JP6990967B2 - Composite seal for turbomachinery - Google Patents

Description

The present invention relates to seals generally designed to reduce leakage, more particularly seals configured to work within a seal slot to reduce leakage between adjacent fixed components of a turbomachine.

Leakage of hot combustion gas and / or cooling flow between turbomachinery components generally reduces power output and reduces efficiency. Hot combustion gas may be contained inside the turbine, for example by bringing pressurized compressor air around the hot gas path. In general, high-pressure cooling flows leaking into the hot gas path between adjacent turbine parts (such as fixed shrouds, nozzles and diaphragms, inner shell casing parts, and rotor parts) reduce efficiency and create an environment free of such leaks. In comparison, higher combustion temperatures and lower engine gas turbine efficiencies are required to maintain the desired power levels. In this way, turbine efficiency can be improved by reducing or eliminating leaks between turbine components.

Traditionally, leaks between turbine component connections are treated with metal seals located within seal slots formed between turbine components, such as fixed components. Seal slots typically extend to the connections between the components, and metal seals located therein block or prevent leakage from the connections. However, preventing leakage between turbine component connections with metal slot seals located in the turbine component seal slots is complicated by the fact that modern turbomachinery produces relatively high temperatures. In the sealed slot by introducing new materials that allow the turbine to operate at higher temperatures (eg, above 1,500 ° C) compared to traditional turbines, such as ceramic matrix composite (CMC) turbine components. Traditional metal turbine slot seals for use may not be suitable.

Preventing leakage between turbine component connections with metal seals means that the turbine component seal slots are formed by the corresponding slot portions of adjacent components (the seals located within it are thereby the connections between the components. It is further complicated by the fact that it spreads over). Misalignment between these adjacent parts (eg, resulting from thermal expansion, manufacturing, assembly and / or installation restrictions, etc.) is an uneven seal whose configuration, shape and / or size can vary over time. Generate a slot contact surface. If the seal does not bend, deform, or cause such irregularities, such irregularities on the seal slot contact surface allow leakage throughout the slot seal located within the seal slot. Unfortunately, many conventional metal shims that cause such uneven seal slot contact surfaces due to misalignment of adjacent turbine components can withstand elevated turbine operating temperatures well. It may not be possible.

Therefore, a composite turbomachinery component connection seal configured for use in a typical turbine seal slot, which withstands the gradually increasing operating temperature of the turbine and adapts to the unevenness of the seal slot contact surface, would be desirable.

U.S. Patent Application Publication No. 2013/0134678

In a first aspect, the present disclosure provides a seal assembly for placement in a seal slot formed at least partially by adjacent turbomachinery components to seal widening gaps between the components. Seal assemblies include metal shims, porous metal support structures, and ceramic, glass or enamel coatings. Metal shims include a sealing surface and a supporting surface. The porous metal support structure is joined to the support surface of the metal shim. The ceramic, glass or enamel coating extends above and inside the porous metal support structure so 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 is a metal shim support surface and metal that extends away from the support surface in order to mechanically connect the coating to the metal shim via a metal support structure. It may be located between the parts of the support structure. In such an embodiment, 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, the support surface of the metal shim and at least one of the metal support structures may include a protective outer coating configured to prevent oxidation of the respective metal component. 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 an embodiment, the portion of the metal support structure that is not joined to the support surface of the metal shim extends or extends from the portion of the metal support structure that is joined to the support surface of the metal shim. May be linked with.

In some embodiments, the coating may be attached to at least one of the support surfaces of the shim and support structure. In some embodiments, the seal assembly has a second porous surface joined to the seal surface of the shim so that the second coating substantially covers the sealing surface side of the metal shim and the second support structure. It may further include a metallic metal support structure, as well as a second ceramic, glass or enamel coating that extends above and inside the second porous metal support structure, the portion of the second coating being a metal shim. May be located between the sealing surface of the enamel 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 within a seal slot formed at least partially by adjacent turbomachinery components to seal widening gaps between the components. do. The method involves joining at least a portion of the porous metal support structure to a metal shim. This method further includes applying a ceramic, glass or enamel coating material to the porous metal support structure so that the coating material covers the support surface side of the metal shim and the surface of the support structure, the metal. Includes a portion located between the support surface of the shim and the portion of the metal support structure. 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 a metal shim via a metal support structure.

