JP2016205389A - Composite seals for turbomachinery - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a composite seal for reducing leakage between adjacent parts of a turbomachine. Composite seals can include metal shims, metal support structures and ceramic, glass or enamel coatings. The shims and support structures can be joined or fused together. The support structure may include internal voids or gaps, and the coating may be applied to the inside of the gaps or gaps in the support structure, between parts of the support structure and the shims, and substantially above the outer surface of the support structure. It may be applied to shims and support structures as it is. The support structure can thereby result in mechanical adhesion between the shim and the coating. In use, the coating provides thermal and / or chemical insulation to the metal shims and supporting structures of the seal. [Selection diagram] Fig. 1

Description

  The present invention relates generally to seals for reducing leakage, and more particularly to seals configured to work in seal slots to reduce leakage between adjacent fixed parts of a turbomachine.

  Leakage of hot combustion gases and / or cooling flow between turbomachine components generally reduces power output and reduces efficiency. For example, hot combustion gases may be contained within the turbine by bringing pressurized compressor air around the hot gas path. In general, leakage of high pressure cooling flow into the hot gas path between adjacent turbine components (such as stationary shrouds, nozzles and diaphragms, inner shell casing components, and rotor components) reduces efficiency and eliminates such leaks. In comparison, increased combustion temperatures and decreased engine gas turbine efficiency are required to maintain desirable power levels. In this way, turbine efficiency can be improved by reducing or eliminating leakage between turbine components.

  Conventionally, leakage between turbine component connections is handled with a metal seal located in a seal slot formed between turbine components, such as stationary components. The seal slot generally extends to the connection between the parts, and a metal seal located therein blocks or prevents leakage from the connection. However, preventing leakage between turbine component connections with a metal slot seal located in the seal slot of the turbine component is complicated by the fact that modern turbomachines produce relatively high temperatures. By introducing new materials such as ceramic matrix composite (CMC) turbine components that allow the turbine to operate at higher temperatures (eg, above 1500 ° C.) compared to conventional turbines, Conventional metal turbine slot seals for use may not be appropriate.

  Preventing leakage between turbine part connections with metal seals is that the seal slots of the turbine parts are formed by corresponding slot portions of adjacent parts (the seals located therein are thereby connected between the parts). Is further complicated by the fact that Unevenness between these adjacent parts (eg resulting from thermal expansion, manufacturing, assembly and / or installation restrictions) can cause uneven seals that can vary in configuration, shape and / or size over time. A slot contact surface is generated. If the seal does not bend, deforms or causes such unevenness, such unevenness of the seal slot contact surface allows leakage across the slot seal located within the seal slot. Unfortunately, due to misalignment of adjacent turbine components, many conventional metal shims that cause such uneven seal slot contact surfaces can withstand the increased operating temperature of the turbine sufficiently. There are cases where it is not possible.

  Therefore, it would be desirable to have a composite turbomachine component connection seal configured for use with a typical turbine seal slot that can withstand the gradually increasing operating temperatures of the turbine and accommodate the unevenness of the seal slot interface.

US Patent Application Publication No. 2013/0134678

  In a first aspect, the present disclosure provides a seal assembly for placing in a seal slot formed at least in part by adjacent turbomachine components for sealing gaps extending between the components. The seal assembly includes a metal shim, a porous metal support structure, and a ceramic, glass or enamel coating. The metal shim includes a seal surface and a support surface. The porous metal support structure is joined to the support surface of the metal shim. The ceramic, glass or enamel coating extends over and within the porous metal support structure such that the coating substantially covers the support surface side and support structure of the metal shim. The portion of the coating is located between the support surface of the metal shim and the portion of the metal support structure.

  In some embodiments, the portion of the coating includes a metal shim support surface and a metal in a direction that extends away from the support surface to mechanically couple the coating to the metal shim via a metal support structure. It may be located between parts of the support structure made. In such embodiments, the direction extending away from the support surface may be substantially perpendicular to the support surface.

  In some embodiments, the metal shim may be a substantially solid metal shim. In some embodiments, the coating may be chemically bonded to the support structure. In some embodiments, at least one of the metal shim support surface and the metal support structure may include a protective outer coating configured to prevent oxidation of the respective metal part. In some embodiments, the metal support structure may be diffusion bonded to the metal shim via at least one braze. In some embodiments, the metal support structure may be a mesh structure. In some embodiments, the portion of the coating may be located between the support surface of the metal shim and the portion of the metal support structure joined to the support surface of the metal shim.

  In some embodiments, the portion of the coating may be located between the support surface of the metal shim and the portion of the metal support structure that is not joined to the support surface of the metal shim. In such embodiments, the portion of the metal support structure that is not joined to the support surface of the metal shim extends from or is the portion of the metal support structure that is joined to the support surface of the metal shim. It may be connected with.

  In some embodiments, the coating may be coupled to at least one of the shim and the support surface of the support structure. In some embodiments, the seal assembly includes a second porosity bonded to the seal surface of the shim such that the second coating substantially covers the metal shim and the seal surface side of the second support structure. And a second ceramic, glass or enamel coating extending over and within the second porous metal support structure, wherein the second coating portion comprises a metal shim Between the sealing surface and a portion of the second metal support structure.

  In another aspect, the present disclosure provides a method of forming a seal assembly for use in a seal slot formed at least in part by adjacent turbomachine components for sealing gaps extending between the components. To do. The method includes joining at least a portion of a porous metal support structure with a metal shim. The method further includes applying a ceramic, glass or enamel coating material to the porous metal support structure such that the coating material covers the support surface side of the metal shim and the surface of the support structure. A portion located between the support surface of the shim shim and the portion of the metal support structure is included. The method also includes increasing the density of the ceramic, glass or enamel coating material to form a ceramic, glass or enamel coating that is mechanically secured to the metal shim via the metal support structure.

  In some embodiments, joining at least a portion of the metal support structure to the metal shim support surface includes diffusion bonding at least a portion of the metal support structure to the metal shim support surface. It's okay. In some embodiments, applying the ceramic, glass or enamel coating material to the porous metal support structure may include applying the high viscosity castable ceramic composition by screen printing or wiping with a towel. is there. In such embodiments, the method may further include removing a portion of the ceramic composition applied to the support structure via a doctor blade, wherein increasing the density of the ceramic composition is not possible. Curing the applied ceramic composition and heat treating. In some embodiments, applying a ceramic, glass or enamel coating material to a porous metal support structure applies a glass or enamel composition in a form that can be applied by painting, dip coating or spray coating. May include. In such embodiments, increasing the density of the glass or enamel composition may include drying and heat treating the applied glass or enamel composition.

