US20160312633A1 - Composite seals for turbomachinery - Google Patents

Composite seals for turbomachinery Download PDF

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Publication number
US20160312633A1
US20160312633A1 US14/695,649 US201514695649A US2016312633A1 US 20160312633 A1 US20160312633 A1 US 20160312633A1 US 201514695649 A US201514695649 A US 201514695649A US 2016312633 A1 US2016312633 A1 US 2016312633A1
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US
United States
Prior art keywords
metallic
support structure
shim
coating
seal
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US14/695,649
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English (en)
Inventor
Edip Sevincer
Neelesh Nandkumar Sarawate
Anthony Marin
Venkat Subramanian Venkataramani
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General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US14/695,649 priority Critical patent/US20160312633A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SARAWATE, NEELESH NANDKUMAR, MARIN, ANTHONY, SEVINCER, EDIP
Priority to JP2016082606A priority patent/JP6990967B2/ja
Priority to CH00535/16A priority patent/CH711017B1/de
Priority to DE102016107429.2A priority patent/DE102016107429A1/de
Priority to CN201610258715.6A priority patent/CN106065787A/zh
Publication of US20160312633A1 publication Critical patent/US20160312633A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/28—Arrangement of seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/005—Selecting particular materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F05D2240/59—Lamellar seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/601—Fabrics
    • F05D2300/6012—Woven fabrics
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6033—Ceramic matrix composites [CMC]

Definitions

  • the present application relates generally to seals for reducing leakage, and more particularly to seals configured to operate within a seal slot to reduce leakage between adjacent stationary components of turbomachinery.
  • Hot combustion gases and/or cooling flows between turbomachinery components generally causes reduced power output and lower efficiency.
  • hot combustion gases may be contained within a turbine by providing pressurized compressor air around a hot gas path.
  • leakage of high pressure cooling flows between adjacent turbine components such as stator shrouds, nozzles, and diaphragms, inner shell casing components, and rotor components
  • Turbine efficiency thus can be improved by reducing or eliminating leakage between turbine components.
  • seal slots of turbine components are formed by corresponding slot portions in adjacent components (a seal positioned therein thereby extending across a junction between components).
  • Misalignment between these adjacent components such as resulting from thermal expansion, manufacturing, assembly and/or installation limitations, etc., produces an irregular seal slot contact surface that may vary in configuration, shape and/or magnitude over time.
  • Such irregularities in the seal slot contact surface allow for leakage across a slot seal positioned within the seal slot if the seal does not flex, deform or otherwise account for such irregularities.
  • many conventional metallic shims that account for such irregular seal slot contact surfaces due to misalignment of adjacent turbine components may not adequately withstand increases in operating temperatures of turbines.
  • composite turbomachinery component junction seals configured for use in typical turbine seal slots that withstand the increasingly higher operating temperatures of turbines and conform to irregularities in the seal slot contact surface would be desirable.
  • the present disclosure provides a seal assembly for positioning within a seal slot formed at least partially by adjacent turbomachinery components to seal a gap extending between the components.
  • the seal assembly includes a metallic shim, a porous metallic support structure, and a ceramic, glass or enamel coating.
  • the metallic shim includes a sealing surface and a support surface.
  • the porous metallic support structure is bonded to the support surface of the metallic shim.
  • the ceramic, glass or enamel coating extends over and within the porous metallic support structure such that the coating substantially covers the support surface side of the metallic shim and the support structure. Portions of the coating are positioned between the support surface of the metallic shim and portions of the metallic support structure.
  • portions of the coating may be positioned between the support surface of the metallic shim and portions of the metallic support structure in a direction extending away from the support surface to mechanically couple the coating to the metallic shim via the metallic support structure.
  • the direction extending away from the support surface may be substantially normal to the support surface.
  • the metallic shim may be a substantially solid metallic shim.
  • the coating may be chemically bonded to the support structure.
  • at least one of the support surface of the metallic shim and the metallic support structure may include a protective outer coating configured to prevent oxidation of the respective metallic component.
  • the metallic support structure may be diffusion bonded to the metallic shim via at least one braze.
  • the metallic support structure may be a mesh structure.
  • portions of the coating may be positioned between the support surface of the metallic shim and portions of the metallic support structure that are bonded to the support surface of the metallic shim.
  • portions of the coating may be positioned between the support surface of the metallic shim and portions of the metallic support structure that are not bonded to the support surface of the metallic shim. In some such embodiments, portions of the metallic support structure that are not bonded to the support surface of the metallic shim may extend from or are coupled to portions of the metallic support structure that are bonded to the support surface of the metallic shim.
  • the coating may be bonded to at least one of the support surface of the shim and the support structure.
  • the seal assembly may further include a second porous metallic support structure bonded to the sealing surface of the shim, and a second ceramic, glass or enamel coating extending over and within the second porous metallic support structure such that the second coating substantially covers the sealing surface side of the metallic shim and the second support structure, and portions of the second coating may be positioned between the sealing surface of the metallic shim and portions of the second metallic support structure.