In some embodiments, joining at least a portion of the metal support structure to the support surface of the metal shim comprises diffusing joining at least a portion of the metal support structure to the support surface of the metal shim. It's okay. In some embodiments, applying a ceramic, glass or enamel coating material to a porous metal support structure may include applying a high viscosity castable ceramic composition by screen printing or wiping with a towel. be. In such embodiments, the method may further include removing a portion of the ceramic composition applied to the support structure via a doctor blade, in which the density of the ceramic composition may be increased. Includes curing and heat treatment of the applied ceramic composition. In some embodiments, applying a ceramic, glass or enamel coating material to a porous metal support structure applies a glass or enamel-based composition in a form that can be painted by painting, dip coating or spray coating. May include things. In such embodiments, increasing the density of the glass or enamel-based composition may include drying and heat treating the coated glass or enamel-based composition.

In another aspect, the present disclosure provides a turbomachine containing a first turbine component and a second turbine component adjacent to the first turbine component, the first and second turbine components being between the turbine components. Form at least a portion of the seal slot that extends into the gap. The turbomachinery is located within the seal slots of the first and second turbine parts and further includes a seal that extends into their gaps. Seals include metal shims, porous metal support structures, and ceramic, glass or enamel coatings. Metal shims include a sealing surface and a supporting surface. The porous metal support structure is joined to the support surface of the metal shim. Ceramic, glass or enamel coatings are such that the coating substantially covers the support surface side and support structure of the metal shim, and the part of the coating is between the support surface of the metal shim and the part of the metal support structure. It is applied on and inside the metal support structure so that it is located.

In some embodiments, the ceramic, glass or enamel coating on the seal is the first of the seal slots collectively formed by the first side surface of the first turbine component and the first side surface of the second turbine component. It may be positioned with respect to the side surface of 1. 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 is of a metal shim that extends substantially perpendicular to the support surface in order to mechanically connect the coating to the metal shim via a metal support structure. It may be located between the support surface and a portion of the metal support structure.

These and other purposes, features, and advantages of the present disclosure, together with the accompanying drawings, will become apparent from the following detailed description of the various aspects of the present disclosure.

It is a figure which shows the sectional view of the part of the 1st exemplary slot seal assembly by this disclosure. FIG. 3 shows a perspective view of an exemplary slot seal of FIG. 1, partially assembled to illustrate the placement of shims, support structures and coating portions. It is a figure which shows the perspective view of the shim of the exemplary slot seal of FIG. 1 and the partial assembly of the support structure. It is a figure which shows the enlarged perspective view of the part of the partial assembly of the shim and the support structure of FIG. It is a figure which shows the enlarged sectional view of the part of the partial assembly of the shim and the support structure of FIG. It is a figure which shows the side sectional view of the exemplary slot seal assembly located in the seal slot for sealing the exemplary connection between turbine components. It is a figure which shows the side 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 invention, the articles "one (a)", "one (an)", "this (the)", and "above" have one or more elements. It means that there is more than that. The terms "comprising," "inclusion," and "having" mean to include, meaning that there may be additional elements beyond those listed. None of the examples of operating parameters exclude other parameters of the disclosed embodiments. Parts, embodiments, features, configurations, arrangements, uses and the like described, exemplified or disclosed herein with respect to specific seal embodiments are in any other seal embodiment disclosed herein. It may be applied in the same way.

According to the present disclosure, composite turbomachinery component connection seals configured for use in turbine seal slots (eg, composite turbine slot seals), as well as methods of manufacture and use thereof, are used for relatively high operation of turbines, including CMC components. 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 interactions between the metal parts of the composite slot seal and the hot gas flow / leakage and / or the seal slot itself and substantially limit the thermal interaction. Has been done. As such, the composite slot seals provided herein allow for use in high temperature turbine applications. In addition to high temperature operation, the composite slot seals of the present disclosure are configured to adapt to irregularities on the seal slot contact surface to reduce leakage due to misalignment and / or roughness of the seal slot surface. ..