  In another aspect, the present disclosure provides a turbomachine that includes a first turbine component and a second turbine component adjacent to the first turbine component, wherein the first and second turbine components are between the turbine components. At least a portion of the seal slot extending into the gap is formed. The turbomachine further includes a seal located within the seal slots of the first and second turbine components and extending into the gap therebetween. The seal includes a metal shim, a porous metal support structure, and a ceramic, glass or enamel coating. The metal shim includes a seal surface and a support surface. The porous metal support structure is joined to the support surface of the metal shim. The ceramic, glass or enamel coating is such that the coating substantially covers the support side of the metal shim and the support structure, and the part of the coating is between the support surface of the metal shim and the part of the metal support structure. Located on and within the metal support structure so as to be located.

  In some embodiments, the ceramic, glass or enamel coating of the seal is the first of the seal slots formed collectively by the first side of the first turbine component and the first side of the second turbine component. It may be positioned relative to one side. In some embodiments, the metal shim is a substantially solid metal shim and the porous metal support structure is a metal mesh structure. In some embodiments, the portion of the coating includes a metal shim extending in a direction that extends substantially perpendicular to the support surface to mechanically couple the coating to the metal shim via the metal support structure. It may be located between the support surface and the part of the metal support structure.

  These and other objects, features and advantages of the present disclosure will become apparent from the following detailed description of various aspects of the present disclosure, taken in conjunction with the accompanying drawings.

FIG. 3 illustrates a cross-sectional view of a portion of a first exemplary slot seal assembly according to the present disclosure. FIG. 2 shows a perspective view of the exemplary slot seal of FIG. 1 partially assembled to illustrate the placement of shims, support structures and coating portions. 2 is a perspective view of the exemplary slot seal shim and support structure subassembly of FIG. 1; FIG. FIG. 4 is an enlarged perspective view of a portion of the shim and support structure subassembly of FIG. 3. FIG. 5 is an enlarged cross-sectional view of a portion of the shim and support structure subassembly of FIG. 4. FIG. 5 shows a side cross-sectional view of an exemplary slot seal assembly located within a seal slot for sealing exemplary connections between turbine components. FIG. 5 is a side cross-sectional view of an exemplary slot seal assembly.

  Hereinafter, embodiments of the present invention will be described in detail. When introducing elements of various embodiments of the present invention, the articles “one (a)”, “one”, “the”, and “above” are used when the element is 1 or It means that there is more than that. The terms “comprising”, “including”, and “having” mean including and mean that there may be additional elements other than the listed elements. Neither example of operating parameters excludes other parameters of the disclosed embodiments. The parts, aspects, features, configurations, arrangements, uses and the like described, illustrated or disclosed herein with respect to a particular seal embodiment are subject to any other seal embodiment disclosed herein. The same applies.

  A composite turbomachine part connection seal configured for use in a turbine seal slot (eg, a composite turbine slot seal), and methods for making and using the same, according to the present disclosure, are described in US Pat. It is configured to withstand temperature and / or adapt to the unevenness of the seal slot contact surface. In particular, the composite slot seal is configured to substantially prevent chemical interaction between the metal components of the composite slot seal and hot gas flow / leakage and / or the seal slot itself and substantially limit thermal interaction. Has been. Thus, the composite slot seal provided herein enables use in high temperature turbine applications. In addition to high temperature operation, the disclosed composite slot seal is configured to accommodate irregularities on the seal slot contact surface to reduce leakage due to seal slot surface misalignment and / or roughness. .

  As shown in FIGS. 1-5, an exemplary seal 10 includes a seal including at least one shim or plate 12, at least one support structure or layer 14, and at least one coating or coating layer 16, coupled to one another. It can be an assembly. The shim 12 can be effective to substantially prevent passage of material therethrough. For example, the shim 12 may be substantially solid or substantially impermeable to at least one of gas, liquid and solid at the pressure and temperature that occurs in a turbomachine. However, the shim 12 can also provide flexibility in the pressure and temperature that occurs in turbomachines to accommodate distortion or bias in the direction of thickness T1 at the slot surface. In one embodiment, shim 12 is a metallic member such as a substantially solid plate. In some such embodiments, the shim 12 can be a high temperature metal alloy or a superalloy. For example, in some embodiments, the shim 12 (and / or support structure 14) is made from Haynes 214, which is stainless steel or a nickel-based alloy (at least a portion), such as a nickel molybdenum chromium alloy, or Haynes 214 with an aluminum oxide coating. May be. In some embodiments, the shim 12 may be made from a metal having a melting temperature of at least 1,500 degrees Fahrenheit, more preferably at least 1800 degrees Fahrenheit. In some embodiments, the shim 12 may be made from a metal having a melting temperature of at least 2,200 degrees Fahrenheit.

  As shown in FIGS. 1-5, the outer sealing surface or side 22 of the shim 12 substantially opposite the support structure 14 may be substantially flat (neutral state). As further described below, the outer sealing surface 22 of the shim 12 provides a cooling high pressure that flows through at least one gap or seam between at least the first and second parts forming (at least a portion) a sealing slot. The seal 10 may be configured to engage or interact with the air flow so that the seal 10 is pushed or pressed against the seal surfaces of the first and second parts of the seal slot to provide gas, liquid and / or Or substantially prevent solids from moving through gaps or seams. Thus, since at least one of shim 12 and coating 16 (or shim 12 and coating 16 acting together) is substantially impermeable to liquids, gases and / or solids at the pressures experienced in turbomachines, 10 provides at least a low leakage rate through the seal slot.