  • 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 a gap extending between the components.
  • the method includes bonding at least one portion of a porous metallic support structure to a metallic shim.
  • the method further includes applying ceramic, glass or enamel coating material to the porous metallic support structure such that the coating material overlies the support surface side of the metallic shim and the support structure, and includes portions that are positioned between the support surface of the metallic shim and portions of the metallic support structure.
  • the method also includes densifying the ceramic, glass or enamel coating material to form a ceramic, glass or enamel coating mechanically fixed to the metallic shim via the metallic support structure.
  • bonding at least one portion of the metallic support structure to the support surface of the metallic shim may include diffusion bonding at least one portion of the metallic support structure to the support surface of the metallic shim.
  • applying ceramic, glass or enamel coating material to the porous metallic support structure may comprise applying a high viscosity castable ceramic composition by screen printing or toweling.
  • the method may further include removing a portion of the ceramic composition applied to the support structure via a doctor blade, and wherein densifying the ceramic composition comprises curing and heat treating the applied ceramic composition.
  • applying ceramic, glass or enamel coating material to the porous metallic support structure may comprise applying a glass or enamel based composition in a paintable form by painting, dip coating or spray coating.
  • densifying the glass or enamel based composition may comprise drying and heat treating the applied glass or enamel based composition.
  • the present disclosure provides a turbomachine that includes a first turbine component and a second turbine component adjacent the first turbine component, the first and second turbine components forming at least a portion of a seal slot extending across a gap between the turbine components.
  • the turbomachine further includes a seal positioned within the seal slot of the first and second turbine components and extending across the gap therebetween.
  • the seal comprises a metallic shim, a porous metallic support structure, and a ceramic, glass or enamel coating.
  • the metallic shim includes a sealing surface and a support surface.
  • the porous metallic support structure is bonded to the support surface of the metallic shim.
  • the ceramic, glass or enamel coating is provided on and within the metallic support structure such that the coating substantially covers the support surface side of the metallic shim and the support structure, and portions of the coating are positioned between the support surface of the metallic shim and portions of the metallic support structure.
  • the ceramic, glass or enamel coating of the seal may be positioned against a first side of the seal slot that is collectively formed by a first side of the first turbine component and a first side of the second turbine component.
  • the metallic shim is a substantially solid metallic shim
  • the porous metallic support structure is a metallic mesh structure.
  • portions of the coating may be positioned between the support surface of the metallic shim and portions of the metallic support structure in a direction extending substantially normal to the support surface to mechanically couple the coating to the metallic shim via the metallic support structure.
  • FIG. 1 is a cross-sectional view of a portion of a first exemplary slot seal assembly according to the present disclosure
  • FIG. 2 is a perspective view of the exemplary slot seal of FIG. 1 partially assembled to illustrate the arrangement of the shim, support structure and coating portions;
  • FIG. 3 is a perspective view of the shim and support structure sub-assembly of the exemplary slot seal of FIG. 1 ;
  • FIG. 4 is an enlarged perspective view of a portion of the shim and support structure sub-assembly of FIG. 3 ;
  • FIG. 5 is an enlarged cross-sectional view of a portion of the shim and support structure sub-assembly of FIG. 4 ;
  • FIG. 6 is a side cross-sectional view of an exemplary slot seal assembly positioned within a seal slot to seal an exemplary junction between turbine components;
  • FIG. 7 is a side cross-sectional view of an exemplary slot seal assembly.
  • Composite turbomachinery component junction seals configured for use in turbine seal slots (e.g., composite turbine slot seals), and methods of manufacturing and using same, according to the present disclosure are configured to withstand the relatively high operating temperatures of turbines including CMC components and/or conform to irregularities in the seal slot contact surface.
  • the composite slot seals are configured to substantially prevent chemical interaction and substantially limit thermal interaction of metallic components of the composite slot seals with the hot gas flow/leakage and/or the seal slot itself.
  • the composite slot seals provided herein allow for use in high temperature turbine applications.
  • the composite slot seals of the present disclosure are configured to conform to irregularities on the seal slot contact surface to decrease leakage due to seal slot surface misalignment and/or roughness.
  • the exemplary seal 10 may be a seal assembly including at least one shim or plate 12 , at least one support structure or layer 14 and at least one coating or coating layer 16 coupled to one another.
  • the shim 12 may be effective in substantially preventing the passage of substances therethrough.
  • the shim 12 may be substantially solid or otherwise substantially impervious to at least one of gases, liquids and solids at pressures and temperatures produced in turbo machinery.
  • the shim 12 may also provide flexibility at pressures and temperatures produced in turbomachinery to accommodate skews or offsets in slot surfaces in the thickness T 1 direction.
  • the shim 12 is a substantially solid plate-like metallic member.
  • the shim 12 may be a high temperature metallic alloy or super alloy.
  • the shim 12 (and/or the support structure 14 ) may be made from stainless steel or a nickel based alloy (at least in part), such as nickel molybdenum chromium alloy, Haynes 214 , or Haynes 214 with an aluminum oxide coating.
