EP3276039A1 - Procédés et appareil de fabrication de bande de frottement abradable de joint d'air externe - Google Patents

Procédés et appareil de fabrication de bande de frottement abradable de joint d'air externe Download PDF

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Publication number
EP3276039A1
EP3276039A1 EP17183877.4A EP17183877A EP3276039A1 EP 3276039 A1 EP3276039 A1 EP 3276039A1 EP 17183877 A EP17183877 A EP 17183877A EP 3276039 A1 EP3276039 A1 EP 3276039A1
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Prior art keywords
particulate
coating
location
micrometers
plasma
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German (de)
English (en)
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EP3276039B8 (fr
EP3276039B1 (fr
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Christopher W. Strock
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RTX Corp
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United Technologies Corp
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    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/134—Plasma spraying
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
    • B05B7/00—Spraying apparatus for discharge of liquids or other fluent materials from two or more sources, e.g. of liquid and air, of powder and gas
    • B05B7/16—Spraying apparatus for discharge of liquids or other fluent materials from two or more sources, e.g. of liquid and air, of powder and gas incorporating means for heating or cooling the material to be sprayed
    • B05B7/22—Spraying apparatus for discharge of liquids or other fluent materials from two or more sources, e.g. of liquid and air, of powder and gas incorporating means for heating or cooling the material to be sprayed electrically, magnetically or electromagnetically, e.g. by arc
    • B05B7/222—Spraying apparatus for discharge of liquids or other fluent materials from two or more sources, e.g. of liquid and air, of powder and gas incorporating means for heating or cooling the material to be sprayed electrically, magnetically or electromagnetically, e.g. by arc using an arc
    • B05B7/226—Spraying apparatus for discharge of liquids or other fluent materials from two or more sources, e.g. of liquid and air, of powder and gas incorporating means for heating or cooling the material to be sprayed electrically, magnetically or electromagnetically, e.g. by arc using an arc the material being originally a particulate material
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/067—Metallic material containing free particles of non-metal elements, e.g. carbon, silicon, boron, phosphorus or arsenic
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/08—Metallic material containing only metal elements
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/18—After-treatment

Definitions

  • This disclosure relates to a gas turbine engine, and more particularly to gaspath leakage seals for gas turbine engines.
  • Gas turbine engines such as those used to power modern commercial and military aircraft, generally include one or more compressor sections to pressurize an airflow, a combustor section for burning hydrocarbon fuel in the presence of the pressurized air, and one or more turbine sections to extract energy from the resultant combustion gases.
  • the airflow flows along a gaspath through the gas turbine engine.
  • the gas turbine engine includes a plurality of rotors arranged along an axis of rotation of the gas turbine engine.
  • the rotors are positioned in a case, with the rotors and case having designed clearances between the case and tips of rotor blades of the rotors. It is desired to maintain the clearances within a selected range during operation of the gas turbine engine as deviation from the selected range can have a negative effect on gas turbine engine performance.
  • the case typically includes an outer airseal located in the case immediately outboard (radially) of the blade tips to aid in maintaining the clearances within the selected range.
  • the airseal typically has an abradable coating along its inner diameter (ID) surface.
  • the abradable coating material may be applied to a bondcoat along the metallic substrate of the outer airseal.
  • the compressor blades comprise titanium-based substrates (a potential source of fire) systems have been proposed with a fire-resistant thermal barrier layer intervening between the bondcoat and the abradable material.
  • An example of such a coating is found in US Patent No. 8,777,562 of Strock et al., issued July 15, 2014 , and entitled "Blade Air Seal with Integral Barrier".
  • US Patent, 8,562,290 of Strock et al. issued October 22, 2013 , and entitled “Blade outer air seal with improved efficiency”, discloses abradable material comprising a matrix of an alloy and a fine hexagonal boron nitride (hBN) containing particles of a coarser hBN.
  • a first thermal spray feedstock comprise agglomerates of alloy particles and fine hBN particles agglomerated using polyvinyl alcohol.
  • the coarse hBN may be from a second spray feedstock.