  As shown in FIGS. 1-5, the support structure 14 can be coupled to a support surface or side 24 of the shim 12 that is substantially opposite the seal surface 22. In some embodiments, the support structure 14 may be a metal, such as a metal material having the characteristics described above with respect to the shim 12. The shim 12 and the support structure 14 may be formed of the same or substantially the same type of metallic material, thereby including the same or substantially the same coefficient of thermal expansion (hereinafter CTE). However, the shim 12 and the support structure 14 need not be formed of the same or substantially similar materials, and need not include the same or substantially the same CTE. However, the shim 12 and the support structure 14 are seals in use in a turbomachine, as the difference in CTE between them breaks or breaks the diffusion bond between them or is further described below. It is preferably configured so that there is no invalidation between them by 10 repeated heat loads. Thus, the CTE of the shim 12 and the CTE of the support structure 14 may differ only to the extent that the diffusion bonding between the shim 12 and the support structure 14 is not invalidated by the repeated heat load of the seal 10 being used in a turbomachine. . That is, the material of the shim 12 and the support structure 14 (or any other factor that affects the CTE) may be different, but the shim 12 and the support structure 14 are different when the seal 10 is used in a turbine seal slot. It may be configured so that when subjected to repeated heat loads, the diffusion bond between them is not damaged or rendered ineffective.

  The support structure 14 can be chemically bonded or fused (eg, by diffusion bonding) to the support surface 24 of the shim 12 and is firmly machined by the coating 16 (chemically bonded to the shim 12). It may be a support structure, member or assembly that can be connected or attached to each other. In this way, the coating 16 can be securely mechanically connected or attached to the shim 12 by the support structure 14. For example, the support structure 14 is a substantially porous metal structure (as opposed to a substantially non-porous shim 12) that includes cavities or voids to hold portions of the coating 16 therein. It's okay. The term “porous” refers to the support structure 14, individually and / or collectively, that the coating 16 extends into the support structure 14 in a direction that extends from the top or outer surface of the support structure 14 toward the shim 12. An acceptable and at least some portion of the coating 16 extends at least generally away from the seal surface 24 of the shim 12 between the seal surface 24 of the shim 12 and at least a portion of the support structure 14, eg, the shim 12 A structure including pores, grooves, voids, gaps, cavities, or other interior spaces that are positioned substantially perpendicular to the sealing surface 24, as used herein to describe one or more members or mechanisms Is done. In some embodiments, the support structure 14 is a porous metal mesh, grid, honeycomb or knitted with interlocked, interwoven or interlaced members, fibers or portions, as shown in FIGS. May be of any kind of structure.

  As shown in FIGS. 1-5, at least some portions of the support structure 14 (e.g., metal mesh members or fiber portions) may be fused or joined to the support surface 24 of the shim 12. However, in some embodiments, other portions of the support structure 14 may be spaced from the support surface 24 of the shim 12 (ie, not fused or joined to the shim 12). For example, the metal mesh support structure 14 includes a metal member or fiber that includes a first portion fused or joined to the support surface 24 of the shim 12 and a second portion that is not joined or fused to the shim 12. Potentially, a regularly spaced support surface 24 of the shim 12 may be included. In this way, only a fragment or part of the support structure 14 may be joined or fused with the shim 12, and the remaining piece or part of the support structure 14 is connected to the joined or fused part (eg, mechanically Attached) or extended from a joined or fused part.

  The shim 12 and at least a portion of the support structure 14 may be joined or fused together so that they can effectively withstand the temperatures, pressures, and other conditions experienced by the seal slot of the turbine. For example, the shim 12 and at least a portion of the support structure 14 may be joined or fused in such a way that a solid chemical bond is formed therebetween. In some embodiments, the shim 12 and at least a portion of the support structure 14 may be in a solid state welded together (eg, through diffusion bonding). In some embodiments, the shim 12 and the support structure 14 may be diffusion bonded together by at least one high temperature brazing.

  The shim 12 and / or support structure 14 of the seal 10 may include one or more protective coatings (not shown) applied or located above or on its outer surface. For example, at least a portion of the outer surface of shim 12, such as sealing surface 22 or support surface 24, and / or at least a portion of the outer surface of support structure 14, may include at least one protective coating or layer. That is, at least a portion of the outer surface of shim 12 (eg, support surface 24) and / or support structure 14 is covered by a protective coating that overlies the underlying metal part (ie, metal shim 12 or metal support structure 14). Sometimes defined. Accordingly, one or more portions of the shim 12 and / or support structure 14 that are diffusion bonded together may include a protective coating or layer. For example, the support structure 14 may be joined to a protective coating that overlies the shim 12 and forms a support surface 24. One or more protective coatings of the metal shim 12 and / or the metal support structure 14 may be configured to substantially prevent or retard oxidation of the underlying metal part. In some embodiments, the one or more protective coatings of the metal shim 12 and / or the metal support structure 14 may include or substantially include an oxide, such as chromium oxide or alumina oxide. .

  At least one coating 16 may be applied to the seal 10 to protect the shim 12 and support structure 14 using at least a portion of the shim 12 and support structure 14 joined or fused together. As shown in FIGS. 1 and 2, the coating 16 is such that the coating 16 substantially covers or overlays at least the support structure 14 and the support surface 24 of the shim 12 (ie, the coating supports the seal 10). The seal 10 may be applied so that it extends above and into the structure 14 and thereby extends above the support surface 24 of the shim 12. The coating 16 can substantially fill the pores or voids of the support structure 14 and may be substantially non-porous (as opposed to the support structure 14). In some embodiments, the coating 16 may also be such that the seal surface 22 side of the seal 10 is the only side or edge of the seal 10 that is not covered by or does not include the coating 16. The support surface 24 side and side edges may be covered or overlaid.

  The coating 16 is at least a metallic shim 12 (and potentially a support structure 14) when the seal 10 is utilized in a turbine seal slot, such as a seal slot formed of a hot gas turbine component, such as a stationary component. ) Chemical interaction can be substantially prevented and thermal interaction can be substantially limited. As described further below, the coating 16 on the support structure 14 is configured to sealingly engage the first and second seal surfaces of the first and second parts forming the seal slot. And substantially preventing gas, liquid and / or solid from moving through the gap or seam between the first and second parts. As such, the coating 16 may be used for silicide formation, oxidation, thermal creep, and / or at least the metal shim 12 (and potentially the support structure 14) during use of the seal 10 in such a turbine seal slot. It can be effective to substantially prevent wear. That is, the coating 16 allows a metal-based seal, such as the seal 10 including one or more metal shims 12 (and potentially the support structure 14), to be utilized in high temperature gas turbine applications. In some embodiments, the coating 16 is effective to protect at least the metallic shim 12 and / or the support structure 14 (eg, prevent or reduce oxidation, silicide formation, thermal creep, wear, etc.). It may be any ceramic, glass or enamel material.