  • the shim 12 may be made of a metal with a melting temperature of at least 1,500 degrees Fahrenheit, and more preferably at least 1800 degrees Fahrenheit. In some embodiments, the shim 12 may be made of a metal with a melting temperature of at least 2,200 degrees Fahrenheit.
  • An exterior sealing surface or side 22 of the shim 12 that substantially opposes the support structure 14 , as shown in FIGS. 1-5 , may be substantially planar (in a neutral state).
  • the exterior sealing surface 22 of the shim 12 may be configured to engage or interact with a cooling high pressure air flow flowing through at least one gap or joint between at least first and second components forming a seal slot (at least in part) so that the seal 10 is forced or pressed against sealing surfaces of the first and second components in the seal slot to substantially prevent gases, liquids and/or solids from migrating through the gap or joint.
  • At least one of the shim 12 and the coating 16 may be substantially impervious to liquids, gases and/or solids at pressures experienced in turbomachinery such that the seal 10 provides at least a low leakage rate past the seal slot.
  • the support structure 14 may be coupled to a support surface or side 24 of the shim 12 that substantially opposes the sealing surface 22 .
  • the support structure 14 may be metallic, such as metallic material with the characteristics described above with respect to the shim 12 .
  • the shim 12 and the support structure 14 may be formed of the same or substantially similar metallic material, and thereby include the same or substantially similar coefficient of thermal expansion (hereinafter CTE).
  • CTE coefficient of thermal expansion
  • the shim 12 and the support structure 14 need not be formed of the same or substantially similar material, or include the same or substantially the same CTE.
  • the shim 12 and the support structure 14 be configured such that any difference in CTE therebetween does not fracture, break or otherwise render a diffusion bond therebetween, as described further below, ineffective due to cyclic thermal loading of the seal 10 during use in turbomachinery.
  • the CTE of the shim 12 and the CTE of the support structure 14 may differ only to such an extent that the diffusion bond between the shim 12 and the support structure 14 is not rendered ineffective by cyclic thermal loading of the seal 10 during use in turbomachinery.
  • the material of the shim 12 and the support structure 14 may differ, but the shim 12 and the support structure 14 may be configured such that a diffusion bond therebetween is not damaged or rendered ineffective when the seal 10 is subjected to cyclic thermal loading when utilized in a seal slot of a turbine.
  • the support structure 14 may be a support structure, member or assembly that is capable of chemically bonding or fusing (e.g., via a diffusion bond) to the support surface 24 of the shim 12 , and capable of securely mechanically coupling or affixing with the coating 16 (which is chemically bonded to the shim 12 ). In this way, the coating 16 may be securely mechanically coupled or affixed to the shim 12 via the support structure 14 .
  • the support structure 14 may be a substantially porous metallic structure (as opposed to the substantially non-porous shim 12 ) that includes cavities or voids for holding portions of the coating 16 therein.
  • porous is used herein, with respect to the support structure 14 , to describe a structure, member(s) or mechanism than includes pores, channels, voids, gaps, cavities or other interior spaces that, individually and/or collectively, allow the coating 16 to extend into the support structure 14 from the top or outer surface of the support structure 14 in a direction extending towards the shim 12 and that at least some portions of the coating 16 are positioned between the sealing surface 24 of the shim 12 and at least a portion of the support structure 14 in a direction extending at least generally away from the sealing surface 24 of the shim 12 , such as substantially normal to the sealing surface 24 of the shim 12 .
  • the support structure 14 may be a porous metallic mesh, lattice, honeycomb or woven-type structure with interlocked, interwoven or intermingled members, fibers or portions, as shown in FIGS. 1-5 .
  • a metallic mesh-type support structure 14 may include metallic members or fibers that include first portions that are fused or bonded to the support surface 24 of the shim 12 and second portions that are not bonded or fused to the shim 12 and, potentially, spaced from the support surface 24 of the shim 12 .
  • the support structure 14 may be bonded or fused to the shim 12 , with the remaining fraction or portion of the support structure 14 being coupled to (e.g., mechanically attached) or extending from the bonded or fused portion.
  • the shim 12 and at least a portion of the support structure 14 may be bonded or fused to each other such that their attachment is capable of effectively withstanding the temperature, pressure and other conditions experienced in a seal slot of a turbine.
  • the shim 12 and at least a portion of the support structure 14 may be bonded or fused in such a manner that creates a solid state chemical bond therebetween.
  • the shim 12 and at least a portion of the support structure 14 may be solid state welded to each other, such as via diffusion bonding.
  • the shim 12 and the support structure 14 may be diffusion bonded to each other by at least one high temperature braze.
  • the shim 12 and/or the support structure 14 of the shim 10 may include one or more protective coating (not shown) applied or positioned over or on an exterior surface thereof.
  • 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.