As shown in FIGS. 1-5, the exemplary seal 10 is a seal comprising 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 each other. It can be an assembly. The shim 12 can be effective in substantially preventing the passage of substances through it. For example, the shim 12 can be substantially solid or substantially impermeable to at least one of gas, liquid and solid at the pressure and temperature generated in a turbomachine. However, the shim 12 can also provide flexibility in the pressure and temperature that occurs in turbomachinery to accommodate distortions or biases in the direction of thickness T1 at the slot surface. In one embodiment, the shim 12 is a metal member, such as a substantially solid plate. In some such embodiments, the shim 12 can be a hot metal alloy or a superalloy. For example, in some embodiments, the shim 12 (and / or support structure 14) is made from stainless steel or a nickel-based alloy (at least a portion), such as Haynes214, which is a nickel molybdenum chromium alloy, or Haynes214 with an aluminum oxide coating. May be done. In some embodiments, the shim 12 may be made of 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 of 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 surface 22 of the shim 12 substantially facing the support structure 14 may be substantially flat (neutral). As further described below, the outer sealing surface 22 of the shim 12 is a cooling pressure flowing through at least one gap or seam between at least one gap or seam forming (at least a portion) a sealing slot. It may be configured to engage or interact with the air flow, whereby the seal 10 is pushed or pressed against the sealing surface of the first and second parts of the seal slot, gas, liquid and /. Or substantially prevent solids from moving through gaps or seams. Thus, at least one of the shims 12 and the coating 16 (or the shims 12 and the coating 16 acting together) is substantially impermeable to liquids, gases and / or solids at the pressures experienced in turbomachinery and thus seals. 10 results in at least a low leakage rate through the seal slot.

As shown in FIGS. 1-5, the support structure 14 can be connected to the support surface or side surface 24 of the shim 12 that is substantially opposed to the seal surface 22. In some embodiments, the support structure 14 may be a metal, eg, a metal material having the above characteristics with respect to the shim 12. The shim 12 and the support structure 14 may be made of the same or substantially the same metal material, thereby comprising the same or substantially the same coefficient of thermal expansion (CTE). However, the shim 12 and the support structure 14 do not need to be made of the same or substantially similar materials, nor do they need to contain the same or substantially the same degree of CTE. However, the shims 12 and the support structure 14 either break or break the diffusion junction between them, or the seals in use in turbomachinery, as further explained below. It is preferable that it is configured so as not to be invalidated between them by the repeated heat load of 10. Therefore, the CTE of the shim 12 and the CTE of the support structure 14 may differ only to the extent that the diffusion bond between the shim 12 and the support structure 14 is not negated by the repeated heat load of the seal 10 in use in the turbomachinery. .. 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 such that when the seal 10 is used in the seal slot of the turbine. The diffusion junctions between them may be configured so that they will not be damaged or invalidated when repeatedly subjected to thermal loading.

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 mechanically bonded by the coating 16 (chemically bonded to the shim 12). It may be a support structure, member or assembly that can be connected or adhered to. In this way, the coating 16 can be firmly 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), including cavities or voids in which the portion of the coating 16 is held. It's okay. The term "porous" means that, with respect to the support structure 14, the coating 16 spreads individually and / or collectively 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. Allowable 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, of the shim 12. Used herein to describe a structure comprising pores, grooves, voids, gaps, cavities or other interior spaces located substantially perpendicular to the sealing surface 24, one or more members or mechanisms. Will be done. In some embodiments, the support structure 14 is a porous metal mesh, lattice, honeycomb or braided with interlocking, woven or interlaced members, fibers or moieties, as shown in FIGS. 1-5. It may be of any kind of structure.

As shown in FIGS. 1-5, at least some portion of the support structure 14 (eg, a metal mesh member or fiber portion) may be fused or joined to the support surface 24 of the shim 12. However, in some embodiments, the rest of the support structure 14 may be spaced from the support surface 24 of the shim 12 at regular intervals (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 neither joined nor fused to the shim 12. Potentially, support surfaces 24 of shims 12 that are spaced at regular intervals may be included. Thus, only a fragment or portion of the support structure 14 may be joined or fused with the shim 12, and the remaining fragment or portion of the support structure 14 may be joined or fused to the joined or fused portion (eg, mechanically). It extends from the part that is attached) or joined or fused.

At least a portion of the shim 12 and the support structure 14 may be joined or fused to each other so that they can substantially withstand the temperature, pressure and other conditions that the seal slot of the turbine receives due to their adhesion. For example, at least a portion of the shim 12 and the support structure 14 may be bonded or fused in such a way that a solid chemical bond is formed between them. In some embodiments, at least a portion of the shim 12 and the support structure 14 may be in a solid state welded to each other (eg, through diffusion bonding). In some embodiments, the shim 12 and the support structure 14 may be diffusely bonded to each other by at least one hot braze.