  In some embodiments, the coating 16 may be formed of a crystalline, glassy, or glass ceramic composite. In such embodiments, the coating 16 may include a metal oxide, nitride, or oxynitride. For example, coating 16 may include stabilized or unstabilized zirconia, alumina, titania, alkaline earth and / or rare earth zirconates, titanates, aluminates, tantalates and niobates, Intermetallic compounds such as tungstate, molybdate, silicate borate, phosphate, silicon nitride, silicon carbide, MAX phase material (Ti2AlC) and combinations thereof may be included. In some embodiments, the coating 16 may be formed from a high temperature porcelain enamel composition. For example, the coating 16 may include an alkali / alkaline earth aluminoborophosphorosilicate glass and a filler. The coating 16 (whether ceramic, glass or enamel) includes the necessary high temperature melt and fluidity to provide optimum stability and compliance in the operating conditions of the seal 10. It's okay.

  In some embodiments, the coating 16 (and / or the protective coating described herein) is at least partially diffused into the metal shim 12 (and / or the metal support structure 14) of the selected species. And / or reaction with the metal shim 12 (and / or the metal support structure 14) to form one or more metal silicides and / or at least one oxide layer with the metal shim 12 (and / or metal By forming on the metal support structure 14), it may be formed on the metal shim 12 (and / or the metal support structure 14). The selected species and one or more metal silicides formed by diffusion / reaction of the metal shim 12 (and / or the metal support structure 14) may be resistant to oxidation. One or more oxide layers formed by diffusion / reaction of the selected species and metal shim 12 (and / or metal support structure 14) may include negligible oxygen diffusing capacity therethrough. Yes, thus protecting the metal shim 12 (and / or the metal support structure 14). For example, Si can be utilized to diffuse into and / or react with the metal shim 12 (and / or the metal support structure 14). is there. In some embodiments, the species selected to form one or more metal silicides and / or at least one oxide layer include Al, Si, B, alloys thereof, or combinations thereof. Can be mentioned. In some embodiments, the metal shim 12 (and / or the metal support structure 14) may be formed of and include a refractory metal such as Mo, W, alloys thereof, or combinations thereof. Alternatively, the refractory metal shim 12 (and / or the support structure 14) may include a silicide layer and / or an alumina protective layer as at least a portion of the coating 16. In some embodiments, the one or more metal silicides and / or the at least one oxide layer are at a high temperature at a selected species of filler layer (eg, a powder or similar form) and a metal shim 12 ( And / or a metal support structure 14) reaction (ie, packing silicidation / oxide layer method). In other embodiments, the one or more metal silicides and / or at least one oxide layer on the metal shim 12 (and / or the metal support structure 14) are grown by vapor deposition (eg, chemical vapor deposition). (CVD) or physical vapor deposition (PVD)) followed by one or more coatings of selected species (eg, metal elements / alloys) by chemical and / or heat treatment.

  In some ceramic coating 16 embodiments, the ceramic coating 16 may be formed from a high viscosity castable composition, such as a castable cement (eg, COTRONICS 904 or 989). The high viscosity castable composition may be applied to the joined shim 12 and support structure 14 by screen printing or wiping with a towel. After the castable composition of coating 16 is applied to the joined shim 12 and support structure 14, excess coating 16 material is removed by the doctor blade method to obtain a desired or required thickness on seal 10 (eg, , A specific amount of coating castable composition above or above the outer surface of the support structure 14. The applied and leveled “green” coating is further processed to increase the density of the coating 16 material and chemically bond it to the bonded shim 12 and support structure 14 by curing and heat treatment. Good. Curing can cure the coating 16 material and heat treatment increases the density of the coating 16 material to a closed porosity state and eventually onto the bonded shim 12 and support structure 14. A coating 16 can be formed. As described above, the coating 16 may be bonded to the metal shim 12 itself, or may be bonded to a protective coating overlying the metal shim 12.

  In some glass or enamel coating 16 embodiments, the coating 16 may be formed from a paintable form of glass or enamel-based composition. The paintable form of the glass or enamel composition can include a relatively low viscosity that allows the glass or enamel composition to be applied to the joined shim 12 and support structure 14, or The joined shim 12 and support structure 14 may be dip coated or spray coated with a glass or enamel based composition. In some embodiments, the glass or enamel composition may include a solvent or the like to reduce the viscosity of the composition. After the glass or enamel composition is applied to the joined shim 12 and support structure 14, the composition is dried, for example, to remove the solvent from the applied composition. After the applied glass or enamel composition on the bonded shim 12 and support structure 14 is dried, the composition is heat treated to be chemically bonded and mechanically coupled to the shim 12 and support structure 14. A coating 16, which is a substantially dense and smooth glassy coating, can be formed.

  In some alternative embodiments, the coating 16 composition may be formulated as a precursor. For example, the coating 16 composition is formed from a sol that can be gelled from precursor slats such as nitrates, carboxylates, alkoxides, etc., and a certain proportion is added as a filler. The gelable sol can be applied to the bonded shim 12 and support structure 14 to form the coating 16 by any of the processes described above.

  As described above, is the coating 16 chemically bonded at least initially to the metal shim 12 (eg, above or in contact with the support surface 24 of the metal shim 12) and / or the metal support structure 14? Alternatively, the coating 16 (whether it is ceramic, glass or enamel) may be applied to the metal shim 12 and the metal support structure 14 so as to be directly connected. Also, as described above, the metallic shim 12 and / or the metallic support structure 14 may include a protective coating. In such embodiments, the coating 16 may be chemically bonded to the protective coating (and thereby indirectly chemically bonded to the metal shim 12 and / or the metal support structure 14).

