• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
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  • 优先权
    • 专利摘要:
    The present invention provides a seal assembly (10) for reducing leakage between adjacent components of turbomachinery. The sealing arrangement (10) contains a metallic insert (12), a metallic holding structure (14) and a ceramic, glass or enamel coating (16). The insert (12) and the holding structure (14) are connected or fused to one another. The holding structure (14) can have internal free spaces or recesses and the coating (16) is applied to the insert (12) and the holding structure (14) so that the coating (16) is within the free spaces or recesses of the holding structure (14) between sections of the holding structure (14) and the insert (12) and is provided essentially over the outer surface of the holding structure (14). The holding structure (14) provides a mechanical fastening between the insert (12) and the coating (16). During use, the coating (16) provides thermal and / or chemical shielding from the metallic insert (12) and the holding structure (14) of the sealing arrangement (10).
    公开号:CH711017B1
    申请号:CH00535/16
    申请日:2016-04-21
    公开日:2021-03-31
    发明作者:Sevincer Edip；Nandkumar Sarawate Neelesh；Marin Anthony；Subramaniam Venkataramani Venkat
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    BACKGROUND OF THE INVENTION
    The present application relates generally to seals to reduce leakage and, more particularly, to seals that are adapted to operate within a seal gap to reduce leakage between adjacent stationary components of the turbomachine.
    Leakage of hot combustion gases and / or cooling flows between turbomachine components generally causes a reduced power output and a lower efficiency. For example, hot combustion gases can be contained in a turbine by providing pressurized compressor air around a hot gas path. Typically, leakage of high pressure cooling flows between adjacent turbine components (such as stator shrouds, vanes and nozzles, liner housing components, and rotor components) in the hot gas path results in reduced efficiency and requires an increase in combustion temperature and a decrease in gas turbine efficiency to a desired level To maintain performance level compared to a surrounding space of such a leak. Turbine efficiency can therefore be improved by reducing or eliminating leakage between turbine components.
    Commonly, leakage between turbine component ports is treated with metallic seals that are positioned in the seal gaps formed between the turbine components, such as stator components. Sealing gaps typically extend across the connections between components so that metallic seals disposed therein block or otherwise prevent leakage through the connections. However, preventing leakage between turbine component connections with metallic gap seals positioned in sealing gaps in the turbine components is complicated due to the relatively high temperatures generated in modern turbo-machinery. Due to the introduction of new materials, such as turbine components made of a composite ceramic matrix (CMC) material, which allow turbines to operate at higher temperatures (e.g. above 1500 ° C) than traditional turbines, conventional metallic turbine gap seals for use in sealing gaps may possibly be inadequate.
    Avoiding leakage between turbine component connections with metallic seals is made even more difficult by the fact that the sealing gaps of turbine components are formed by corresponding gap sections in adjacent components (with a seal positioned therein extending over a transition between components). Misalignment between these adjacent components, such as due to thermal expansion, manufacturing, assembly and / or installation restrictions, etc., causes an uneven gasket gap contact surface that varies in design, shape and / or size over time can. Such irregularities on the gap contact surface allow leakage via a gap seal which is arranged within the sealing gap if the seal does not bend, deform or otherwise compensate for such irregularities. Unfortunately, many conventional metallic shims that compensate for such uneven gasket gap contact surfaces due to the misalignment of adjacent turbine components cannot adequately withstand increases in turbine operating temperatures.
    Therefore, it would be desirable to have composite turbomachine component transition seals that are adapted for use in typical turbine seal gaps that can withstand the increasingly higher operating temperatures of turbines and accommodate non-uniformities in the seal gap contact surface.
    BRIEF DESCRIPTION OF THE INVENTION
    In a first aspect, the present disclosure provides a seal assembly for positioning within a seal gap formed at least in part by adjacent turbomachine components to seal a gap extending between the components. The sealing arrangement contains a metallic shim, a porous metallic support structure and a ceramic, glass or enamel coating. The metallic insert has a sealing surface and a holding surface. The porous metallic holding structure is connected to the holding surface of the metallic insert. The ceramic, glass or enamel coating extends over and within the porous metallic holding structure, so that the coating essentially covers the holding surface side of the metallic insert and the holding structure. Sections of the coating are arranged between the holding surface of the metallic insert and parts of the metallic holding structure.
    In some exemplary embodiments, portions of the coating between the holding surface of the metallic insert and portions of the metallic holding structure can be arranged in a direction that extends away from the holding surface in order to connect the coating to the metallic insert via the metallic holding structure. In some embodiments, the direction extending away from the holding surface may be substantially normal to the holding surface.
    In some exemplary embodiments, the metallic insert can be a metallic insert consisting essentially of solid material.
    In some embodiments, the coating can be chemically bonded to the support structure.
    In some exemplary embodiments, the holding surface of the metallic insert and / or the metallic holding structure can have an outer protective coating which is designed to avoid oxidation of the metallic component in question.
    In some exemplary embodiments, the metallic holding structure can be diffusion-connected to the metallic insert via at least one soldering point.
    In some embodiments, the metallic support structure can be a mesh structure.
    In some exemplary embodiments, sections of the coating can be arranged between the holding surface of the metallic insert and sections of the metallic holding structure which are connected to the holding surface of the metallic insert.
    In some exemplary embodiments, sections of the coating can be arranged between the holding surface of the metallic insert and sections of the metallic holding structure that are not connected to the holding surface of the metallic insert. In some of these embodiments, portions of the metallic retaining structure that are not connected to the retaining surface of the metallic insert may extend away from or be connected to portions of the metallic retaining structure that are connected to the retaining surface of the metallic insert.
    In some exemplary embodiments, the coating can be connected to at least the holding surface of the insert and / or the holding structure.
    In some embodiments, the sealing arrangement can also have a second porous metallic holding structure which is connected to the sealing surface of the insert and a second ceramic, glass or enamel coating that extends over and within the second porous metallic holding structure, so that the second coating essentially covers the sealing surface side of the metallic insert and the second holding structure and sections of the second coating can be arranged between the sealing surface of the metallic insert and sections of the second metallic holding structure.