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 above its outer surface. For example, at least a portion of the outer surface of the shim 12, such as the sealing surface 22 or the support surface 24, and / or at least a portion of the outer surface of the support structure 14 may include at least one protective coating or layer. That is, at least a portion of the outer surface of the shim 12 (eg, the support surface 24) and / or the support structure 14 is provided with a protective coating overlaid on the underlying metal component (ie, the metal shim 12 or the metal support structure 14). May be defined. Thus, one or more portions of the shims 12 and / or support structures 14 diffusely bonded to each other may include a protective coating or layer. For example, the support structure 14 may be superposed on the shim 12 and bonded to a protective coating forming the support surface 24. The protective coating of the metal shim 12 and / or the metal support structure 14 may be configured to substantially prevent or delay the oxidation of the underlying metal component. In some embodiments, one or more protective coatings of the metal shim 12 and / or the metal support structure 14 may or may contain oxides such as chromium or alumina oxides. ..

At least one coating 16 may be applied to the seal 10 to protect the shim 12 and the support structure 14 using at least a portion of the shim 12 and the support structure 14 bonded or fused together. As shown in FIGS. 1 and 2, the coating 16 is such that the coating substantially covers or overlaps at least the support surface 24 of the support structure 14 and the shim 12 (ie, the coating supports the seal 10). It may be applied to the seal 10 (so that it extends above and within the structure 14 and thereby 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 is also such that the sealing surface 22 side of the seal 10 is the only side or edge of the seal 10 that is not covered by the coating 16 or does not contain the coating 16. It may cover or overlap the support surface 24 side and side edges.

The coating 16 is at least a metal shim 12 (and potentially a support structure 14) when the seal 10 is used in a turbine seal slot, such as a seal slot formed of a part of a high temperature gas turbine, such as a fixed part. ) May be one or more coating materials that are effective in substantially preventing chemical interactions and substantially limiting thermal interactions. As further described below, the coating 16 on the support structure 14 is configured to hermetically engage the first and second sealing surfaces of the first and second components forming the seal slot. And can substantially prevent gas, liquid and / or solids from moving through gaps or seams between the first and second components. Thus, the coating 16 of silicide formation, oxidation, thermal creep and / or at least a metal shim 12 (and potentially support structure 14) during the use of the seal 10 in the seal slot of such a turbine. It can be effective in substantially preventing wear. That is, the coating 16 allows a metal-based seal, eg, a seal 10 containing one or more metallic shims 12 (and potentially a support structure 14), to be used in high temperature gas turbine applications. In some embodiments, the coating 16 is effective in protecting at least the metal shim 12 and / or the support structure 14 (eg, preventing or reducing oxidation, silicide formation, thermal creep, wear, etc.). Ceramic, glass or enamel material.

In some embodiments, the coating 16 may be formed of a crystalline, vitreous or glass-ceramic composite. In such embodiments, the coating 16 may include metal oxides, nitrides or oxynitrides. For example, the coating 16 may include stabilized or unstabilized zirconia, alumina, titania, alkaline earth and / or rare earth zirconate, titanate, aluminate, tantalate and niobate, Intermetal compounds such as tungstate, molybdenate, 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 enamel composition. For example, the coating 16 may include alkaline / alkaline earth aluminum noborophosphorosilicate glass and fillers. The coating 16 (whether ceramic, glass or enamel material) contains the high temperature meltability and fluidity required to provide optimum stability and compliance under 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 by reaction with the metal shim 12 (and / or the metal support structure 14), one or more metal silicates and / or at least one oxide layer can be applied to 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). One or more metal silicides formed by diffusion / reaction of selected species and metal shims 12 (and / or metal support structures 14) may be resistant to oxidation. One or more oxide layers formed by diffusion / reaction of selected species and metal shims 12 (and / or metal support structures 14) may contain negligible oxygen diffusion capacity through it. Yes, and thus protect the metal shim 12 (and / or the metal support structure 14). For example, Si can be utilized to diffuse into the metal shim 12 (and / or the metal support structure 14) and / or react with the metal shim 12 (and / or the metal support structure 14). be. In some embodiments, Al, Si, B, alloys thereof, or combinations thereof are used as the species selected to form one or more metal silicides and / or at least one oxide layer. Can be mentioned. In some embodiments, the metal shim 12 (and / or the metal support structure 14) may or may be formed of refractory metals such as Mo, W, alloys thereof, or combinations thereof. The refractory metal shim 12 (and / or 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 at least one oxide layer are at elevated temperature with a packed layer of selected species (eg, powder or similar form) and a metal shim 12 (eg, powder or similar form). And / or may be formed by the reaction of a metal support structure 14) (ie, pack siliciding / oxide layer method). In other embodiments, the one or more metal silicates and / or at least one oxide layer on the metal shim 12 (and / or the metal support structure 14) is vapor-deposited (eg, chemical vapor-deposited). It may be formed by one or more coatings of selected species (eg, metal elements / alloys) by (CVD) or physical vapor deposition (PVD)) followed by chemical and / or heat treatment.