  The coating 16 substantially fills the voids of the support structure 14 (including any space between the support structure 14 and the shim 12 as further described below), and the top surface or the outer surface of the support structure 14. It can extend upward (thus covering the support surface 22 of the shim 12). As described further below, the support structure 14 may be configured to be chemically bonded to the shim 12 and mechanically coupled to the coating 16. Thus, the coating 16 effective to thermally and chemically insulate the metal shim 12 is at least initially chemically bonded to the metal shim 12 and the metal support structure 14 and mechanically May be fixed.

  In order for the coating 16 to provide continuous or reliable protection to at least the metal shim 12 (and potentially the metal support structure 14), the support structure 14 may be placed over the metal shim 12, eg, a turbine seal. It may be effective to maintain adhesion or coating of the coating 16 on at least the sides, edges or portions of the metal shim 12 that may be exposed during use in the slot. For example, a chemical bond or coupling between the ceramic or glass coating 16 and the metal shim 12 and the metal support structure 14 (or a protective coating thereon) may result in a ceramic or glass coating 16 and the metal shim 12 and metal. Due to a thermal mismatch with the support structure 14, the thermal cycle of the shim 12 (eg, occurring during use of the shim 12) may not be tolerated. As shown in FIGS. 1 and 2 and described above, the metal support structure 14 may be joined or fused to the metal shim 12, and the coating 16 may extend at least throughout the voids of the support structure 14 or within the voids. May be provided. More specifically, however, the coating 16 also extends or is located at least partially in a direction extending between the shim 12 and the portion of the support structure 14, at least generally away from the sealing surface 22 of the shim 12. Sometimes. In some embodiments, the coating 16 is at least partially substantial relative to the support surface 24 of the shim 12 between the shim 12 and a portion (or portion thereof) of the individual member, fiber or support structure 14. May be located in a direction extending vertically. Thereby, the coating 16 is provided or spread substantially around the fiber, member or portion of the support structure 14 (except that portion fused or joined to the shim 12). Thus, at least a portion of the fiber, member or support structure 14 portion is joined or fused to the metal shim 12, and the coating 16 portion is located between the shim 12 and the support structure 14 portion. The support structure 14 provides a mechanical attachment of the coating 16 to the metallic shim 12 that prevents the coating 16 from separating or decoupling from the shim 12. For example, if a chemical bond between the coating 16 and the metal shim 12 and / or the metal support structure 14 (or a protective coating thereon) fails due to a thermal mismatch therebetween, a fiber, member Or placing a coating 16 that is substantially around the portion of the support structure 14 (eg, above the outer surface of the support surface 24 and between the portions of the support surface 24 and the shim 12) results in mechanical attachment, The coating 16 is prevented from becoming separated or decoupled from the metal shim 12 (via the metal support structure 14).

  As described above, the portion of the coating 16 is a portion of the metal shim 12 and the portion of the support structure 14 that is spaced from the metal shim 12 (eg, not joined or fused to the metal shim 12, It may be located between a portion joined to or fused to the shim 12 or a portion connected to the portion). The portion of the coating 16 may also be located between the metal shim 12 and the portion of the support structure 14 that is joined or fused to the metal shim 12. As shown in FIGS. 1 and 5, for example, the portion of the fiber, member or support structure 14 that joins or fuses to the metal shim 12 is the portion of the fiber, member or support structure 14 and the support surface 24 of the shim 12. It may include or define a shape that provides or forms an interstitial space or void 26. In the exemplary embodiment illustrated in FIGS. 1, 4 and 5, the portion of the fiber, member or support structure 14 that is joined or fused to the support surface 24 of the shim 12 has a space or void 26 in each fiber, The cross section is substantially circular so that it is formed between the member or portion of the support structure 14 and the support surface 24 of the shim 12. Other configurations of the support structure 14 may be utilized that form such a space or gap 26 between the support surface or side 24 of the shim 12 and the support structure 14 (if joined). Thus, the shape or configuration of the fiber, member or portion of the support structure 14 allows the coating 16 to be between the mating portion of the support structure 14 and the seal surface or side 24 of the shim 12 (eg, generally from the seal surface 24). It can be allowed to be located in a direction that extends away or in a direction that extends substantially perpendicular to the sealing surface 24.

  FIG. 6 illustrates a cross-sectional view of an exemplary slot seal assembly 110 located within an exemplary seal slot for sealing exemplary connections between turbine components, such as stationary components. The exemplary slot seal assembly 110 is quite similar to the exemplary slot seal assembly 10 of FIGS. 1-5 above. As such, like reference numbers beginning with “1” are used to indicate like aspects or functions, and the above description directed to such aspects or functions (and alternative embodiments) is exemplary. The same applies to the new slot seal assembly 110. In particular, FIG. 6 is attached to the seal slot formed by the exemplary first turbine component 142, the adjacent exemplary second turbine component 144, and the first and second components 142, 144. 2 illustrates a cross-section of a portion of an exemplary turbomachine that includes an exemplary composite slot seal 110. The first and second turbine components 142, 144 may be first and second fixed components, for example, first and second nozzles of the first and second fixed components, respectively. In other embodiments, the first and second parts 142, 144 are any other adjacent turbomachine parts, such as fixed or translating and / or rotating (ie moving) turbine parts. Good. That is, the exemplary composite slot seals 10, 110 described herein may be configured for any number or type of turbomachine components that require a seal to reduce leakage between the components, Or it can be used with its turbomachinery parts.

  The cross-sections of the exemplary components 142, 144 and exemplary composite slot seal 110 illustrated in FIG. 6 are taken along the width of the structure, whereby the exemplary width and thickness / Indicates the height. It is noted that the relative width, thickness and cross-sectional shape of the structure illustrated in FIG. 6 are exemplary and the structure may include any other relative width, thickness and cross-sectional shape. . Further, the length of the structure (extending in and out of the page of FIG. 6) may be any length, and the shape and configuration of the structure in the longitudinal direction may be any shape or configuration. Also, although only two exemplary turbine components 142, 144 forming one seal slot are shown, it is also noted that multiple components may form multiple seal slots in communication with each other. Is done. For example, a plurality of turbine components may be arranged circumferentially so that the seal slots formed thereby are arranged circumferentially and communicate with each other. In such an embodiment, the slot seal 10, 110, 210 according to the present disclosure extends to a plurality of seal slots to seal a plurality of gaps or connections, thereby reducing leakage between a plurality of turbine components. May be configured.