  • at least a portion of the outer surface of the shim 12 (e.g., the support surface 24 ) and/or the support structure 14 may be defined by a protective coating overlying the underlying metallic component (i.e., the metallic shim 12 or the metallic support structure 14 ).
  • the portion or portions of the shim 12 and/or the support structure 14 which are diffusion bonded to each other may include the protective coating or layer.
  • the support structure 14 may be bonded to protective coating overlying on the shim 12 and forming the support surface 24 .
  • the protective coating(s) of the metallic shim 12 and/or the metallic support structure 14 may be configured to substantially prevent or retard oxidation of the underlying metallic component.
  • the protective coating(s) of the metallic shim 12 and/or the metallic support structure 14 may include or substantially comprise an oxide, such as chromium oxide or alumina oxide.
  • the at least one coating 16 may be applied to the seal 10 to protect the shim 12 and support structure 14 .
  • the coating 16 may be applied to the seal 10 such that the coating 16 substantially covers or overlies at least the support structure 14 and the support surface 24 of the shim 12 (i.e., the coating extends over and into the support structure 14 of the seal 10 and thereby over the support surface 24 of the shim 12 ).
  • the coating 16 may substantially fill the pores or voids of the support structure 14 , and may be substantially non-porous (as opposed to the support structure 14 ).
  • the coating 16 may also cover or overlie the support surface 24 side and the side edges of the seal 10 such that the sealing surface 22 side of the seal 10 is the only side or edge of the seal 10 not covered by, or contains, the coating 16 .
  • the coating 16 may be one or more coating material that is/are effective in substantially preventing chemical interaction and substantially limiting thermal interaction of at least the metallic shim 12 (and, potentially, the support structure 14 ) when the seal 10 is utilized in a seal slot of a turbine, such as a seal slot formed by components of a high temperature gas turbine, such as stator components.
  • the coating 16 on the support structure 14 may be configured to sealingly engage first and second sealing surfaces of first and second components that form a seal slot to substantially prevent gases, liquids and/or solids from migrating through a gap or joint between the first and second components.
  • the coating 16 may be effective in substantially preventing 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 seal slot of a turbine.
  • the coating 16 allows for metallic-based seals, such as the seal 10 with the one or more metallic shim 12 (and, potentially, the support structure 14 ), to be utilized in high temperature gas turbine applications.
  • the coating 16 may be a ceramic, glass or enamel material that is effective in protecting (e.g., preventing or reducing oxidation, silicide formation, thermal creep, wear, etc.) at least the metallic shim 12 and/or the support structure 14 .
  • the coating 16 may be formed of a crystalline, glassy or glass ceramic composite.
  • the coating 16 may include metal oxides, nitrides or oxynitrides.
  • the coating 16 may include stabilized or unstabilized zirconia, alumina, titania, alkaline earth and/or rare earth zirconates, titanates, aluminates, tantalates and niobates, tungstates, molybdates, silicates borates, phosphates, silicon nitride, silicon carbide, intermetallic compounds such as MAX phase materials (Ti2AlC) and combinations thereof.
  • the coating 16 may be formed of a high temperature porceain enamel composition.
  • the coating 16 may include alkali/alkali earth alumino boro phosphor silicate glasses and fillers.
  • the coating 16 (whether a ceramic, glass or enamel material) may include the required high temperature melt and flow properties to provide optimum stability and compliance at the operating conditions of the seal 10 .
  • the coating 16 (and/or the protective coating described herein) may be formed on the metallic shim 12 (and/or the metallic support structure 14 ) by, at least in part, the diffusion of selected species into, and/or reaction with, the metallic shim 12 (and/or the metallic support structure 14 ) to form metal silicide(s) and/or at least one oxide layer on the metallic shim 12 (and/or the metallic support structure 14 ).
  • the metal silicide(s) formed by the diffusion/reaction of the selected species and the metallic shim 12 (and/or the metallic support structure 14 ) may be resistant to oxidation.
  • the one or more oxide layer formed by the diffusion/reaction of the selected species and the metallic shim 12 (and/or the metallic support structure 14 ) may include negligible oxygen diffusion capacity therethrough, thus protecting the metallic shim 12 (and/or the metallic support structure 14 ).
  • Si may be utilized and diffused into, and/or reacted with, the metallic shim 12 (and/or the metallic support structure 14 ).
  • the selected species for forming the metal silicide(s) and/or the at least one oxide layer may include Al, Si, B, alloys thereof, or combinations thereof.
  • the metallic shim 12 (and/or the metallic support structure 14 ) may be formed of or include a refractory metal, such as Mo, W, alloys thereof, or combinations thereof, and 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 .
  • the metal silicide(s) and/or the at least one oxide layer may be formed by reaction with a packed bed of the selected species (e.g., in a powder or like form) and the metallic shim 12 (and/or the metallic support structure 14 ) at high temperatures (i.e., a pack siliciding/oxide layer method).