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

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

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

As mentioned above, is the coating 16 chemically bonded at least first 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 that they are directly linked. Also, as mentioned above, the metal shim 12 and / or the metal support structure 14 may include a protective coating. In such embodiments, the coating 16 may be chemically bonded to the protective coating (thus indirectly chemically bonded to the metal shim 12 and / or the metal support structure 14).

The coating 16 substantially fills the voids in the support structure 14, including any space between the support structure 14 and the shim 12, as further described below, on the top or outer surface of the support structure 14. It can extend upwards (thus covering the support surface 22 of the shim 12). As further described 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, which is effective in thermally and chemically insulating the metal shim 12, is at least first chemically bonded to the metal shim 12 and the metal support structure 14 and mechanically. May be fixed.

The support structure 14 is placed on top of the metal shim 12, eg, a turbine seal, so that the coating 16 provides continuous or reliable protection to at least the metal shim 12 (and potentially the metal support structure 14). It may be effective in maintaining 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 of the seal 10 in the slot. For example, a chemical bond or coupling between a ceramic or glass coating 16 and a metal shim 12 and a metal support structure 14 (or a protective coating on it) may be a ceramic or glass coating 16 and a metal shim 12 and a metal. Due to the thermal inconsistency with the support structure 14, it may not withstand the thermal cycle of the shim 12 (eg, which occurs during use of the shim 12). As shown in FIGS. 1 and 2 and described above, the metal support structure 14 may be joined or fused with the metal shim 12, and the coating 16 may be at least over the voids of the support structure 14 or inside the voids. May be provided to. However, more specifically, the coating 16 also spreads or is located, at least in part, in a direction that extends away from the sealing surface 22 of the shim 12, at least in general, between the shim 12 and the portion of the support structure 14. Sometimes. In some embodiments, the coating 16 is substantially relative to the support surface 24 of the shim 12, at least in part, between the shim 12 and a portion (or portion thereof) of the individual member, fiber or support structure 14. It may be located in a direction that extends vertically. Thereby, the coating 16 is provided or spread substantially around a portion of the fiber, member or support structure 14 (except for that portion fused or bonded to the shim 12). Thus, at least a portion of the fiber, member or support structure 14 is joined or fused to the metal shim 12 and the portion of the coating 16 is located between the shim 12 and the portion of the support structure 14. The support structure 14 results in mechanical attachment of the coating 16 to the metal shim 12 which prevents the coating 16 from separating or decoupling from the shim 12. For example, if the chemical bond between the coating 16 and the metal shim 12 and / or the metal support structure 14 (or the protective coating on it) fails due to a thermal mismatch between them, the fiber, member. Alternatively, placing the coating 16 substantially around the portion of the support structure 14 (eg, above the outer surface of the support surface 24 and between the support surface 24 and the shim 12) results in mechanical adhesion, which results in mechanical adhesion. Prevents the coating 16 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 support structure 14 (eg, not joined or fused to the metal shim 12 but made of metal) which is spaced at regular intervals between the metal shim 12 and the metal shim 12. It may be located between a portion extending from or connected to a portion joined or fused to the shim 12). The portion of the coating 16 may also be located between the metal shim 12 and the portion of the support structure 14 bonded 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 bonded or fused to the metal shim 12 comprises the portion of the fiber, member or support structure 14 and the support surface 24 of the shim 12. May include or define shapes that provide or form intervening spaces or voids 26. In the exemplary embodiments illustrated in FIGS. 1, 4 and 5, the portion of the fiber, member or support structure 14 bonded or fused to the support surface 24 of the shim 12 has space or voids 26, respectively. The cross section is substantially circular so that it is formed between the portion of the member or support structure 14 and the support surface 24 of the shim 12. A support structure 14 of any other configuration may be utilized that forms such a space or void 26 between the support surface or side surface 24 of the shim 12 and the support structure 14 (if joined). Thus, the shape or composition of the portion of the fiber, member or support structure 14 is such that the coating 16 is placed between the joint portion of the support structure 14 and the sealing surface or side surface 24 of the shim 12 (eg, generally from the sealing surface 24). It can be allowed to be located in a direction that spreads away or 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 parts, such as fixed parts. The exemplary slot seal assembly 110 is fairly similar to the exemplary slot seal assembly 10 of FIGS. 1-5 above. As such, similar reference numbers beginning with "1" are used to indicate similar embodiments or functions, and the above description directed to such embodiments or functions (and alternative embodiments) is exemplary. The same applies equally to the slot seal assembly 110. In particular, FIG. 6 is mounted in a sealed slot formed by an exemplary first turbine component 142, an adjacent exemplary second turbine component 144, and first and second components 142 and 144. FIG. 3 shows a cross section of a portion of an exemplary turbomachinery, including an exemplary composite slot seal 110. The first and second turbine parts 142 and 144 may be the first and second nozzles of the first and second fixing parts, eg, the first and second fixing parts, respectively. In other embodiments, the first and second parts 142, 144 are any other adjacent turbomachinery parts, such as fixed or converted and / or rotating (ie, moving) turbine parts. good. That is, the exemplary composite slot seals 10, 110 described herein are configured for any number or type of turbomachinery components that require sealing to reduce leakage between components. Or it can be used with its turbomachinery parts.