  As shown in FIG. 6, the first and second adjacent turbine components 142, 144 can be spaced apart from each other so that the connection, gap or path 190 is first and second. Can spread between adjacent parts 142, 144, eg, fixed parts. Thereby, such a connection 190 can allow a flow, such as an air flow, between the first and second turbine components 142, 144. In some configurations, the first and second turbine components 142, 144 are between a first air stream 150, such as a cooling air stream, and a second air stream 160, such as a hot combustion air stream. May be located. The term “air flow” as used herein refers to any material or composition, or combination of materials or compositions, that is converted through a connection 190 between the first and second turbine components 142, 144. Note that it is used to describe the movement of

  In order to receive a seal that extends across the connection 190 and thereby seal or block the connection 190, the first and second adjacent parts 142, 144 may each include a slot as shown in FIG. is there. In the illustrated illustrated embodiment, the first part 142 includes a first seal slot 170 and the second part includes a second seal slot 180. The first and second seal slots 170, 180 may have any size, shape, or configuration capable of receiving a seal therein. For example, as shown in the exemplary embodiment illustrated in FIG. 6, the first and second seal slots 170, 180 are substantially similar to each other and located in a mirrored relationship, From inside the part 142, a net slot or cavity can be defined together that extends across the connection 190 and into the second part 144. Thus, the set of first and second seal slots 170, 180 together form a cavity or seal slot to support opposing portions of the seal so that the seal 110 is adjacent to the parts 142, 144. It is possible to pass through the connecting portion 190 that spreads between the two.

  In some arrangements where the first and second turbine components 142, 144 are adjacent, the first and second seal slots 170, 180 are substantially aligned (eg, mirrored or symmetrical). May be arranged in such a way that they are aligned with each other. However, due to manufacturing and assembly limitations and / or variations, as well as thermal expansion, motion, etc. during use, the first and second seal slots 170, 180 may be distorted, twisted, bent, or centered. May shift. In other scenarios, the first and second seal slots 170, 180 may be mirrored or remain in a symmetrical relationship, but the relative positioning of the first and second seal slots 170, 180 is May vary (eg from use, wear or operating conditions). The term “eccentric” is used herein to encompass any scenario where the seal slot has changed its relative position or orientation compared to the nominal or initial position or configuration.

  An off-center configuration (not shown) with respect to the exemplary first and second seal slots 170, 180 and exemplary seal 110 of the exemplary first and second turbine components 142, 144 of FIG. The exemplary seal 110 reveals the cause of misalignment and maintains sealing contact between the coating 116 and the first and second seal slots 170, 180 to provide first and second turbine components 142. It is preferable to be flexible in order to effectively block or remove the connection 190 that extends between 144 and thereby reduce or prevent the first and second airflows 150, 160 from interacting. More particularly, as shown in FIG. 6, the first and second airflows 150, 160 can interact with the connection 190, so that the first airflow 150 is the shim 112 of the seal 110. With a "drive" air flow that acts against the outer seal surface 122 of the first side and presses the coating 116 of the seal 110 against the first sides 135, 145 of the first and second seal slots 170, 180, respectively. is there. In such a scenario, the seal 110 (and / or coating 116) preferably has a first air flow to account for any misalignment between the first and second seal slots 170,180. It may be flexible enough to deform (eg, elastically) as a result of the force applied by 150 (eg, exceeding the force applied by the second air flow 160), It may be hard enough to resist being “folded” or “pushed”. That is, in such a scenario, the exemplary seal 110 can be sufficiently flexible, but the sealing force between the coating 116 of the shim 112 and the first side surfaces 135, 145 by the force of the first air flow 150. It is preferable that it is hard enough to maintain the consistency. For example, the metal shim 112, the metal support structure 114, and the coating 116 may be configured to accommodate irregularities on the seal slot contact surfaces 135, 145 during use of the turbine. In some such embodiments, the coating 116 may be a glass insulating coating having a transition temperature (Tg) that is similar to that of the operating temperature of the turbine / seal 110 so that the glass coating 116 is at the operating temperature. Be flexible or deformable to facilitate at least conformal deformation of the coating 116 to the first side surfaces 135, 145. As noted above, in addition to being sufficiently flexible (in all directions) to effectively seal the connection 190 in an off-center scenario, the exemplary seal 110 preferably includes assembly requirements. It may be hard enough to satisfy.

  The size of the seal 110 may be any size, but may depend on, or at least be related to, the parts 142, 144 on which the seal 110 is installed. The thickness T1 of the exemplary seal 110 may be less than the thickness T2 of the first and second seal slots 170, 180, thereby assembling the first and second adjacent parts 142, 144. In some cases, it may be less than the net slot thickness T2 formed by the first and second seal slots 170,180. In some embodiments, the exemplary seal 110 has a thickness T1 preferably in the range of about 0.01 inch to about 1/4 inch, more preferably about 0.05 inch to about 0.1 inch. Can be in range. Similarly, when the parts 142, 144 are installed adjacent to each other, the width W1 of the seal 110 is created by the first and second slots 170, 180 of the first and second parts 142, 144, respectively. Net slot width W2 and the gap 190 between the parts 142, 144 may be smaller. In some embodiments, the width W1 of the exemplary seal 110 may preferably be in the range of about 0.125 inches to about 0.75 inches.

