such modifications and alterations that fall within the spirit of the invention.

Claims

1. A turbine component, comprising: Multiple flow path components are arranged adjacent to each other, and each of the multiple flow path components has a front surface, a rear surface, a pressure side surface and a suction side surface. A sealing channel is defined by a pressure-side surface of one of the plurality of flow path members and a suction-side surface of an adjacent flow path member, and extends from the front surface of the flow path members to the rear surface; wherein the sealing channel has an open front end near the front surface and at least two rear ends near the rear surface of the flow path members. as well as A plurality of sealing layers are disposed within the sealing channel such that one or more of the plurality of sealing layers extend from the open front end to one of the at least two rear ends, and one or more other sealing layers extend from the open front end to the other of the at least two rear ends, wherein the one or more sealing layers have a lower degree of plastic deformation than the one or more other sealing layers.

2. The component according to claim 1, characterized in that, The sealed channel extends from the open front end and is divided into at least two rear sections terminating at the at least two rear ends.

3. The component according to claim 2, characterized in that, The at least two rear sections diverge at an angle of at least 1 degree.

4. The component according to claim 3, characterized in that, The angle is in the range of approximately 3 degrees to approximately 90 degrees.

5. The component according to claim 2, characterized in that, At least one of the at least two rear sections has a thickness less than that of the sealing channel at the open front end.

6. The component according to claim 1, characterized in that, The plurality of sealing layers are substantially conformable to the sealing channel.

7. The component according to claim 1, characterized in that, The one or more sealing layers have higher oxidation resistance than the one or more other sealing layers.

8. The component according to claim 1, characterized in that, The one or more sealing layers have a thickness greater than the thickness of the one or more other sealing layers.

9. The component according to claim 1, characterized in that, Each of the plurality of sealing layers has a thickness ranging from approximately 0.1 mm to approximately 1 mm.

10. A method for assembling multiple flow path components, comprising: The plurality of flow path members are arranged adjacent to each other, each of the plurality of flow path members having a front surface, a rear surface, a pressure side surface, and a suction side surface, such that a sealing channel is defined by the pressure side surface of one of the plurality of flow path members and the suction side surface of an adjacent flow path member, the sealing channel extending from the front surface of the flow path member to the rear surface, and wherein the sealing channel has an open front end adjacent to the front surface and at least two rear ends adjacent to the rear surface of the flow path member; and Multiple sealing layers are disposed in the sealing channel through the following steps: One or more of the plurality of sealing layers are inserted into the sealing channel through the open front end to arrange the one or more sealing layers from the open front end to one of the at least two rear ends; and One or more other sealing layers of the plurality of layers are inserted into the sealing channel through the open front end to arrange the one or more other sealing layers to extend from the open front end to another of the at least two rear ends, wherein the one or more sealing layers have a lower degree of plastic deformation than the one or more other sealing layers.

11. The method according to claim 10, characterized in that, The sealed channel extends from the open front end and is divided into at least two rear sections terminating at the at least two rear ends.

12. The method according to claim 11, characterized in that, The at least two rear sections diverge at an angle of at least 1 degree.

13. The method according to claim 10, characterized in that, The one or more sealing layers have higher oxidation resistance than the one or more other sealing layers.

14. The method according to claim 10, characterized in that, The one or more sealing layers have a thickness greater than the thickness of the one or more other sealing layers.

15. The method according to claim 10, characterized in that, The setup steps include sequentially inserting the one or more sealing layers and the one or more other sealing layers.

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