The cross sections of the exemplary parts 142, 144 and the exemplary composite slot seal 110 exemplified in FIG. 6 are taken along the width of the structure, thereby the exemplary width and thickness of the structure /. Indicates the height. It is noted that the relative width, thickness and cross-sectional shape of the structure exemplified in FIG. 6 is 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 composition of the structure in the length direction may be any shape or composition. Also note that although only two exemplary turbine parts 142 and 144 forming one seal slot are shown, multiple parts may form multiple seal slots communicating with each other. Will be done. For example, a plurality of turbine components may be arranged in the circumferential direction, and as a result, the seal slots formed thereby may also be arranged in the circumferential direction and communicate with each other. In such embodiments, the slot seals 10, 110, 210 according to the present disclosure are such that they extend across a plurality of seal slots to seal a plurality of gaps or connections, thereby reducing leakage between the plurality of turbine components. May be configured.

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

The first and second adjacent parts 142 and 144, respectively, may include a slot as shown in FIG. 6 in order to receive a seal extending over the connection 190 and thereby seal or block the connection 190. be. In an exemplary illustrated embodiment, the first component 142 comprises a first seal slot 170 and the second component comprises a second seal slot 180. The first and second seal slots 170, 180 may have any size, shape, or configuration in which the seal can be received. 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 are located in a mirrored relationship with the first. From the inside of the part 142, a net slot or cavity extending across the connection 190 and into the second part 144 can be defined together. Thus, the pair of first and second seal slots 170, 180 together form a cavity or seal slot to support the opposing portions of the seal, so that the seal 110 is an adjacent component 142, 144. It is possible to pass through the connection portion 190 extending between the two.

In some arrangements where the first and second turbine parts 142 and 144 are adjacent, the first and second seal slots 170, 180 are substantially aligned (eg, mirrored or symmetrical). It may be configured to align with each other. However, due to manufacturing and assembly limitations and / or fluctuations, as well as thermal expansion, movement, etc. during use, the first and second seal slots 170, 180 may be distorted, twisted, bent or hearted. May shift. In other scenarios, the first and second seal slots 170, 180 may be mirrored or remain symmetrical, but the relative positioning of the first and second seal slots 170, 180 is. May change (eg from use, wear or operating conditions). The term "misaligned" is used herein to include any scenario in which the seal slot has changed its relative position or orientation relative to its nominal or initial position or configuration.

Displaced configurations (not shown) with respect to exemplary first and second seal slots 170, 180 and exemplary seal 110 of exemplary first and second turbine components 142, 144 of FIG. In, 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, with the first and second turbine components 142. It is preferred to be flexible in order to effectively block or remove the connection 190 extending between 144, thereby reducing or preventing the interaction of the first and second airflows 150, 160. 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 "driving" air flow that acts on the outer sealing surface 122 and presses the coating 116 of the seal 110 against each of the first sides 135, 145 of the first and second sealing slots 170, 180. be. In such a scenario, the seal 110 (and / or coating 116) preferably has a first air flow to clarify the cause of 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 the 150 (eg, greater than the force applied by the second airflow 160), but the connection 190 is "" It may be hard enough to resist being "folded" or "pushed". That is, in such a scenario, the exemplary seal 110 may be flexible enough, but the force of the first airflow 150 is responsible for sealing the coating 116 of the shim 112 with the first sides 135 and 145. It is preferable that it is hard enough to maintain the condition. For example, the metal shim 112, the metal support structure 114, and the coating 116 may be configured to adapt to the irregularities on the seal slot contact surfaces 135 and 145 during use of the turbine. In some such embodiments, the coating 116 may be a glass insulating coating having a transition temperature (Tg) similar to that of the operating temperature of the turbine / seal 110, so that the glass coating 116 is at the operating temperature. It becomes flexible or deformable, facilitating contoured deformation of at least the first side surface 135, 145 of the coating 116. As mentioned above, in addition to being flexible enough (in all directions) to effectively seal the connection 190 in a misalignment scenario, the exemplary seal 110 is preferably an assembly requirement. It may be hard enough to meet.