    In another aspect, the present disclosure provides a method of forming a seal assembly for use within a seal gap formed at least in part by adjacent turbomachine components to seal a gap extending between the components. The method includes connecting at least a portion of a porous metallic support structure to a metallic insert. The method also includes the application of ceramic, glass or enamel coating material to the porous metallic holding structure, so that the coating material covers the holding surface side of the metallic insert and the holding structure and has sections that are positioned between the holding surface of the metallic insert and sections of the metallic holding structure are. The method also includes densifying the ceramic, glass or enamel coating material to form a ceramic, glass or enamel coating that is mechanically attached to the metallic insert by means of the metallic support structure.
    In some exemplary embodiments, connecting at least a portion of the metallic holding structure to the holding surface of the metallic insert may comprise diffusion joining of at least a portion of the metallic holding structure to the holding surface of the metallic insert.
    In some exemplary embodiments, the application of ceramic, glass or enamel coating material to the porous metallic holding structure can comprise the application of a highly viscous, pourable ceramic composition by screen printing or contact application.
    In some such embodiments, the method may further include scraping off a portion of the ceramic composition that has been applied to the support structure, and wherein densifying the ceramic composition includes curing and heat treating the applied ceramic composition.
    In some embodiments, applying the ceramic, glass, or enamel coating material to the porous metallic support structure may include applying a glass or enamel-based composition in a paintable form by painting, dip coating, or spray coating.
    In some embodiments, densifying the glass or enamel-based composition can include drying and heat treating the applied glass or enamel-based composition.
    In another aspect, the present disclosure provides a turbomachine having a first turbine component and a second turbine component adjacent to the first turbine component, the first and second turbine components defining at least a portion of a sealing gap across a gap between the turbine components. The turbomachine also includes a seal that is disposed within the seal gap of the first and second turbine components and extends across the space therebetween. The seal contains a metallic insert, a porous metallic support structure and a ceramic, glass or enamel coating. The metallic insert contains a sealing surface and a holding surface. The porous metallic holding structure is connected to the holding surface of the metallic insert. The ceramic, glass or enamel coating is provided on and within the metallic holding structure, so that the coating essentially covers the holding surface side of the metallic insert and the holding structure, and sections of the coating are arranged between the holding surface of the metallic insert and sections of the metallic holding structure .
    In some embodiments, the ceramic, glass or enamel coating of the seal can be positioned against a first side of the sealing gap, which is jointly formed by a first side of the first turbine component and a first side of the second turbine component.
    In some exemplary embodiments, the metallic insert is a substantially metallic insert made of solid material and the porous metallic holding structure is a metallic mesh structure.
    In some exemplary embodiments, portions of the coating between the holding surface of the metallic insert and portions of the metallic holding structure can be arranged in a direction that extends substantially normal to the holding surface in order to mechanically connect the coating over the metallic holding structure with the metallic insert connect.
    These and other objects, features, and advantages of the disclosure will become apparent from the following detailed description of the various aspects of the disclosure taken in conjunction with the accompanying drawings.
    BRIEF DESCRIPTION OF THE DRAWINGS
    FIG. 1 is a cross-sectional view of a portion of a first exemplary gap seal arrangement in accordance with the present disclosure.
    FIG. 2 is a perspective view of the exemplary gap seal from FIG. 1, which is partially constructed to illustrate the arrangement of the insert, the holding structure and the coating parts;
    FIG. 3 is a perspective view of the partial arrangement of the insert and the holding structure of the exemplary gap seal from FIG. 1;
    FIG. 4 is an enlarged perspective view of a portion of the sub-assembly of the insert and holding structure from FIG. 3;
    FIG. 5 is an enlarged cross-sectional view of a portion of the subassembly of the insert and holding structure from FIG. 4;
    Figure 6 is a cross-sectional view of an exemplary gap seal assembly positioned within a seal gap to seal an exemplary transition between turbine components; and
    FIG. 7 is a cross-sectional view of an exemplary gap seal arrangement.
    DETAILED DESCRIPTION
    In the following, the indefinite or definite articles “a”, “an”, “the” and “this” are intended to mean that one or more of the named elements are present. The terms “having,” “containing,” and “having” are intended to be inclusive and to mean that there may be additional elements other than those specified. Any examples of operating parameters are not exclusive of other parameters of the disclosed embodiments. Components, aspects, features, configurations, arrangements, uses, and the like described, illustrated, or otherwise disclosed herein with respect to any particular seal embodiment may equally be applied to any other seal embodiment disclosed herein.
    Composite seals for turbomachine component transitions, which are set up for use in turbine seal gaps (e.g. turbine gap composite seals) and methods for producing and using the same, according to the present disclosure are set up to withstand the relatively high operating temperatures of the turbines having CMC components and / or adapt to unevenness of the sealing gap contact surface. In particular, the composite gap seals are set up essentially to prevent chemical interaction and essentially to limit thermal interaction of metallic components of the composite gap seals with the hot gas flows / a leak and / or the seal gap itself. In this way, the composite gap seals provided herein enable use in high temperature turbine applications. In addition to high temperature operation, the composite gap seals of the present disclosure are configured to accommodate bumps in the seal gap contact surface to accommodate leakage due to misalignment of the seal gap surface and / or roughness.
    As illustrated in Figures 1-5, the exemplary seal 10 can be a sealing arrangement comprising at least one insert or plate 12, at least one holding structure or holding layer 14 and at least one coating or coating layer 16, which are connected to one another. The insert 12 may be effective to substantially prevent the passage of substances therethrough. For example, the insert 12 can consist essentially of solid material or otherwise be essentially impermeable to gases and / or liquids and / or solids at pressures and temperatures that are generated in the turbomachine. However, the shim 12 can also provide flexibility in the pressures and temperatures generated in the turbomachine to accommodate skewings or offsets in the gap surfaces in the thickness direction T1. In one embodiment, the insert 12 is a substantially solid plate-like metallic element. In such embodiments, the shim 12 can be a high temperature metallic alloy or superalloy. For example, the insert 12 (and / or the support structure 14) can be made of stainless steel or a nickel-based alloy (at least in part), such as a nickel-molybdenum-chromium alloy, Haynes 214 or Haynes 214 with an aluminum oxide coating. In some embodiments, the insert 12 can be made from a metal having a melting temperature of at least 1500 degrees Fahrenheit (815.6 degrees Celsius), and preferably at least 1800 degrees Fahrenheit (982.2 degrees Celsius). In some embodiments, the insert 12 can be made from a metal with a melting temperature of at least 2200 degrees Fahrenheit (1204 degrees Celsius).