  • thermal spray processes such as air plasma spray.
  • the plasma spray process involves a single feedstock outlet discharging a mixture of coating constituents and fugitive porosity former in to a plasma jet.
  • Proposals have been made to segregate the porosity former and introduce that through a relatively downstream outlet while the matrix and solid lubricant are introduced from a conventionally located upstream outlet. Examples of these are found in US Patent 4696855, of Petit, Jr. et al., issued September 29, 1987 , and entitled “Multiple Port Plasma Spray Apparatus and Method for Providing Sprayed Abradable Coatings", and US Patent 4299865, of Clingman et al., issued November 10, 1981 and entitled “Abradable Ceramic Seal and Method of Making Same”.
  • US Patent 4386112, of Eaton et al., issued May 31, 1983 , and entitled “Co-Spray Abrasive Coating” shows separate introduction of matrix and abrasive in an abrasive coating.
  • One aspect of the disclosure involves a method for applying an abradable coating.
  • the method comprises: generating a plasma; introducing a matrix-forming first particulate to the plasma at a first location; introducing a second particulate of an organic particulate and/or salt particulate to the plasma at a second location downstream from the first location to mix with the matrix-forming first particulate, the second particulate having a characteristic size in the range 6.0 micrometers to 45.0 micrometers; and directing the first particulate and the second particulate to a target to form a coating on the target.
  • An embodiment may additionally and/or alternatively include removing the second particulate from the coating so as to leave porosity.
  • a further embodiment may additionally and/or alternatively include the second particulate characteristic size being a D50 size.
  • a further embodiment may additionally and/or alternatively include the D50 size being 15 micrometers to 35 micrometers.
  • a further embodiment may additionally and/or alternatively include the second particulate having a D90 size of at most 45 micrometers.
  • a further embodiment may additionally and/or alternatively include the first particulate having metallic particles of D50 particle size of 11-90 micrometers.
  • a further embodiment may additionally and/or alternatively include the metallic particles comprising Cu-Ni alloy or an MCrAlY.
  • a further embodiment may additionally and/or alternatively include the first particulate being an agglomerate of said metallic particles and particles of an inorganic non-metallic filler.
  • a further embodiment may additionally and/or alternatively include the second particulate being introduced at a volume flow rate of 40% to 80% of a total particulate flow rate.
  • a further embodiment may additionally and/or alternatively include the second location being at least 0.30 inch (7.62 mm) downstream of the first location.
  • a further embodiment may additionally and/or alternatively include the first location being within 2.0 diameters of a nozzle downstream of the nozzle outlet.
  • a further embodiment may additionally and/or alternatively include the second location being at least 3.0 diameters downstream of the nozzle outlet.
  • a further embodiment may additionally and/or alternatively include the second location being at least 0.60 inch (15.24 mm) downstream of a nozzle outlet.
  • a further embodiment may additionally and/or alternatively include both the first particulate and the second particulate being injected into a core of the plasma.
  • a further embodiment may additionally and/or alternatively include the coating being applied to a blade outer airseal substrate.
  • a further embodiment may additionally and/or alternatively include the coating having Vickers micro-hardness of a coating cross-section of not more than 400 measured with a 50g load in a location when 100 randomly located indents are made on the cross-section.
  • a further embodiment may additionally and/or alternatively include the coating having a cohesive bond strength of 750 psi (5.17 MPa) to 2000 psi (13.8 MPa).
  • the invention provides a blade outer airseal coated by the method.
  • Another aspect of the invention involves a method for applying an abradable coating.
  • the method comprises: generating a plasma; introducing a matrix-forming first particulate to the plasma at a first location; introducing a second particulate of a fugitive porosity-former to the plasma at a second location downstream from the first location to mix with the matrix-forming first particulate, the second particulate fugitive-former having a characteristic size in the range 6.0 micrometers to 45.0 micrometers; directing the first particulate and the second particulate to a target to form a coating on the target; and removing the fugitive porosity-former from the coating.
  • FIG. 1 is a view of a plasma spray apparatus.