The size of the seal 110 may be of any size, but may depend on, or at least be related to, the parts 142 and 144 in which the seal 110 is installed. The thickness T1 of the exemplary seal 110 may be smaller than the thickness T2 of the first and second seal slots 170, 180, thereby assembling the first and second adjacent parts 142 and 144. In some cases, it may be smaller than the net slot thickness T2 formed by the first and second seal slots 170, 180. In some embodiments, the thickness T1 of the exemplary seal 110 is preferably in the range of about 0.01 inches to about 1/4 inch, more preferably about 0.05 inches to about 0.1 inches. It can be within range. Similarly, when the parts 142 and 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 and 144, respectively. It may be smaller than the net slot width W2 and the gap 190 between the parts 142 and 144. 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 embodiments exemplified in FIG. 6, for example, the seal 110 may be positioned and arranged in the seal slots (ie, first and second seal slots 170, 180), and as a result, the first. The 1 or cooling air flow 150 acts on 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 impermeable nature of the shims 112 and / or the coating 116, the seal 110 thereby prevents the cooling airflow 150 from moving through the gap 190 into the second or hot combustion airflow 160. In addition, the coating 116 protects the metal shim 112 from the high temperatures of the combustion airflow 160. Thus, the outside of the coating 116 of the seal 110 or the sealing surface (eg, the surface interacting with the exemplary first side surface 135, 145 or the other of the exemplary first and second sealing slots 170, 180). At least the shape and configuration of the seal surface) may be related to the shape and configuration of slots 142 and 144 in which the seal 110 is installed. That is, at least the outside or the shape and configuration of the sealing surface of the coating 116 of the seal 110, such as contours, surface textures, etc., is sealed 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 sealing surface of the coating 116 of the seal 110 is between the seal assembly 110 and the first sides 135, 145 of the first and second seal slots 170, 180. And finally to effectively prevent or reduce the leakage of the first airflow 150 to the second or hot combustion airflow 160 (and also to remove the metal shim 12 from the high temperature of the hot combustion airflow 160). Can it be flat to be substantially smooth and substantially adjacent to the first sides 135, 145 of the first and second seal slots 170, 180, which are substantially smooth and substantially flat (to protect)? Alternatively, it can be substantially engaged with the first side surfaces 135, 145 of the first and second seal slots 170, 180 which are substantially flat. In some alternative embodiments (not shown), at least the shape and configuration of the outer or sealing surface of the coating 116 of the seal 110 is the corresponding sealing surface of the first and second seal slots 170, 180 (eg, 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, exemplified in 6.

FIG. 7 shows 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, similar reference numbers beginning with "2" are used to indicate similar embodiments or functions, and the above description directed to such embodiments or functions (and alternative embodiments) is exemplary. The same applies equally to the 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 symmetrical in the thickness direction. Therefore, the seal assembly 210 provides ease of installation or assembly of the seal 210 in the turbine seal slot, as the seal 210 does not need to be placed in a particularly correct position in the thickness direction.

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

The seal assemblies disclosed herein provide a low leakage rate similar to the leakage rate possible with conventional slot seals, such as solid metal shim seals, while silicide formation when applied to modern high temperature turbomachinery. Eliminates increased concerns about oxidation, thermal creep and / or wear. In addition, the seal assemblies disclosed herein may be less susceptible to manufacturing variability as compared to existing seals. Accordingly, the seal assemblies disclosed herein reduce leakage with low manufacturing and operational risk and are applicable to both OEM and retrofit applications.