    An outer sealing surface or sealing side 22 of the insert 12, which is essentially opposite the holding structure 14, as shown in FIGS. 1-5, can be essentially flat (in a neutral state). As will be further explained below, the outer sealing surface 22 of the insert 12 can be designed to interact with or act on a high-pressure cooling air flow that flows through the at least one intermediate space or the connection between the at least one and second component, which forms a sealing gap ( at least partially) so that the seal 10 is forced or pressed against the sealing surfaces of the first and second components in the sealing gap in order to essentially prevent gases, liquids and / or solids from escaping through the gap or connection. As such, the insert 12 and / or the coating 16 (or the insert 12 and the coating 16 acting together) can be substantially impermeable to liquids, gases, and / or solids at pressures exerted in turbomachines, so that the seal 10 provides at least a low leakage rate through the sealing gap.
    As shown in FIGS. 1-5, the holding structure 14 can be connected to a holding surface or holding side 24 of the insert 12 which is essentially opposite the sealing surface 22. In some embodiments, the retaining structure 14 can be metallic, such as metallic material having the properties described above with respect to the insert 12. The insert 12 and the retaining structure 14 can be made of the same or substantially the same metallic material and thereby the same or substantially have the same coefficient of thermal expansion (hereinafter CTE). However, the insert 12 and the retaining structure 14 need not be made of the same or substantially the same material or have the same or substantially the same CTE. It is preferred, however, that the insert 12 and the retaining structure 14 are designed such that any difference in the CTE between them tears, breaks or otherwise makes ineffective due to the cyclical nature of a diffusion bond between the two, as will be further described below thermal load on the seal 10 during use in the turbomachine. As such, the CTE of the insert 12 and the CTE of the holding structure 14 can only differ by such an amount that the diffusion connection between the insert 12 and the holding structure 14 is not rendered ineffective by cyclic thermal loading of the seal 10 during use in the turbo machine. In other words, the material of the insert 12 and the retaining structure 14 (or any other factor affecting the CTE) can be different, but the insert 12 and the retaining structure 14 can be designed so that a diffusion connection between them is not damaged or rendered ineffective when the seal 10 is subjected to cyclic thermal loading when it is used in a sealing gap of a turbine.
    The holding structure 14 can be any holding structure, holding element or holding arrangement that is able to chemically bond or fuse (e.g. by means of a diffusion bond) with the holding surface 24 of the insert 12 and is able to to be securely mechanically bonded or attached to the coating 16 (which is chemically bonded to the insert 12). In this way, the coating 16 can be securely mechanically connected or fastened to the insert 12 by means of the holding structure 14. For example, the holding structure 14 can be a substantially porous metallic structure (opposite the substantially non-porous insert 12) that contains recesses or spaces for holding parts of the coating 16 therein. The term “porous” is used herein with reference to the retaining structure 14 to describe a structure, element or elements or mechanisms that have pores, channels, spaces, recesses, depressions or other internal spaces that are unique to the coating 16 and / or collectively allow to extend into the holding structure 14 from the upper or outer surface of the holding structure 14 in a direction that extends towards the insert 12 and that at least some portions of the coating 16 between the sealing surface 24 of the insert 12 and At least a portion of the support structure 14 are disposed in a direction that extends at least generally away from the sealing surface 24 of the insert 12, such as substantially normal to the sealing surface 24 of the insert 12. In some embodiments, the support structure 14 can be a porous metallic Mesh, grid, honeycomb structure or woven structure with intertwined, interwoven or inei be mixed elements, fibers or parts, as shown in Figures 1-5.
    As shown in Figures 1-5, at least some portions of the support structure 14 (e.g., portions of the metallic mesh elements or fibers) may be fused or connected to the support surface 24 of the insert 12. In some embodiments, however, other portions of the support structure 14 may be spaced from the support surface 24 of the insert 12 (i.e., not fused or bonded to the insert 12). For example, a metallic mesh-like support structure 14 may include metallic elements or fibers that include first portions that are fused or connected to the support surface 24 of the insert 12 and second portions that are not joined or fused to the insert 12 and potentially from the support surface 24 of the insert 12 are spaced apart. In this manner, only a portion or portion of the support structure 14 can be connected or fused to the insert 12, while the remaining portion or portion of the support structure 14 is connected to (e.g., mechanically attached) or protrudes away from the connected or fused portion.
    The shim 12 and at least a portion of the support structure 14 can be joined or fused together so that their attachment is able to effectively withstand the temperatures, pressures and other conditions they experience in a sealing gap of a 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 monolithic chemical bond is established therebetween. In some exemplary embodiments, the insert 12 and the at least one section of the holding structure 14 can be firmly welded to one another, such as by means of a diffusion connection. In some exemplary embodiments, the insert 12 and the holding structure 14 can be connected to one another by means of a diffusion connection through at least one high-temperature soldering point.
    The insert 12 and / or the holding structure 14 of the insert 10 can have one or more protective coatings (not illustrated) which are applied or arranged over or on their outer surface. For example, at least a portion of the outer surface of the insert 12, such as the sealing surface 22 or the holding surface 24 and / or at least a portion of the outer surface of the holding structure 14 can have at least one protective coating or protective layer. In other words, at least a portion of the outer surfaces of the insert 12 (for example the holding surface 24) and / or the holding structure 14 can be formed by a protective coating that covers the underlying metallic component (that is, the metallic insert 12 or the metallic holding structure 14 ) covered. As such, the portion or portions of the insert 12 and / or the support structure 14 may include the protective coating or protective layer. For example, the holding structure 14 can be connected to a protective coating that covers the insert 12 and forms the holding surface 24. The protective coating (s) of the metallic insert 12 and / or the metallic holding structure 14 can be designed to essentially prevent or delay an oxidation of the metallic components underneath. In some exemplary embodiments, the protective coating (s) of the metallic insert 12 and / or the metallic holding structure 14 can contain or substantially comprise an oxide, such as for example chromium oxide or aluminum oxide.