  As shown in the embodiment illustrated in FIG. 6, for example, the seal 110 may be positioned and disposed within a seal slot (ie, the first and second seal slots 170, 180), so that the first One or cooling air flow 150 acts against the outer sealing surface 122 of the shim 112 to press the coating 116 against the first side surfaces 135, 145 of the first and second sealing slots 170, 180. Due to the impervious nature of the shim 112 and / or coating 116, the seal 110 thereby prevents the cooling air stream 150 from moving through the gap 190 into the second or hot combustion air stream 160. Further, the coating 116 protects the metal shim 112 from the high temperature of the combustion air stream 160. In this manner, the exterior or seal surface of the coating 116 of the seal 110 (eg, a surface that interacts with the exemplary first side surfaces 135, 145 or other of the exemplary first and second seal slots 170, 180). At least the shape and configuration of the seal surface) may be related to the shape and configuration of the slots 142, 144 in which the seal 110 is installed. That is, the shape and configuration of at least the exterior or seal surface of the coating 116 of the seal 110, such as contour, surface texture, etc., is a sealing engagement with the first and second seal slots 170, 180 in which the seal 110 is installed. May be configured to ensure. For example, in the illustrated example of FIG. 6, the outside or seal surface of the coating 116 of the seal 110 is between the seal assembly 110 and the first side surfaces 135, 145 of the first and second seal slots 170, 180, And finally to effectively prevent or reduce leakage of the first air stream 150 to the second or hot combustion air stream 160 (and also to remove the metal shim 12 from the high temperature of the hot combustion air stream 160. Can be substantially smooth and substantially planar to be substantially adjacent to the first side 135, 145 of the first and second sealing slots 170, 180, or Alternatively, it can substantially engage the first side surfaces 135, 145 of the substantially planar first and second seal slots 170, 180. In some alternative embodiments (not shown), at least the shape or configuration of the coating 116 of the seal 110 or the seal surface is configured so that the shape and configuration of the corresponding seal surfaces (e.g., FIG. 6 may be shaped or configured differently from the shape and configuration of the exemplary first side surfaces 135, 145, etc. of the first and second seal slots 170, 180 illustrated in FIG.

  FIG. 7 illustrates a cross-sectional view of another exemplary slot seal assembly 210 according to the present disclosure. The exemplary slot seal assembly 210 is substantially similar to the exemplary slot seal assemblies 10 and 110 of FIGS. 1-6 above. As such, like reference numerals beginning with “2” are used to indicate like aspects or functions, and the above description directed to such aspects or functions (and alternative embodiments) is exemplary. The same applies to the new slot seal assembly 210. As shown in FIG. 7, the slot seal assembly 210 differs from the seal assemblies 10 and 110 in that the seal 210 is symmetric in the thickness direction. Thus, the seal assembly 210 provides ease of installation or assembly of the seal 210 in the turbine seal slot, since the seal 210 does not need to be particularly correctly positioned in the thickness direction.

  As shown in FIG. 7, both sides of the seal surface 222 and the support surface 224 of the metal shim 12 include a metal support structure 214 joined thereto. In some embodiments (not shown), the support structure 214 may extend over one or more side edges of the metal shim 212 and over the seal surface 222 and the support surface 224. Similarly, both the support structure 214 joined to the sealing surface 222 of the metal shim 212 and the support structure 214 joined to the support surface 224 include a coating 216 applied thereon. In some embodiments (not shown), the coating 216 is bonded to one or more side edges of the metal shim 212 and to the support structure 214 and the support surface 224 bonded to the seal surface 222. May extend over / into the supported support structure 214. A coating 216 applied on or in the support structure 214 joined to the sealing surface or side 222 of the shim 210 may be applied to the shim 212 sealing surface side 22 (eg, from the cooling air flow 150 discussed above with respect to FIG. 6). ) Can be insulated or protected.

  The seal assembly disclosed herein provides a low leak rate similar to that possible with conventional slot seals, such as solid metal shim seals, while silicide formation when applied to modern hot turbomachinery. Eliminates increased concerns regarding oxidation, thermal creep and / or wear. Further, the seal assemblies disclosed herein may be less susceptible to manufacturing variations compared to existing seals. Thus, the seal assembly disclosed herein reduces leakage with low manufacturing and operational risks and is applicable to both OEM and retrofit applications.

  It should be understood that the above description is intended to be illustrative and not restrictive. Numerous modifications and changes may be made herein by those skilled in the art without departing from the general spirit and scope of the invention as defined by the following claims and their equivalents. For example, the above-described embodiments (and / or aspects thereof) may be used in combination with each other. Moreover, many modifications may be made to adapt a particular situation or material to the teachings of various embodiments without departing from the scope thereof. Although the dimensions and types of materials described herein are intended to define the parameters of the various embodiments, they are by no means limiting and are merely exemplary. Many other embodiments will be apparent to those of skill in the art upon reviewing the above description. The scope of the various embodiments should, therefore, be determined with reference to the appended claims, along with the full scope of equivalents to which such claims are entitled. In the appended claims, the terms “including” and “in which” are used as plain English equivalents of the terms “comprising” and “here”, respectively. used. Further, in the following claims, the terms “first”, “second”, “third” and the like are used merely as labels and do not impose numerical requirements on the object. Also, the term “operably connected” as used herein arises from both separate and separate parts that are directly or indirectly coupled, and integrally formed (ie, monolithic) parts. Connect. Further, the following claims limitations are not written in a means-plus-function format, and such claims limitations are "means for" along with descriptions of functions not including further structure. Is not intended to be construed under 35 USC 112, sixth paragraph, unless and unless explicitly used. It should be understood that not all such objectives or advantages described above may be achieved in accordance with any particular embodiment. Thus, for example, in a manner that achieves or optimizes one group of advantages or advantages taught herein without necessarily achieving other objectives or advantages as taught or suggested herein. Those skilled in the art will appreciate that the systems and techniques described herein may be embodied or implemented.

  Although the invention has been described in detail in connection with only a limited number of embodiments, it will be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but equivalent to the spirit and scope of the invention. Furthermore, while various embodiments of the invention have been described, it should be understood that aspects of the present disclosure include only a small portion of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.

  The description herein includes the best mode for disclosing the invention, and has been created, used, and incorporated into the apparatus or system to enable those skilled in the art to practice the invention. An example is used, including performing the method. The patentable scope of the invention is defined in the claims, and may include other examples that occur to those skilled in the art. Such other examples are those having structural elements that do not differ from the literal meaning of the claims, or equivalent structural elements that do not substantially differ from the literal meaning of the claims. If included, it is intended to be within the scope of the claims.