It should be understood that the above description is for illustrative purposes only and not for limiting purposes. Numerous modifications and modifications may be made herein by one of ordinary skill 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 embodiments (and / or embodiments thereof) may be used in combination with each other. Moreover, many modifications can be made to adapt a particular situation or material to the teachings of various embodiments without departing from its scope. The dimensions and types of materials described herein are for defining parameters of various embodiments, but they are by no means limiting, but merely exemplary. Many other embodiments will be apparent to those of skill in the art by reviewing the above description. Therefore, the scope of the various embodiments should be determined by reference to the appended claims, along with the full scope of the equivalents entitled by such claims. In the appended claims, the terms "include" and "here" are used as plain English equivalents of the terms "comprising" and "herein," 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" arises herein from both separate, directly or indirectly connected, separate parts and integrally formed (ie, monolithic) parts. Point to the connection. Furthermore, the following claims limitation is not written in a means-plus-function format, and such claims limitation is "means for" with a description of the function without further structure. Unless explicitly used, and until it is used, it is not intended to be construed under Article 112, paragraph 6 of the US Patent Act. It should be understood that not all such objectives or benefits described above will be achieved according to any particular embodiment. Thus, for example, in a manner that achieves or optimizes one benefit or group of benefits taught herein, without necessarily achieving other objectives or benefits 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 the context of only a limited number of embodiments, it will be readily appreciated that the invention is not limited to such disclosed embodiments. Rather, the invention may be modified to incorporate any number of modifications, modifications, substitutions or equivalent arrangements not previously described but equivalent to the spirit and scope of the invention. Further, although 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 embodiments described. Accordingly, the invention is not considered to be limited by the above description, but only by the appended claims.

The description herein includes and incorporates the best embodiments of the invention, as well as the creation and use of the device or system to enable one of ordinary skill in the art to practice the invention. You are using an example, including performing a method. The scope of the invention to be patentable is defined in the claims, which may include other examples that come to the mind of one of ordinary skill in the art. Such other examples are cases where they have 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 seals, slot seal assembly 12 shims, plate 14 support structure, layer 16 coating, coating layer 22 seal surface, side surface, support surface 24 seal surface, side surface, support surface 26 space, void 110 composite slot seal, slot seal assembly 112 Sim 114 Support structure 116 Coating 122 Seal surface 135 Seal slot contact surface, first side surface 142 First turbine component, first component, slot 144 Second turbine component, second component, slot 145 Seal slot contact Surface, first side surface 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 (8)

A gap (190) located in the seal slot of the first turbine component (142) and the second turbine component (144) and between the first turbine component (142) and the second turbine component (144). A seal assembly (10) for sealing, wherein the seal assembly (10) is
A metal shim (12) including a sealing surface (22) and a supporting surface (24),
It is a porous metal support structure (14), and a part of the porous metal support structure (14) is joined to a support surface (24) of the metal shim (12). The other portion of the metallic metal support structure (14) is not joined to the support surface (24) of the metal shim (12) and is separated from the metal shim (12) by the metal shim (12). A porous metal support structure (14) forming a plurality of voids between the support surface (24) of 12) and the porous metal support structure (14).
A ceramic, glass or enamel coating (16) that spreads over and over the porous metal support structure (14).
The support surface (12) of the metal shim (12) in which the coating (16) has penetrated into the porous metal support structure (14) and is not bonded to the porous metal support structure (14). Located in a plurality of voids between 24) and the porous metal support structure (14),
The coating (16) covers the outer surface of the porous metal support structure (14), and the coating (16) extends beyond the outermost surface of the porous metal support structure (14). A first turbine component (142), comprising a coating (16) having a thickness that thermally and chemically insulates the metal shim (12), wherein the coating (16) forms the seal slot. A seal assembly (10) configured to be hermetically engaged with a first side surface (145) of a first side surface (135) and a second turbine component (144). The seal assembly (10) according to claim 1, wherein the metal shim (12) is a substantially solid metal shim (12). The seal assembly (10) according to claim 1 or 2, wherein the coating (16) is chemically bonded to the porous metal support structure (14). The seal assembly (10) according to claim 1 or 2, wherein the metal support structure (14) is diffusion-bonded to the metal shim (12) by at least one brazing. The seal assembly (10) according to any one of claims 1 to 4, wherein the metal support structure (14) is a mesh structure. Any of claims 1 to 5, wherein the coating (16) is joined to at least one of the support surface (24) of the metal shim (12) and the porous metal support structure (14). The seal assembly (10) according to claim 1. A second turbine component (144) adjacent to the first turbine component (142) and the first turbine component (142), the first turbine component (142) and the second turbine component (144). The first turbine component (142) and the second turbine component (144), which form at least a part of the seal slot extending in the gap between the).
The seal set according to any one of claims 1 to 6, which is located in a seal slot of the first turbine component (142) and the second turbine component (144) and extends in a gap between them. A turbomachine, including a three-dimensional (10). The ceramic, glass or enamel coating (16) of the seal assembly (10) is the first side surface (135) of the first turbine component (142) and the first of the second turbine component (144). The turbomachine according to claim 7 , located on the first side surface of the seal slot collectively formed by the side surface (145).

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