    With the insert 12 and the at least one portion of the holding structure 14 that are connected or fused to one another, the at least one coating 16 can be applied to the seal 10 in order to protect the insert 12 and the holding structure 14. As shown in FIGS. 1 and 2, the coating 16 can be applied to the seal 10 so that the coating 16 covers or overlays at least the holding structure 14 and the holding surface 24 of the insert 12 (i.e. the coating extends over and into the holding structure 14 of the seal 10 and thereby over the holding surface 24 of the insert 12). The coating 16 can substantially fill the pores and spaces of the holding structure 14 and can be substantially non-porous (compared to the holding structure 14). In some embodiments, the coating may also cover or overlay the side of the retaining surface 24 and the side edges of the seal 10 so that the side of the sealing surface 22 of the seal 10 is the only side or edge of the seal 10 that is not covered by the coating 16 or coating 16.
    The coating 16 may be one or more coating material (s) that are effective and substantially avoid chemical interaction and substantially thermal interaction of at least the metallic shim 12 (and potentially the Holding structure 14) when the seal 10 is used in a sealing gap of a turbine, such as a sealing gap formed by components of a high temperature gas turbine, such as stator components. As will be further explained below, the coating 16 on the holding structure 14 can be designed to act on the first and second sealing surfaces of the first and second components, which form a sealing gap, in a sealing manner in order to essentially prevent the passage of gases, liquids and / or or to prevent solids through the gap or connection of the first and second components. In this way, the coating 16 can be effective to essentially prevent silicide formation, oxidation, thermal creep and / or wear of at least the metallic shim 12 (and potentially the support structure 14) during use of the seal 10 in such a sealing gap of a turbine . In other words, the coating 16 enables metal based seals, such as the seal 10 with the one or more metal shims 12 (and potentially the support structure 14) to be used in high temperature gas turbine applications. In some exemplary embodiments, the coating 16 can be a ceramic, glass or enamel material that is effective in protecting (for example preventing or reducing oxidation, silicide formation, thermal creep, wear, etc.) at least the metallic insert 12 and / or the holding structure 14th
    In some embodiments, the coating 16 can be formed from a crystalline-vitreous or glass-ceramic composition. In some of these embodiments, the coating 16 may include metal oxides, nitrides, or oxynitrides. For example, the coating 16 can be stabilized or unstabilized zirconium oxide, aluminum oxide, titanium oxide, zirconates, titanates, aluminates, tantalates and niobates of alkaline earths and / or rare earths, tungstates, molybdates, silicate borates, phosphates, silicon nitrites, silicon carbides, intermetallic compounds, such as MAX phase materials (Ti2AlC) and combinations thereof. In some embodiments, the coating 16 can be formed from a high temperature enamel compound. For example, the coating 16 may include alkaline / alkaline earths, aluminoboro-phosphorus-silicate glasses and fillers. The coating 16 (whether ceramic, glass or enamel material) can have a required high melting temperature and flow properties in order to provide the optimum stability and conformity in the operating states of the seal 10.
    In some embodiments, the coating 16 (and / or other protective coatings described herein) on the metallic insert (and / or the metallic support structure 14) can be at least partially due to the diffusion of selected species in and / or by reaction with the metallic Insert 12 (and / or the metallic holding structure 14) are formed in order to form metallic (s) silicide (s) and / or at least one oxide layer on the metallic insert 12 (and / or the metallic holding structure 14). The metallic silicide or metallic suicides that are formed by the diffusion / reaction of the selected species and the metallic insert 12 (and / or the metallic holding structure 14) can be resistant to oxidation. The one or more oxide layers formed by the diffusion / reaction of the selected species and the metallic insert 12 (and / or the metallic support structure 14) may have negligible oxygen diffusion properties therethrough, whereby the metallic insert 12 (and / or the metallic holding structure 14) are protected. For example, Si can be used and diffused into and / or react with the metallic insert 12 (and / or the metallic support structure 14). In some exemplary embodiments, the selected species for forming the metallic silicide or metallic silicides and / or the at least one oxide layer can comprise Al, Si, B, alloys thereof, or combinations thereof. In some embodiments, the metallic insert 12 (and / or the metallic support structure 14) may include or be formed from refractory metal, such as Mo, W, alloys thereof, or combinations thereof, and the refractory metallic insert 12 (and / or the support structure 14). may have a silicide layer and / or an aluminum oxide protective layer at least as a portion of the coating 16. In some embodiments, the metallic silicide or the metallic silicides and / or the at least one oxide layer can be produced by a reaction between a fixed bed of the selected species (for example in a powder or such form) and the metallic insert 12 (and / or the metallic Holding structure 14) can be formed at high temperatures (i.e., a bed-siliciding / oxide layer process). In other exemplary embodiments, the metallic silicide or metallic silicides and / or the at least one oxide layer on the metallic insert 12 (and / or the holding structure 14) can be formed by one or more coatings of the selected species (for example metallic elements / alloys). by vapor phase deposition (e.g. chemical vapor deposition (CVD) or physical vapor deposition (PVD)) followed by chemical treatment and / or heat treatment.
    In some embodiments of the ceramic coating 16, the ceramic coating 16 may be formed from a pourable composition having a high viscosity, such as a pourable cement (e.g., COTRONICS 904 or 989). The pourable composition with high viscosity can be applied to the connection of the insert 12 and the holding structure 14 by screen printing or contact application. After the pourable composition of the coating 16 has been applied to the connection of the insert 12 and the holding structure 14, excess material of the coating 16 can be removed by a scraper to a desired or required thickness on the seal 10 (for example a certain amount of pourable Composition of the coating on or above the outer surface of the holding structure 14). The applied and scraped off “unsintered” coating can be processed further in order to compact the material of the coating 16 and to bond it chemically to the compound of the insert 12 and the holding structure 14 by curing and heat treatment. The curing can set the material of the coating 16 and the heat treatment can compact the material of the coating 16 to a state with closed porosity, in order to finally form the coating 16 on the connection of the insert 12 and the holding structure 14. As indicated above, the coating 14 can be connected to the metallic insert 12 itself or to a protective coating that covers the metallic insert 12.