  • US Patent 4299865 identifies downstream introduction (injection) of polyester porosity former at -140 +325 Mesh (44-105 micrometers). US Patent 4696855 also discloses downstream injection.
  • FIG. 1 shows a substrate 10 to be coated and the apparatus 12 used to deposit the powders onto the substrate.
  • the exemplary apparatus is based on that of US Patent 4696855 ; however other baselines may be used.
  • the powder supply means may be the powder supply means (powder hoppers, carrier gas sources, valves and the like); means for moving the substrate 10 and the apparatus 12 relative to each other (e.g., six-axis robot carrying the gun and a similar robot or manipulator carrying the substrate) are also not shown.
  • the specific manner in which the substrate 10 and apparatus 12 are moved will depend on the nature of the substrate.
  • Either the substrate 10 may be moved while the apparatus 12 is kept in a fixed position, the apparatus 12 moved while the substrate 10 is kept in a fixed position, or the substrate 10 and apparatus 12 both moved.
  • Exemplary substrates are metallic (e.g., nickel-based superalloy) and/or of components such as blade outer airseals (BOAS).
  • Alternative substrates include those of bearing compartment knife edge seal mating surfaces, plate seals (axial) and the inner diameter (ID) of vanes which have seals that are cut by knife edges on a rotor.
  • the apparatus 12 includes a gun assembly 14.
  • the gun assembly 14 is of the plasma arc type.
  • a high temperature electric arc is generated between spaced apart electrodes.
  • Primary and secondary gases e.g., helium, argon, or nitrogen, or mixtures thereof, pass through the arc, and are ionized to form a high temperature, high velocity plasma plume or stream 15 which extends in a downstream direction from the gun nozzle 19 towards the substrate 10.
  • the gun nozzle 19 (plasma nozzle) is typically water cooled.
  • a fixturing bracket 16 is attached to the front end 17 of the gun assembly 14 by means not shown in the Figure. Attached to the bracket 16 are nozzles 18 which each spray a stream of cooling gases onto the substrate 10 to prevent the substrate 10 from being excessively heated by the plasma stream 15.
  • Useful cooling gases include, e.g., nitrogen, argon, and/or air.
  • powder ports 22, 24 are arranged to direct separate streams of powder particles into the plasma stream 15.
  • First powder ports 22 (shown as an opposed pair, but optionally a single port at a single circumferential location) direct particles of a first type of powder 23 into the stream 15, and second powder ports 24 (shown as an opposed pair, but optionally a single port at a single circumferential location) direct particles of a second type of powder 25 into the stream 15.
  • FIG. 1 shows two first powder ports 22 about 180° from each other, and two second powder ports 24 about 180° from each other, and generally radially aligned with the position of the first powder ports 22.
  • the first powder ports 22 are axially upstream of the second powder ports 24, and are constructed and arranged to inject the first powder particles 23 into the stream 15 at a distance A from the front end 17 of the gun assembly 14; the second powder ports 24 inject the second powder particles 25 into the stream 15 at a downstream distance B.
  • the distance between the gun front end 17 and the substrate 10 is designated C.
  • US Patent 4696855 states that, as a result of a selected arrangement of the first and second powder ports 22, 24, and the rate and velocity in which the powder particles 23, 25 are separately injected into the stream 15, there is little mixing of the particles 23, 25 in the stream 15. Furthermore, the residence or dwell time of the second powder particles 25 in the plasma stream 15 is less than the dwell time of the first powder particles 23.
  • powder particles 23, 25 are delivered to the powder ports 22 and 24 by lines 32 and 34, respectively.
  • the lines 32, 34 are pressurized with a carrier gas which is typically argon.
  • the two feed lines 32 are each connected to a separate powder feeder which contain the first powder particles 23 and the two feed lines 34 are each connected to a separate powder feeder which contain the second powder particles 25. All powder feeders are independently controllable (e.g., via a microprocessor-based controller 50) to deliver powder at a specified rate and velocity to and through their respective powder ports.
  • the plasma stream 15 spreads radially outwardly from the stream axis 26 as the downstream distance from the gun front end 17 increases.