  • the metal silicide(s) and/or the at least one oxide layer on the metallic shim 12 (and/or the metallic support structure 14 ) may be formed through one or more coating of the selected species (e.g., metallic elements/alloys) through vapor phase deposition (e.g., chemical vapor deposition (CVD) or physical vapor deposition (PVD)), followed by chemical and/or heat treatment.
  • the selected species e.g., metallic elements/alloys
  • vapor phase deposition e.g., chemical vapor deposition (CVD) or physical vapor deposition (PVD)
  • CVD chemical vapor deposition
  • PVD physical vapor deposition
  • the ceramic coating 16 may be formed from a high viscosity castable composition, such as a castable cement (e.g., COTRONICS 904 or 989).
  • a high viscosity castable composition such as a castable cement (e.g., COTRONICS 904 or 989).
  • the high viscosity castable composition may be applied on the bonded shim 12 and the support structure 14 by screen printing or toweling. After the castable composition of the coating 16 is applied to the bonded shim 12 and the support structure 14 , excess coating 16 material may be removed by doctor blading to a desired or required thickness on the seal 10 (e.g., a particular amount of coating castable composition on the top or above the outer surface of the support structure 14 ).
  • the applied and bladed “green” coating may be further processed to densify and chemically bond to the coating 16 material to the bonded shim 12 and the support structure 14 by curing and heat treating.
  • the curing may set the coating 16 material, and the heat treating may densify the coating 16 material to a closed porosity state to, ultimately, form the coating 16 on the bonded shim 12 and the support structure 14 .
  • the coating 14 may be bonded to the metallic shim 12 itself or to a protective coating overlying the metallic shim 12 .
  • the coating 16 may be formed from glass or enamel based compositions in a paintable form.
  • the paintable form glass or enamel based compositions may include a relatively low viscosity that allows the glass or enamel based compositions to be painted on the bonded shim 12 and the support structure 14 , or the bonded shim 12 and the support structure 14 may be dip or spray coated with the glass or enamel based compositions.
  • the glass or enamel based compositions may include a solvent or the like to decrease the viscosity of the compositions. After the glass or enamel based compositions are applied to the bonded shim 12 and the support structure 14 , the compositions may be dried, such as to remove solvents from the applied compositions.
  • the compositions may be heat treated to form a coating 16 of a substantially dense, smooth, glassy coating that is chemically bonded and mechanically coupled to the shim 12 and the support structure 14 .
  • the coating 16 composition may be formulated as precursor.
  • the coating 16 composition be formed of a gellable sol from precursor slats such as nitrates, carboxylates, alkoxides with a certain fraction added as fillers.
  • the gellable sol may be applied to bonded shim 12 and the support structure 14 to form the coating 16 by any of the aforementioned processes.
  • the coating 16 (whether it be ceramic, glass or an enamel) may be applied to the metallic shim 12 and the metallic support structure 14 such that the coating 16 is, at least initially, chemically bonded or coupled directly to the metallic shim 12 (e.g., over or on the support surface 24 of the metallic shim 12 ) and/or the metallic support structure 14 .
  • the metallic shim 12 and/or metallic support structure 14 may include a protective coating.
  • the coating 16 may be chemically bonded to the protective coating (thereby indirectly chemically bonded to the metallic shim 12 and/or metallic support structure 14 ).
  • the coating 16 may substantially fill voids of the support structure 14 (including any or spaces between the support structure 14 and the shim 12 , as explained further below) and extend over the top or outer surface of the support structure 14 (to thereby cover the support surface 22 of the shim 12 ).
  • the support structure 14 may be chemically bonded to the shim 12 and configured to mechanically couple with the coating 16 .
  • the coating 16 which is effective in thermally and chemically insulating the metallic shim 12 , may be at least initially both chemically bonded and mechanically fixed to the metallic shim 12 and the metallic support structure 14 .
  • the support structure 14 may be effective in maintaining the attachment or coverage of the coating 16 over the metallic shim 12 —such as sides, edges or portions of at least the metallic shim 12 that may be exposed to during use of the seal 10 in a seal slot of a turbine.
  • the chemical bond or coupling between a ceramic or glass coating 16 and the metallic shim 12 and metallic support structure 14 (or a protective coating thereon) may not withstand the thermal cycling of the shim 12 (occurring during use of the shim 12 , for example) due to the thermal mismatch between the ceramic or glass coating 16 and the metallic shim 12 and metallic support structure 14 .
  • the metallic support structure 14 may be bonded or fused to the metallic shim 12 and the coating 14 may be provided at least throughout or within voids of the support structure 14 . More specifically, however, the coating 14 may also extend or be positioned, at least partially, between the shim 12 and portions of the support structure 14 in a direction extending at least generally away from the sealing surface 22 of the shim 12 . In some embodiments, the coating 14 may be positioned, at least partially, between the shim 12 and the individual members, fibers or portions of the support structure 14 (or portions thereof) in a direction extending substantially normal to the support surface 24 of the shim 12 .