    In some embodiments of the glass or enamel coating 16, the coating 16 can be formed by a glass or enamel based composition in a paintable form. The paintable form of glass or enamel-based compositions can have a relatively low viscosity, which enables the glass or enamel-based composition to be painted onto the connection of the insert 12 and the holding structure 14, or the connection of the insert 12 and the holding structure 14 can through Dipping or spraying can be coated with the glass or enamel-based composition. In some embodiments, the glass or enamel based composition can include a solvent or the like to reduce the viscosity of the composition. After the glass or enamel-based compositions have been applied to the joint of insert 12 and support structure 14, the compositions can be dried to remove solvents from the applied compositions. After the applied glass or enamel-based compositions have dried on the joint of the insert 12 and the support structure 14, the compositions can be heat treated to form a substantially dense, smooth, vitreous coating that chemically and mechanically bond with the insert 12 and the Holding structure 14 is connected.
    In some alternative embodiments, the composition of the coating 16 can be formulated as a precursor. For example, the composition of the coating can be formed by a gellable sol of precursor salts such as hydrates, carboxyls, alkoxides with a certain proportion which is added as a filler. The gellable soul can be applied to the joint of the insert 12 and the support structure 14 to form the coating 16 by any of the foregoing methods.
    As explained above, the coating 16 (regardless of whether it is ceramic, glass or enamel) can be applied to the metallic insert 12 and the metallic support structure 14, so that the coating 16 at least initially chemically directly with the metallic insert 12 (for example above or on the holding surface 24 of the metallic insert 12) and / or the metallic holding structure 14 is chemically connected or coupled. As indicated above, the metallic insert 12 and / or the metallic holding structure 14 can have a protective coating. In some embodiments, the coating 16 may be chemically bonded to the protective coating (whereby it is indirectly chemically bonded to the metallic insert 12 and / or the metallic retaining structure 14).
    The coating 16 can essentially fill voids of the support structure 14 (having any spaces between the support structure 14 and the insert 12, as will be further explained below) and extend over the upper surface or outer surface of the support structure 14 (thereby to to cover the holding surface 22 of the insert 12). As will be explained further below, the holding structure 14 can be chemically bonded to the insert 12 and designed to bond mechanically to the coating 16. In this way, the coating 16, which is effective to thermally and chemically insulate the metallic insert 12, can at least initially be both chemically bonded and mechanically attached to the metallic insert 12 and the metallic holding structure 14.
    In order that the coating 16 provides permanent and reliable protection at least for the metallic insert 12 (and potentially for the metallic support structure 14), the support structure 14 can be effective in maintaining the attachment or covering of the coating 16 over the metallic one Insert 12 - such as sides, edges and portions of at least the metallic insert 12 that are exposed in a sealing gap of the turbine 10 during use of the seal 10. For example, the chemical bond or coupling between a ceramic or glass coating 16 and the metallic insert 12 and the metallic support structure 14 (or a protective coating thereon) may possibly be due to the thermal cycling of the insert 12 (e.g. occurring during use of the insert 12) may not be able to withstand the thermal mismatch between the ceramic or glass coating 16 and the metallic insert 12 and the metallic retaining structure 14. As shown in FIGS. 1 and 2 and explained above, the metallic holding structure 14 can be connected or fused to the metallic insert 12 and the coating 14 can be provided at least by or within free spaces of the holding structure 14. More precisely, however, the coating 14 can also extend or be arranged at least partially between the insert 12 and sections of the holding structure 14 in a direction that extends at least generally away from the sealing surface 22 of the insert 12. In some embodiments, the coating 14 may be at least partially disposed between the insert 12 and individual elements, fibers, or portions of the support structure 14 (or portions thereof) in a direction that extends substantially normal to the support surface 24 of the insert 12. The coating 14 may be provided or extend substantially around fibers, elements, or portions of the support structure 14 (other than portions thereof that are fused or bonded to the insert 12). In this way, the holding structure 14 provides a mechanical attachment of the coating 14 to the metallic insert 12, which prevents the coating 14 from becoming detached or separating from the insert 12 because at least some of the fibers, elements or portions of the holding structure 14 are connected or fused to the metallic insert 12 and sections of the coating 14 are arranged between the insert 12 and the sections of the holding structure 14. For example, if the chemical bond between the coating 16 and the metallic insert 12 and / or the metallic support structure 14 (or a protective coating thereon) fails due to a thermal mismatch therebetween, the arrangement of the coating 16 is essentially around the fibers, elements or sections the holding structure 14 (e.g. via the outer surface of the holding surface 24 and between the sections of the holding surface 24 and the insert 12) a mechanical fastening that prevents the coating 16 from being detached from the metallic insert 12 (by means of the metallic holding structure 14) or is separated.
    As indicated above, portions of the coating 14 can be arranged between the metallic insert 12 and portions of the holding structure 14 that are spaced apart from the metallic insert 12 (for example, sections that are not connected or fused to the metallic insert 12, but rather rather, protrude away from it or are connected with sections that are connected or fused to the metallic insert 12). Sections of the coating 14 can also be arranged between the metallic insert 12 and sections of the holding structure 14 that are connected or fused to the metallic insert 12. As shown in FIGS. 1 and 5, for example, the fibers, elements or portions of the holding structure 14 that are connected or fused to the metallic shim 12 can have or define a shape that defines a space or free space 26 between the fibers, Provide or form elements or sections of the holding structure 14 and the holding surface 24 of the insert 12. In the exemplary embodiment illustrated in FIGS. 1, 4 and 5, the fibers, elements or sections of the holding structure 14, which are connected or fused to the holding surface 24 of the insert 12, are essentially circular in cross section, so that a space or free space 26 is formed between the relevant fibers, elements or sections of the holding structure 14 and the holding surface 24 of the insert 12. Other configurations of the holding structure 14 that form such a space or free space 26 between the holding surface or side 24 of the insert 12 and the holding structure 14 (in the connected state) can be used. In this way, the shape or design of the fibers, elements or sections of the holding structure 14 can enable the coating 14 to be arranged between the connected sections of the holding structure 14 and the sealing surface or sealing side 24 of the insert 12 (e.g. in a direction that generally extends extends away from or substantially normal to the sealing surface 24).