  • the resulting overall shape of the stream 15 is similar to that of a tapered cylinder.
  • the plasma stream 15 actually comprises a central stream of moving gases 40 and a radially outer, peripheral stream of moving gases 42.
  • the central stream 40 represents a core and the peripheral stream 42 is believed to represent a turbulent boundary layer cooler than the core due to mixing.
  • the diameter d c of the central stream 40 increases only slightly as the downstream distance increases, while the diameter do of the outer stream 42 increases to a much greater extent as the downstream distance increases.
  • the temperature as well as the velocity of the gases within the central plasma stream 40 is considerably higher than the temperature and velocity of the gases in the outer stream 42.
  • each first powder feeder is selected to inject a substantially continuous flow of powder particles of the first powder type (e.g., agglomerate of metallic matrix and solid lubricant or other non-fugitive filler) through its respective first powder port 22 and directly into the central stream of gases 40.
  • the first powder particles 23 are carried by the central stream 40 until they impact upon the substrate 10. Tests have shown that there is little radial deviation of the first powder particles 23 outside of the central stream 40, apparently due to their relatively high axial momentum in the stream 15, although other forces may be acting to produce this effect.
  • the second powder particles 25 may be injected through the stream 42 and into the stream 40. Whereas the turbulence of the stream 42 is believed to cause uneven distribution of particles it might carry, by penetrating the introduction of the second powder particles in to the steam 40. A more even and mixed distribution with the first powder is achieved.
  • each of the second powder ports 24 is radially outward of, as well as axially downstream of, the outlet end 46 of each of the first powder ports 22.
  • the operating parameters of each second powder feeder are selected to inject the second powder particles 25 into the plasma stream 15 such that they do not enter the central stream of gases 40. Rather, the second powder particles 25 are carried by the outer stream of gases 42 until they impact upon the substrate 10. Whether the different powder particles 23, 25 are properly injected into their respective plasma stream portion 40, 42 and are carried by such stream portion to the substrate 10, can be determined by evaluating the distribution of the powder particles 23, 25 in the stream 15.
  • outer stream of gas 42 forms a low temperature turbulent layer around the central stream of hot gases 40.It is desirable to inject the first powder particles 23 and second powder particles 25 through the outer gas stream to be carried to the substrate 10 by gas stream 40. The particles 23 and 25 mix within the plasma stream 15. This is unlike prior art plasma spray processes, wherein the different powder types are deliberately injected into separate portions of the plasma stream to prevent mixing.
  • downstream injection of the fugitive former expands the possible candidates for porosity formers.
  • substantially finer powders of polymer or other porosity formers may have one or more advantages.
  • Downstream injection of the fugitive allows smaller and lower melting point or decomposition point fugitives to be used. It is more consistent and predictable to inject into the higher energy core gas stream 40 than injecting into the outer turbulent layer (because of the turbulence). Downstream injection into the core gas stream imparts more velocity and uniformity than would downstream injection into the outer turbulent layer.
  • the downstream injection into the core gas steam may also replace a baseline upstream injection into the turbulent layer. Overheating the smaller particles is avoided by both. Downstream is cooler and the turbulent periphery is cooler. Downstream core injection has the advantage of not being turbulent and therefore has a more consistent influence on the particles.
  • abradable coatings there are two primary categories of wear mechanisms: those that cause wear through the constituent particles; and fracture in and between the constituent particles. The latter is considered normal abradable wear.
  • the fracture mechanism of constituent particle removal (splats and groups of splats) takes the lowest energy per unit volume of coating wear and results in low levels of blade heating and wear. The force at which these fractures take place are conventionally related to coating hardness and density.
  • the conventionally used HR15Y scale for macro hardness measurement uses a 15kg load and measures a relatively large volume of coating. Within that volume there is microstructural variation in metal content (vs. porosity and non-metallic components). The local variations in metal content within that volume can be further characterized by micro indentation which uses a smaller indenter load (50 g) and indicates the properties of a proportionately smaller volume of coating.