  • the coating 14 thereby may be provided or extend substantially about fibers, members or portions of the support structure 14 (but for the portions thereof that are fused or bonded to the shim 12 ). In this way, because at least some of the fibers, members or portions of the support structure 14 are bonded or fused to the metallic shim 12 and portions of the coating 14 are positioned between the shim 12 and portions of the support structure 14 , the support structure 14 provides a mechanical attachment of the coating 14 to the metallic shim 12 that prevents the coating 14 from detaching or decoupling from the shim 12 .
  • the positioning of the coating 16 substantially about the fibers, members or portions of the support structure 14 e.g., over the outer surface of the support surface 24 and between portions of the support surface 24 and the shim 12 ) provides a mechanical attachment that prevents the coating 16 from becoming detached or decoupled from the metallic shim 12 (via the metallic support structure 14 ).
  • portions of the coating 14 may be positioned between the metallic shim 12 and portions of the support structure 14 that are spaced from the metallic shim 12 (e.g., portions that are not bonded or fused to the metallic shim 12 , but rather extend from, or are coupled to, portions that are that are bonded or fused to the metallic shim 12 ). Portions of the coating 14 may also be positioned between the metallic shim 12 and portions of the support structure 14 that are bonded or fused to the metallic shim 12 . As shown in FIGS.
  • the fibers, members or portions of the support structure 14 that are bonded or fused to the metallic shim 12 may include or define a shape that provides or forms a space or void 26 between the fibers, members or portions of the support structure 14 and the support surface 24 of the shim 12 .
  • the fibers, members or portions of the support structure 14 that are bonded or fused to the support surface 24 of the shim 12 are substantially circular in cross-section such that a space or void 26 is formed between the respective fibers, members or portions of the support structure 14 and the support surface 24 of the shim 12 .
  • the support structure 14 may be utilized.
  • the shape or configuration of the fibers, members or portions of the support structure 14 may allow the coating 14 to be positioned between bonded portions of the support structure 14 and the sealing surface or side 24 of the shim 12 (e.g., in a direction extending generally away from, or substantially normal to, the sealing surface 24 ).
  • FIG. 6 illustrates a cross-sectional view of an exemplary slot seal assembly 110 positioned within an exemplary seal slot to seal an exemplary junction between turbine components, such as stator components.
  • the exemplary slot seal assembly 110 is substantially similar to the exemplary slot seal assembly 10 of FIGS. 1-5 described above, and therefore like reference numerals preceded with “1” are used to indicate like aspects or functions, and the description above directed to such aspects or functions (and the alternative embodiments thereof) equally applies to the exemplary slot seal assembly 110 .
  • FIG. 1 illustrates a cross-sectional view of an exemplary slot seal assembly 110 positioned within an exemplary seal slot to seal an exemplary junction between turbine components, such as stator components.
  • the exemplary slot seal assembly 110 is substantially similar to the exemplary slot seal assembly 10 of FIGS. 1-5 described above, and therefore like reference numerals preceded with “1” are used to indicate like aspects or functions, and the description above directed to such aspects or functions (and the alternative embodiments thereof) equally applies to the exemplary slot seal assembly 110 .
  • FIG. 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 slot seal 110 installed in the seal slot 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 nozzles of first and second stators, respectively.
  • the first and second components 142 , 144 may be any other adjacent turbomachinery components, such as stationary or translating and/or rotating (i.e., moving) turbine components.
  • the exemplary composite slot seals 10 , 110 described herein may be configured for, or used with, any number or type of turbomachinery components requiring a seal to reduce leakage between the components.
  • the cross-section of the exemplary components 142 , 144 and exemplary composite slot seal 110 illustrated in FIG. 6 is taken along a width of the structures, thereby illustrating an exemplary width and thickness/height of the structures.
  • the relative width, thickness and cross-sectional shape of the structures illustrated in FIG. 6 is exemplary, and the structures may include any other relative width, thickness and cross-sectional shape.
  • the length of the structures (extending in-out of the page of FIG. 6 ) may be any length, and the shape and configuration of the structures in the length direction may be any shape or configuration.
  • a plurality of components may form a plurality of seal slots that are in communication with one another.
  • a plurality of turbine components may be circumferentially arranged such that seal slots formed thereby are also circumferentially arranged and in communication with one another.
  • the slot seals 10 , 110 , 210 according to the present disclosure may be configured to span a plurality of seal slots to seal a plurality of gaps or junctions and thereby reduce leakage between a plurality of turbine components.
  • the first and second adjacent turbine components 142 , 144 may be spaced from one another such that a junction, gap or pathway 190 extends between the first and second adjacent components 142 , 144 , such as stators. Such a junction 190 may thereby allow flow, such as airflow, between the first and second turbine components 142 , 144 .
  • the first and second turbine components 142 , 144 may be positioned between a first airflow 150 , such as a cooling airflow, and a second airflow 160 , such as hot combustion airflow.
  • airflow is used herein to describe the movement of any material or composition, or combination of materials or compositions, translating through the junction 190 between the first and second turbine components 142 , 144 .
  • the first and second adjacent components 142 , 144 may each include a slot, as shown in FIG. 6 .