    FIG. 6 illustrates a cross-sectional view of an exemplary gap seal arrangement 110, which is arranged in an exemplary sealing gap in order to seal an exemplary transition between turbine components, such as stator components. The exemplary gap seal assembly 110 is substantially similar to the exemplary gap seal assembly 10 of FIGS. 1-5, as described above, and therefore the same reference numbers are used with a prefixed “1” to denote the same aspects or functions and the above description includes the directed to such aspects or functions (and the alternative exemplary embodiments thereto) can equally be transferred to the exemplary gap seal arrangement 110. In particular, Figure 6 shows a cross-section of a portion of an exemplary turbomachine including an exemplary first turbine component 142, an adjacent exemplary second turbine component 144, and an exemplary composite gap seal 110 installed in the sealing gap formed by the first and second components 142, 144. The first and second turbine components 142, 144 may be first and second stator components, such as first and second vanes of first and second stators, respectively. In other embodiments, the first and second components 142, 144 can be any other adjacent turbomachine component, such as a stationary or a transition and / or a rotating (i.e., moving) turbine component. In other words, the exemplary composite gap seals 10, 110 described herein can be configured for or used with any number or type of turbomachine components that require a seal to reduce leakage between the components.
    The cross section of the exemplary components 142, 144 and the exemplary composite gap seal 110, which is illustrated in FIG. 6, was created along a width of the structures, whereby an exemplary width and thickness / height of the structures is illustrated. It is noted that the relative width, thickness, and cross-sectional shape of the structures illustrated in Figure 6 are exemplary and the structures can have any other relative width, thickness and cross-sectional shape. In addition, the length of the structures (which extends into and out of the plane of the drawing of FIG. 6) can be any length and the shape and configuration of the structures in the longitudinal direction can be any shape or configuration. It is also indicated that although only two exemplary turbine components 142, 144 are shown defining a sealing gap, a plurality of components may form a plurality of sealing gaps that are in communication with one another. For example, a plurality of turbine components may be arranged in the circumferential direction so that sealing gaps formed therebetween are also arranged in the circumferential direction and are in communication with each other. In such embodiments, the gap seals 10, 110, 210 can be designed in accordance with the present disclosure to span a plurality of sealing gaps in order to seal a plurality of gaps or transitions and thereby reduce the leakage between a plurality of turbine components.
    As illustrated in FIG. 6, the first and second adjacent turbine components 142, 144 can be spaced apart from one another so that a transition, gap or path 190 between the first and second adjacent components 142, 144, such as Stators, extends. Such a transition 190 can allow a flow, such as an air flow, between the first and second components 142, 144. In some implementations, the first and second turbine components 142, 144 may be disposed 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. It is noted that the term “airflow” is used herein to describe the movement of any material or composition or combination of materials or compositions that translates through the transition 190 between the first and second turbine components 142, 144.
    In order to accommodate a seal that stretches over the transition 190 and thereby blocks the transition 190 or blocks it in some other way, the first and second adjacent components 142, 144 can each have a gap, as shown in FIG. In the illustrated exemplary embodiment, the first component 142 has a first sealing gap 170 and the second component has a second sealing gap 180. The first and second sealing gaps 170, 180 can be of any size, shape, or configuration that is capable of receiving a seal therein. For example, the first and second sealing gaps 170, 180, as shown in the exemplary embodiment illustrated in FIG extends from within the first component 142 over the transition 190 and into the second component 144. In this way, the pair of first and second sealing gaps 170, 180 can jointly form a recess or a sealing gap to support opposing portions of the gasket so that the gasket 110 passes through the transition 190 that extends between the adjacent components 142, 144 extends.
    In some arrangements where the first and second components 142, 144 are adjacent, the first and second sealing gaps 170, 180 can be formed so that they are substantially aligned (e.g., in a mirrored or symmetrical relationship). However, the first and second sealing gaps 170, 180 may be displaced, twisted, inclined, or otherwise misaligned during use due to manufacturing and assembly limitations and / or variances, such as thermal expansion, movement, and the like. In other scenarios, the first and second sealing gaps 170, 180 can remain in a mirrored or symmetrical relationship, but the relative positioning of the first and second sealing gaps 170, 180 can change (such as through use, wear and tear, or operating conditions). The term “misaligned” is used herein to encompass any scenario in which the gaps have changed their relative position or orientation with respect to a nominal or home position or configuration.
    With reference to the exemplary first and second sealing gaps 170, 180 of the exemplary first and second turbine components 142, 144 and the exemplary seal 110 from FIG. 6, the exemplary seal 110 is preferably flexible in a misaligned configuration (not shown), to accommodate the misalignment and to maintain the sealing contact of the coating 116 with the first and second sealing gaps 170, 180 to effectively block or eliminate the junction 190 that extends between the first and second turbine components 142, 144, thereby a Reduce or prevent interaction of the first and second air flow 150, 160. In particular, as shown in FIG. 6, the first and second air flows 150, 160 can interact with the transition 190, so that the first air flow 150 is a “driving” air flow which is directed against the outer sealing surface 122 of the insert 112 of the seal 110 acts to urge the coating 116 of the seal 110 against the side surfaces 135, 145 of the first and second seal gaps 170 and 180, respectively. In such scenarios, the seal 110 (and / or the coating 166) may preferably be sufficiently flexible to move (e.g., resiliently) as a result of the forces exerted by the first air flow 150 (e.g. above those exerted by the second air flow 160). deform to accommodate any misalignment between the first and second sealing gaps 170, 180, but be sufficiently rigid to resist being "folded" or otherwise "pushed" into the transition 190. In other words, the exemplary seal 110 in such a scenario can preferably be sufficiently flexible, but still sufficiently rigid, to maintain the sealing action of the coating 116 of the insert 112 with the first side surfaces 135, 145 by the forces of the first air flow 150. For example, the metallic shim 112, the metallic support structure 114, and the coating 116 can be configured to conform to bumps on the seal gap contact surfaces 135, 145 during use of the turbine. In some such embodiments, the coating 116 may be a glass insulation coating with a transition temperature (Tg) corresponding to the operating temperatures of the turbine / seal 110 such that the glass coating 116 becomes soft or deformable at operating temperatures to accommodate the deformation and contouring of at least the coating 116 the first side surfaces 135, 145 to enable. In addition to having sufficient flexibility (in all directions) to effectively seal the transition 190 in misalignment scenarios, as described above, the exemplary seal 110 may preferably be sufficiently rigid to meet the assembly requirements.