  • microhardness within an area of higher metal content is higher (than in low-metal content regions and higher than that indicated by a macrohardness indentation that indicates the average influence of many higher and lower metal concentration regions).
  • microhardness is taken to indicate the relative ease with which these constituent particles may be fractured from the coating by contact with the blade. It may thus be possible to improve abradability by reducing the hardness or strength of the larger high metal content regions without adversely affecting other coating performance characteristics such as erosion resistance. This may be done by reducing the size of the metal rich regions without changing the fugitive to matrix ratio.
  • fugitive particle size By reducing fugitive particle size while maintaining overall volume fraction, a larger number of fugitive particles are used per volume of coating and therefore the average spacing between these fugitive particles is reduced. Furthermore, by reducing this average spacing, the size of the metal-rich areas are also reduced proportionally. With smaller metal-rich areas, there are less metal matrix particles connecting them to the rest of the coating and they are easier to break away during rub interaction. For example, if the diameter of the fugitive is reduced by half, the volume of a single particle is only 1/8th that of the original. This results in the number of fugitive particles per volume being increased by a factor of 8. This example reduces the average interparticle spacing by 50% and therefore also the average size of the metal-rich regions.
  • fugitive is 15-30 micrometers with 22.5 micrometers nominal (e.g., D50) compared with a baseline of 60-120 micrometers or 90 micrometers nominal (e.g., a baseline slightly larger than the nominal of US Patent 4299865 ).
  • This example has a diameter ratio of 4 which means that the average fugitive particle spacing would be reduced by a factor of 4 and the associated larger metal rich areas also reduced in thickness by a factor of 4.
  • candidate fugitive porosity formers are not limited to polymers. Additional candidates are salt fugitives (e.g., chlorides, phosphates, nitrates, sulfates, and the like). Sodium chloride is one example. These may be subject to chemical decomposition or vaporization if introduced as fine powder in the conventional upstream injection location. The fugitive may be removed from the coating by one or more methods. One mechanism is the heating from running the engine. Other active steps include heating of coated parts after coating but before installation. Salt fugitive may be dissolved out via water immersion.
  • salt fugitives e.g., chlorides, phosphates, nitrates, sulfates, and the like.
  • Sodium chloride is one example. These may be subject to chemical decomposition or vaporization if introduced as fine powder in the conventional upstream injection location.
  • the fugitive may be removed from the coating by one or more methods. One mechanism is the heating from running the engine. Other active steps include heating of
  • organic material that would otherwise be a fugitive may be left in and not burned/vaporized out before service or even in service. Leaving in this material may improve aerodynamic efficiency.
  • the material may be removed in a thin surface layer during low incursion rate rub events by the temperature rise associated with frictional heating by the blade tips. This removal along a shallow surface layer (1-25 microns) leaves porosity in that surface layer that provides a location for plastically smeared abradable matrix material to be deposited during wear while leaving lower regions filled to improve aerodynamic efficiency.
  • Characteristic fugitive particle size is 11-45 micrometers. This characteristic may be a D50 value or mass median diameter. Exemplary D50 are 11-35 micrometers, more particularly 15-35 micrometers or 11-25 micrometers. Exemplary D90 values are up to 45 micrometers, more narrowly, up to 35 micrometers. For example, it may be -325 mesh. Table I below shows several ranges. For a given row example further variants involve having only some of the values in the associated columns. Table I Fugitive Sizes Example/Range Size (micrometers) Mesh D50 D10 D90 1 11-35 6 45 2 15-35 6 45 3 11-25 6 35 4 22 11 33 5 11-35 6 -325
  • Matrix material may be selected from current or future matrix alloys and sizes.
  • Exemplary alloys include Cu-Ni alloys (e.g., Cu26Ni8.5A14Cr) or an MCrAlY (although the Y may be eliminated in lower temperature engine locations).
  • Exemplary D50 particle size is 11-90 micrometers. The upper end of that range may be less desirable because larger particles contribute to larger islands of metal matrix material and have been associated with increased blade wear. Thus, alternative D50 upper ends are 75 micrometers and 45 micrometers. An alternative lower (D10) end is 16 micrometers. Table II below shows several ranges. For a given row example further variants involve having only some of the values in the associated columns.