  • the first component 142 includes a first seal slot 170 and the second component includes a second seal slot 180 .
  • the first and second seal slots 170 , 180 may have any size, shape, or configuration capable of accepting a seal therein. For example, as shown in the illustrated exemplary embodiment in FIG.
  • the first and second seal slots 170 , 180 may be substantially similar to one another and positioned in a mirrored relationship to define together a net slot or cavity that extends from within the first component 142 , across the junction 190 , and into the second component 144 .
  • the pair of first and second seal slots 170 , 180 may jointly form a cavity or seal slot to support opposing portions of a seal such that the seal 110 passes through the junction 190 extending between the adjacent components 142 , 144 .
  • the first and second seal slots 170 , 180 may be configured such that they are substantially aligned (e.g., in a mirrored or symmetric relationship). However, due to manufacturing and assembly limitations and/or variations, as well as thermal expansion, movement and the like during use, the first and second seal slots 170 , 180 may be skewed, twisted, angled or otherwise misaligned. In other scenarios, the first and second seal slots 170 , 180 may remain in a mirrored or symmetric relationship, but the relative positioning of the first and second seal slots 170 , 180 may change (such as from use, wear or operating conditions).
  • the term “misaligned” is used herein to encompass any scenario wherein seal slots have changed relative positions or orientations as compared to a nominal or initial position or configuration.
  • the exemplary seal 110 is preferably flexible to account for the misalignment and maintain sealing contact of the coating 116 with the first and second seal slots 170 , 180 to effectively cut off or eliminate the junction 190 extending between the first and second turbine components 142 , 144 to thereby reduce or prevent the first and second airflows 150 , 160 from interacting. More particularly, as shown in FIG.
  • the first and second airflows 150 , 160 may interact with the junction 190 such that the first airflow 150 is a “driving” airflow that acts against the exterior sealing surface 122 of the shim 112 of the seal 110 to force the coating 116 of the seal 110 against first side surfaces 135 , 145 of the first and second seal slots 170 , 180 , respectively.
  • the seal 110 (and/or coating 166 ) may be preferably sufficiently flexible to deform (e.g., elastically) as a result of the forces applied by the first airflow 150 (e.g., above that applied by the second airflow 160 ) to account for any misalignment between the first and second seal slots 170 , 180 , but sufficiently stiff to resist being “folded” or otherwise “pushed” into the junction 190 .
  • the exemplary seal 110 may be preferably sufficiently flexible, but yet sufficiently stiff, to maintain sealing engagement of the coating 116 of the shim 112 with the first side surfaces 135 , 145 via the forces of the first airflow 150 .
  • the metallic shim 112 , metallic support structure 114 , and the coating 116 may be configured to conform to irregularities on the seal slot contact surfaces 135 , 145 during use of the turbine.
  • the coating 116 may be a glass insulating coating with a transition temperature (Tg) similar to that of the operating temperatures of the turbine/seal 110 so that the glass coating 116 becomes soft or deformable at operating temperatures to facilitate deformation an contouring of at least the coating 116 to the first side surfaces 135 , 145 .
  • Tg transition temperature
  • the exemplary seal 110 may preferably be sufficiently stiff to satisfy assembly requirements.
  • the size of the seal 110 may be any size, but may be dependent upon, or at least related to, the components 142 , 144 in which the seal 110 is installed.
  • the thickness T 1 of the exemplary seal 110 may be less than the thickness T 2 of the first and second seal slots 170 , 180 , and thereby the thickness T 2 of the net slot created by the first and second seal slots 170 , 180 when the first and second adjacent components 142 , 144 are assembled.
  • the thickness T 1 of the exemplary seal 110 may preferably be within the range of about 0.01 inches to about 1 ⁇ 4 inches, and more preferably within the range of about 0.05 inches to about 0.1 inches.
  • the width W 1 of the seal 110 may be less than the width W 2 of the net slot created by the first and second slots 170 , 180 of the first and second components 142 , 144 , respectively, and the gap 190 between the components 142 , 144 when the components 142 , 144 are installed adjacent to one another.
  • the width W 1 of the exemplary seal 110 may preferably be within the range of about 0.125 inches to about 0.75 inches.
  • the seal 110 may be positioned and arranged within the seal slot (i.e., the first and second seal slots 170 , 180 ) such that the first or cooling airflow 150 acts against the exterior sealing surface 122 of the shim 112 to force the coating 116 against the first side surfaces 135 , 145 of the first and second seal slots 170 , 180 . Due to the impervious nature of the shim 112 and/or the coating 116 , the seal 110 thereby prevent the cooling airflow 150 from migrating through the gap 190 and into the second or hot combustion airflow 160 . Further, the coating 116 protects the metallic shim 112 from the high temperatures of the combustion airflow 160 .
  • At least the shape and configuration of the exterior or sealing surface of the coating 116 of the seal 110 may be related to the shape and configuration of the slots 142 , 144 in which the seal 110 is installed.