    The size of the seal 110 can be any size, but can be dependent on or at least related to the components 142, 144 in 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 sealing gaps 170, 180 and thereby the thickness T2 of the total gap formed by the first and second sealing gaps 170, 180 when the first and second adjacent components 142, 144 can be mounted. In some embodiments, the thickness T1 of the example gasket 110 can be in a range of 0.01 "(0.25mm) to about 1/4" (6.35mm), and more preferably within a range of about 0.05 (1, 3mm) inch to about 0.1 inch (2.5mm). Equally, the width W1 of the seal 110 can be smaller than the width W2 of the total gap which is formed by the first and the second sealing gap 170, 180 of the first and second components 142, 144 and of the intermediate space 190 between the components 142, 144, when the components 142, 144 are installed adjacent to each other. In some embodiments, the width W1 of the example seal 110 may preferably be within a range of about 0.125 inches (3.18 mm) to about 0.75 inches (19 mm).
    As shown in the embodiment illustrated in Figure 6, the seal 110 can be positioned and arranged, for example, within the sealing gap (ie the first and second sealing gap 170, 180) so that the first or cool air flow 150 against the outer Sealing surface 122 of the insert 112 acts to force the coating 116 against the first side surfaces 135, 145 of the first and second sealing gaps 170, 180. Due to the impermeable shape of the insert 112 and / or the coating 116, the seal 110 prevents the cooling air flow 150 from passing through the intermediate space 190 and into the second or hot combustion air flow 160. In addition, the coating 116 protects the metallic insert 112 from the high temperatures of the combustion air flow 160. In this way, at least the shape and design of the outer or sealing surface of the coating 116 of the seal 110 (e.g. the surface with the exemplary first side surfaces 135, 145 or other sealing surfaces of the exemplary first and second sealing gaps 170, 180) are related to the shape and configuration of the gaps 142, 144 in which the gasket 110 is installed. In other words, the shape and design of at least the outer or sealing surface of the coating 116 of the seal 110, such as the contour, surface texture, etc., can be designed to provide a sealing contact with the first and second sealing gaps 170, 180, in which the seal 110 is installed. For example, in the example illustrated in FIG. 6, the outer or sealing surface of the coating 116 of the seal 110 can be essentially smooth or flat in order to essentially abut or otherwise essentially the essentially planar first side surfaces 135, 145 of the first and second Sealing gap 170, 180 to act in order to prevent or reduce leakage of the first air flow 150 between the seal winding arrangement 110 and the first side surfaces 135, 145 of the first and second sealing gap 170, 180 and ultimately into the second or hot combustion air flow 160 (and also to protect the metallic insert 12 from the high temperatures of the hot combustion air flow 160). In some alternative exemplary embodiments (not shown), the shape and design of at least the outer or sealing surface of the coating 116 of the seal 110 can be shaped or implemented differently than those of the corresponding sealing surfaces of the first and second sealing gap 170, 180 (such as the exemplary first Side surfaces 135, 145 of the first and second sealing gap 170, 180, which are illustrated in Figure 6).
    FIG. 7 illustrates a cross-sectional view of another exemplary gap seal arrangement 210 in accordance with the present disclosure. The exemplary gap seal assembly 210 is essentially the same as the exemplary gap seal assemblies 10 and 110 of FIGS. 1-6 described above, and therefore the same reference numbers are used with a prefixed “2” to denote the same aspects or functions and the description above That is, directed to such aspects or functions (and the alternative embodiments thereto) may equally be transferred to the exemplary gap seal assembly 210. As shown in Figure 7, the gap seal assembly 210 differs from the seal assemblies 10 and 110 in that the seal 210 is symmetrical in the thickness direction. As such, the seal assembly 110 provides easy installation or assembly of the seal 210 in a turbine seal gap since the seal 210 does not require any particular thickness orientation.
    As shown in FIG. 7, both the side of the sealing surface 222 and the side of the sealing surface 224 of the metallic insert 12 have a metallic holding structure 214 which is connected to it. In some exemplary embodiments (not shown), the holding structure 214 can extend over one or more side edges of the metallic insert 212 and onto the sealing surface 222 and the holding surface 224. In the same way, both the holding structure 214, which is connected to the sealing surface 222, and the holding structure 214, which is connected to the holding surface 224 of the metallic insert 212, have the coating 216 applied thereon. In some embodiments (not shown), the coating 216 may extend over one or more side edges of the metallic shim 212 and onto / into the holding structure 214 connected to the sealing surface 222 and the holding structure 214 connected to the holding surface 224. The coating 216, which is applied to and into the holding structure 214, which is connected to the sealing surface or sealing side 222 of the insert 210, can isolate or protect the side of the sealing surface 22 of the insert 212 (such as from the cooling air flow 150 which was explained above with reference to FIG. 6).
    The seal assemblies disclosed herein provide a low rate of leakage, similar to that possible with traditional gap seals, such as solid metal shim seals, while facing problems of silicide, oxidation, thermal creep and / or increased Wear can be eliminated when applied to modern high-temperature turbo-machines. In addition, the seal assemblies disclosed herein can be less sensitive to manufacturing variability as compared to existing seals. The sealing arrangements disclosed herein therefore reduce leakage with low manufacturing and operational risks and are applicable in both OEM and retrofit applications.
    The present application provides composite seals for reducing leakage between adjacent components of turbomachinery. The composite seals can contain a metallic shim, a metallic support structure and a ceramic, glass or enamel coating. The insert and the support structure can be connected or fused to one another. The holding structure can have internal free spaces or recesses and the coating can be applied to the insert and the holding structure, so that the coating is provided within the free spaces or recesses of the holding structure, between sections of the holding structure and the insert and essentially over the outer surface of the holding structure is. The holding structure can provide a mechanical fastening between the insert and the coating. In use, the coating provides thermal and / or chemical shielding from the metallic shim and the retaining structure of the seal.
    权利要求:
    Claims (10)
    [1]
    1. A sealing arrangement (10) for arrangement within a sealing gap which is at least partially formed by adjacent turbomachine components in order to seal a gap extending between the components, the sealing arrangement comprising:a metallic insert (12) having a sealing surface (22) and a holding surface (24);a porous metallic support structure (14) connected to the support surface of the metallic insert; anda ceramic, glass or enamel coating (16) which extends over and within the porous metallic holding structure (14) so that the coating essentially covers the holding surface side of the metallic insert and the holding structure (14).
    [2]
    2. Sealing arrangement (10) according to claim 1, wherein the metallic insert (12) is a substantially metallic insert (12) made of solid material or wherein the metallic holding structure (14) is a mesh structure.