10 seal, slot seal assembly 12 shim, plate 14 support structure, layer 16 coating, coating layer 22 seal face, side face, support face 24 seal face, side face, support face 26 space, void 110 composite slot seal, slot seal assembly 112 Shim 114 Support structure 116 Coating 122 Sealing surface 135 Sealing slot contact surface, first side 142 First turbine part, first part, slot 144 Second turbine part, second part, slot 145 Sealing slot contact Surface, first side 150 first air flow, cooling air flow 160 second air flow, combustion air flow 170 first seal slot 180 second seal slot 190 gap, path 210 seal, slot seal assembly, Shim 212 Metal shim 214 Support structure 216 Coating 222 Side surface, seal surface 224 Support surface

Claims (23)

A seal assembly (10) for sealing a gap extending between said parts placed in a seal slot at least partially formed by adjacent turbomachine parts, said seal assembly (10) being ,
A metal shim (12) including a sealing surface (22) and a support surface (24);
A porous metal support structure (14) joined to the support surface (24) of the metal shim (12);
A ceramic, glass or enamel coating (16) extending over and within the porous metal support structure (14), wherein the coating (16) is on the support surface side (24) of the metal shim (12). And substantially covering the support structure (14),
A seal assembly (10), wherein a portion of the coating (16) is located between the support surface (24) of the metal shim (12) and a portion of the metal support structure (14).   The seal assembly (10) of claim 1, wherein the coating (16) is mechanically coupled to the metal shim (12) via the metal support structure (14). A portion of the coating (16) extends between the support surface (24) of the metal shim (12) and the metal support structure (14) in a direction that extends away from the support surface (24). Located in the seal assembly (10).   The seal assembly (10) according to claim 2, wherein the direction extending away from the support surface (24) is substantially perpendicular to the support surface (24).   The seal assembly (10) of claim 1, wherein the metal shim (12) is a substantially solid metal shim (12).   The seal assembly (10) of claim 1, wherein the coating (16) is chemically bonded to the support structure (14).   At least one of the support surface (24) and the metal support structure (14) of the metal shim (12) has a protective outer coating configured to prevent oxidation of the respective metal component. The seal assembly (10) of claim 1, wherein the seal assembly (10) is included.   The seal assembly (10) of claim 1, wherein the metallic support structure (14) is diffusion bonded to the metallic shim (12) by at least one brazing.   The seal assembly (10) of claim 1, wherein the metallic support structure (14) is a mesh structure.   The metal support structure (14) in which the coating (16) portion is joined to the support surface (24) of the metal shim (12) and the support surface (24) of the metal shim (12). The seal assembly (10) according to claim 1, which is located between the two parts.   The metal support structure in which the portion of the coating (16) is not joined to the support surface (24) of the metal shim (12) and the support surface (24) of the metal shim (12) 14. The seal assembly (10) according to claim 1, which is located between the part (14).   The portion of the metal support structure (14) not joined to the support surface (24) of the metal shim (12) is joined to the support surface (24) of the metal shim (12). The seal assembly (10) of claim 10, wherein the seal assembly (10) extends from or is connected to a portion of the metallic support structure (14).   The seal assembly (10) of claim 1, wherein the coating (16) is joined to at least one of the support surface (24) and the support structure (14) of the shim (12). A second porous metal support structure (214) joined to the sealing surface (222) of the shim (212);
A second ceramic, glass or enamel coating (216) extending over and within the second porous metal support structure (214), so that the second coating (216) is Substantially covering the sealing surface side (222) of the metal shim (12) and the second support structure (214);
The portion of the second coating (216) is located between the sealing surface (222) of the metal shim (212) and the portion of the second metal support structure (214). The seal assembly (210) described. A method of forming a seal assembly (10) for use in a seal slot at least partially formed by adjacent turbomachine components to seal a gap extending between the components, the method comprising: ,
Joining at least a portion of the porous metal support structure (14) and the metal shim (12);
A ceramic, glass or enamel coating material (16) is applied to the porous metal support structure (14) so that the coating material is supported on the support surface side (24) of the metal shim (12) and Covering the support structure (14) and including a portion located between the support surface (24) of the metal shim (12) and a portion of the metal support structure (14);
Increasing the density of the ceramic, glass or enamel coating material (16) to form a ceramic, glass or enamel coating mechanically secured to the metal shim (12) by the metal support structure (14); Including a method.   At least a part of the metal support structure (14) and the metal shim (12) are joined to at least a part of the metal support structure (14) and the support surface (24) of the metal shim (12). The method of claim 14, comprising diffusion bonding with the support surface (24).   Applying a ceramic, glass or enamel coating material (16) to the porous metal support structure (14) comprises applying a high viscosity castable ceramic composition by screen printing or wiping with a towel. Item 15. The method according to Item 14.   The method further comprises removing a portion of the ceramic composition applied to the support structure (14) with a doctor blade, wherein increasing the density of the ceramic composition cures and heat treats the applied ceramic composition. The method of claim 16, comprising:   Applying a ceramic, glass or enamel coating material (16) to the porous metal support structure (14) may apply a paintable glass or enamel composition by painting, dip coating or spray coating. 15. The method of claim 14, comprising:   The method of claim 18, wherein increasing the density of the glass or enamel composition comprises drying and heat treating the applied glass or enamel composition. A first turbine component (142) and a second turbine component (144) adjacent to the first turbine component (142), wherein the first and second turbine components (142, 144) are First and second turbine components (142, 144) forming at least a portion of a seal slot extending into a gap between the turbine components (142, 144);
A turbomachine comprising: a seal located in the seal slot of the first and second turbine components (142, 144) and extending into the gap therebetween;
A metal shim (12) including a sealing surface (22) and a support surface (24);
A porous metal support structure (14) joined to the support surface (24) of the metal shim (12);
A ceramic, glass or enamel coating (16) applied on and within the metal support structure (14), so that the coating (16) is on the support surface side of the metal shim (12) (24) and the support structure (14) substantially, wherein the portion of the coating is between the support surface (24) of the metal shim (12) and the portion of the metal support structure (14). Located in the turbomachinery.   The seal wherein the ceramic, glass or enamel coating (16) of the seal (10) is collectively formed by a first side of the first turbine part and a first side of the second turbine part. The turbomachine according to claim 20, wherein the turbomachine is located on a first side of the slot.   The turbomachine according to claim 20, wherein the metallic shim (12) is a substantially solid metallic shim (12) and the porous metallic support structure (14) is a metallic mesh structure.   The support surface (24) of the metal shim (12) and the metal support structure (14) in a direction in which a portion of the coating (16) extends substantially perpendicular to the support surface (24). The turbomachine according to claim 20, wherein the turbomachine is mechanically connected between the coating (16) and the metal shim (12) via the metal support structure (14), between the metal support structure (14) and the metal shim (12). .