  • the shape and configuration of at least the exterior or sealing surface of the coating 116 of the seal 110 such as the contour, surface texture, etc., may be configured to ensure sealing engagement with the first and second seal slots 170 , 180 in which the seal 110 is installed. For example, in the illustrated example in FIG.
  • the exterior or sealing surface of the coating 116 of the seal 110 may be substantially smooth and planar to substantially abut or otherwise substantially engage the substantially planar first side surfaces 135 , 145 of the first and second seal slots 170 , 180 to effectively prevent or reduce leakage of the first airflow 150 between the seal assembly 110 and the first side surfaces 135 , 145 of the first and second seal slots 170 , 180 and, ultimately, into the second or hot combustion airflow 160 (and to also protect the metallic shim 12 from the high temperatures of the hot combustion airflow 160 ).
  • the shape and configuration of at least the exterior or sealing surface of the coating 116 of the seal 110 may be shaped or configured differently than that of the corresponding sealing surfaces of the first and second seal slots 170 , 180 (such as the exemplary first side surfaces 135 , 145 of the first and second seal slots 170 , 180 illustrated in FIG. 6 ).
  • FIG. 7 illustrates a cross-sectional view of another exemplary slot seal assembly 210 according to the present disclosure.
  • the exemplary slot seal assembly 210 is substantially similar to the exemplary slot seal assemblies 10 and 110 of FIGS. 1-6 described above, and therefore like reference numerals preceded with “2” are used to indicate like aspects or functions, and the description above directed to such aspects or functions (and the alternative embodiments thereof) equally applies to the exemplary slot seal assembly 210 .
  • slot seal assembly 210 differs from seal assemblies 10 and 110 in that the seal 210 is symmetrical in the thickness direction. As such, seal assembly 210 provides for ease of installation or assembly of the seal 210 in a turbine seal slot as the seal 210 does not need to be particularly oriented in the thickness direction.
  • both the sealing surface 222 and the support surface 224 sides of the metallic shim 12 include a metallic support structure 214 bonded thereto.
  • the support structure may 214 may extend over one or more side edges of the metallic shim 212 and onto the sealing surface 222 and the support surface 224 .
  • both the support structure 214 bonded to the sealing surface 222 and the support structure 214 bonded to the support surface 224 of the metallic shim 212 include the coating 216 applied thereto.
  • the coating 216 may extend over one or more side edges of the metallic shim 212 and onto/into the support structure 214 bonded to the sealing surface 222 and the support structure 214 bonded to the support surface 224 .
  • the coating 216 applied on and in the support structure 214 that is bonded to the sealing surface or side 222 of the shim 210 may insulate or protect the sealing surface side 22 of the shim 212 (such as from the cooling airflow 150 discussed above with respect to FIG. 6 ).
  • seal assemblies disclosed herein provide low leakage rate similar to that possible with tradition slot seals, such as solid metal shim seals, while eliminating the silicide formation, oxidation, thermal creep and/or increased wear concerns when applied to modern high temperature turbomachinery. Moreover, the seal assemblies disclosed herein may be less susceptible to manufacturing variations as compared to existing seals. The seal assemblies disclosed herein thus reduce leakage with low manufacturing and operational risks, and are applicable in both OEM and retrofit applications.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Gasket Seals (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
US14/695,649 2015-04-24 2015-04-24 Composite seals for turbomachinery Abandoned US20160312633A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US14/695,649 US20160312633A1 (en) 2015-04-24 2015-04-24 Composite seals for turbomachinery
JP2016082606A JP6990967B2 (ja) 2015-04-24 2016-04-18 ターボ機械用の複合シール
CH00535/16A CH711017B1 (de) 2015-04-24 2016-04-21 Dichtungsanordnung für Turbomaschinen.
DE102016107429.2A DE102016107429A1 (de) 2015-04-24 2016-04-21 Verbunddichtungen für Turbomaschinen
CN201610258715.6A CN106065787A (zh) 2015-04-24 2016-04-25 用于涡轮机的复合密封件

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US14/695,649 US20160312633A1 (en) 2015-04-24 2015-04-24 Composite seals for turbomachinery

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US20160312633A1 true US20160312633A1 (en) 2016-10-27

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US14/695,649 Abandoned US20160312633A1 (en) 2015-04-24 2015-04-24 Composite seals for turbomachinery

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US (1) US20160312633A1 (de)
JP (1) JP6990967B2 (de)
CN (1) CN106065787A (de)
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US20190292920A1 (en) * 2018-03-23 2019-09-26 United Technologies Corporation Turbine component with a thin interior partition

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US20190292920A1 (en) * 2018-03-23 2019-09-26 United Technologies Corporation Turbine component with a thin interior partition
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JP2016205389A (ja) 2016-12-08
JP6990967B2 (ja) 2022-01-12
CH711017B1 (de) 2021-03-31
CN106065787A (zh) 2016-11-02
CH711017A2 (de) 2016-10-31
DE102016107429A1 (de) 2016-10-27

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