    [3]
    3. Sealing arrangement (10) according to one of the preceding claims, wherein the holding surface (24) of the metallic insert (12) and the metallic holding structure (14) have an outer protective coating which is designed to prevent oxidation of the respective metallic component.
    [4]
    4. Sealing arrangement (10) according to claim 3, wherein the portions of the metallic holding structure (14) which are not connected to the holding surface (24) of the metallic shim (12) extend away from and are connected to portions of the metallic holding structure ( 14), which are connected to the holding surface of the metallic shim (12).
    [5]
    5. Sealing arrangement (10) according to one of the preceding claims, wherein the coating is connected to the holding surface (24) of the insert (12) and the holding structure (14).
    [6]
    A method of forming a seal assembly (10) for use within a seal gap defined at least in part by adjacent turbomachine components to seal a gap extending between the components, the method comprising:Connecting at least a portion of a porous metallic support structure (14) to a metallic insert (12);Applying a ceramic, glass or enamel coating material to the porous metallic holding structure (14) so that the coating material covers the holding surface side of the metallic insert (12) and the holding structure (14) and has sections that lie between the holding surface (24) of the metallic Insert (12) and portions of the metallic support structure (14) are arranged; andCompaction of the ceramic, glass or enamel coating material in order to form a ceramic, glass or enamel coating (16) which is mechanically attached to the metallic insert (12) via the metallic holding structure (14).
    [7]
    7. The method according to claim 6, wherein the connection of at least a portion of the metallic holding structure (14) with the holding surface (24) of the metallic insert (12) diffusion bonding of at least a portion of the metallic holding structure (14) to the holding surface of the metallic insert (12) includes.
    [8]
    8. The method according to claim 6 or 7, wherein the application of ceramic, glass or enamel coating material to the porous metallic holding structure (14) comprises the application of a pourable ceramic composition with high viscosity by screen printing or contact application and / or wherein the application of ceramic -, glass or enamel coating material on the porous metallic holding structure (14) comprises the application of a glass or enamel-based composition in a paintable form by painting, dip coating or spray coating.
    [9]
    9. The method of claim 8, further comprising removing a portion of the ceramic composition applied to the support structure (14) with a scraper and wherein densifying the ceramic composition comprises curing and heat treating the applied ceramic composition.
    [10]
    10. Turbomachine having:a first turbine component (142) and a second turbine component (144) adjacent the first turbine component, the first and second turbine components defining at least a portion of a sealing gap that extends across a gap between the turbine components; anda seal assembly (10) disposed within the seal gap of the first and second turbine components and extending across the space therebetween, the seal assembly comprising:a metallic insert (12) having a sealing surface (22) and a holding surface (24);a porous metallic support structure (14) connected to the support surface of the metallic insert (12); anda ceramic, glass or enamel coating (16) which is present on and in the metallic holding structure (14) so that the coating essentially covers the holding surface side of the metallic insert (12) and the holding structure (14) and sections of the coating are arranged between the holding surface of the metallic insert (12) and sections of the metallic holding structure (14).
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    同族专利:
    公开号 | 公开日
    CH711017A2|2016-10-31|
    DE102016107429A1|2016-10-27|
    JP2016205389A|2016-12-08|
    JP6990967B2|2022-01-12|
    CN106065787A|2016-11-02|
    US20160312633A1|2016-10-27|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4209334A|1976-04-15|1980-06-24|Brunswick Corporation|Porous ceramic seals and method of making same|
    US4289446A|1979-06-27|1981-09-15|United Technologies Corporation|Ceramic faced outer air seal for gas turbine engines|
    US4289447A|1979-10-12|1981-09-15|General Electric Company|Metal-ceramic turbine shroud and method of making the same|
    US4433845A|1981-09-29|1984-02-28|United Technologies Corporation|Insulated honeycomb seal|
    US4639388A|1985-02-12|1987-01-27|Chromalloy American Corporation|Ceramic-metal composites|
    US5080934A|1990-01-19|1992-01-14|Avco Corporation|Process for making abradable hybrid ceramic wall structures|
    US5064727A|1990-01-19|1991-11-12|Avco Corporation|Abradable hybrid ceramic wall structures|
    US5104286A|1991-02-08|1992-04-14|Westinghouse Electric Corp.|Recirculation seal for a gas turbine exhaust diffuser|
    US5934687A|1997-07-07|1999-08-10|General Electric Company|Gas-path leakage seal for a turbine|
    EP1327703A1|2002-01-15|2003-07-16|Siemens Aktiengesellschaft|Coating system with a porous layer|
    US6652231B2|2002-01-17|2003-11-25|General Electric Company|Cloth seal for an inner compressor discharge case and methods of locating the seal in situ|
    US6733234B2|2002-09-13|2004-05-11|Siemens Westinghouse Power Corporation|Biased wear resistant turbine seal assembly|
    US7842335B2|2004-04-07|2010-11-30|General Electric Company|Field repairable high temperature smooth wear coating|
    US7527472B2|2006-08-24|2009-05-05|Siemens Energy, Inc.|Thermally sprayed conformal seal|
    US7798769B2|2007-02-15|2010-09-21|Siemens Energy, Inc.|Flexible, high-temperature ceramic seal element|
    US20130140774A1|2010-01-13|2013-06-06|Dresser-Rand Company|Annular seal apparatus and method|
    US8613451B2|2010-11-29|2013-12-24|General Electric Company|Cloth seal for turbo-machinery|
    US20120211943A1|2011-02-22|2012-08-23|General Electric Company|Sealing device and method for providing a seal in a turbine system|
    JP5654906B2|2011-03-07|2015-01-14|三井造船株式会社|In-pipe introduction device|
    US20140062034A1|2012-08-06|2014-03-06|General Electric Company|Gas path leakage seal for a turbine|
    EP3175154A4|2014-08-01|2018-04-25|The Patent Well LLC|A polyurea gasket and gasket tape and a method of making and using the same|US20190292920A1|2018-03-23|2019-09-26|United Technologies Corporation|Turbine component with a thin interior partition|
    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2019-05-31| NV| New agent|Representative=s name: FREIGUTPARTNERS IP LAW FIRM DR. ROLF DITTMANN, CH |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/695,649|US20160312633A1|2015-04-24|2015-04-24|Composite seals for turbomachinery|
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