  • Exemplary persistent non-metallic filler (“soft filler”) is selected to limit adhesion of metal particles and interfere with the smearing and material transfer often associated with rub interactions.
  • hBN is one example.
  • Table III shows several particle size ranges. For a given row example further variants involve having only some of the values in the associated columns.
  • Table III Filler Sizes Example/Range Size (micrometers) Mesh D50 D10 D90 1 11-35 6 45 2 15-35 6 45 3 11-25 6 35 4 22 11 33 5 11-35 6 -325
  • Exemplary proportions of the matrix and soft filler in the first powder source are 1 to 25 volume % as a percentage of the sum of soft filler and metal volume.
  • agglomerates may be as agglomerates.
  • exemplary agglomerates are agglomerated with a fugitive agent such as polyvinyl alcohol at a volume percentage in the agglomerate of 1-5 volume %.
  • Table IV shows several ranges. For a given row example further variants involve having only some of the values in the associated columns.
  • Table IV Agglomerate Properties Example/Range Size (micrometers) Vol% filler D50 D10 D90 1 75 16 125 1-25 2 45 16 90 5-15 3 22 11 75 5-15 4 45 16 75 7-12 5 35-45 11-22 55-100 3-15 6 20-80 10-25 50-140 1-25
  • the as-applied coating may have an exemplary 20-35% by volume matrix and ⁇ 10% porosity (preferably ⁇ 5% in order to provide good bonding between metal particles; this allows a lower ultimate metal content for a given bulk strength and erosion resistance).
  • Non-matrix components may represent the fugitive porosity former and soft fillers at combined content of 55% to 80% by volume.
  • Exemplary soft filler content may be 0% to 15% by volume.
  • Soft filler serves to prevent transfer of material (coating material shifted by the blades or material transferred from the blades themselves) by allowing release of that material.
  • the fugitive may represent 40% to 80% by volume, more particularly, 60% to 75%. With approximately constant deposition efficiency, relative volume flow rates in the spray process may be similar to these relative volumes.
  • Exemplary ratios of the fugitive flow rate to the first powder in an air plasma spray process are 0.2 to 0.4 (by weight, with an example where the first powder has a theoretical density of 8.5 g/cc and the fugitive has a theoretical density of 1.2 g/cc).
  • the A value or distance will be of a similar magnitude to the nozzle diameter (e.g., up to about 3 times the nozzle diameter, with exemplary values of 0.5 to 2.0 or 0.5-1.5 and a nominal of about 0.75).
  • This A value may represent the injection location of all material in a baseline spray apparatus being modified to add downstream injection of fugitive or other material.
  • the B value will be greater than the A value by any of several measures.
  • Exemplary B may be at least twice the nozzle diameter or at least 3.0 times (e.g., 2.5-10.0 or 3.0-8.0).
  • An exemplary separation (B-A) of the two introductions is at least the A value or the nozzle diameter, more particularly at least twice either or both of those amounts.
  • An exemplary nozzle diameter is 0.25 inch (6.35 mm).
  • an exemplary separation (B-A) of the two introductions is at least 6 mm or at least 12 mm, with an exemplary range of 6 mm to 30 mm, more particularly, 8 mm to 25 mm. If, such as shown for the fugitive, an angled introduction is made, then the positions at which A or B may be measured may correspond to the intersections of the centerlines of the powder discharges with the plasma centerline.
  • Table V below provides exemplary injection parameters. The basic example is the aforementioned 0.25 inch (6.35 mm) nozzle. Several variations reflect scaling. Table V Injection Parameters Parameter Units Ex. 1 Ex. 2 Ex. 3 Ex.
  • standard temperature and pressure are a temperature of 273.15 K (0 °C, 32 °F) and an absolute pressure of exactly 100 kPa (1 bar, 14.504 psi, 0.98692 atm.).
  • the B distance may be 20% greater or 40% greater than nominal or 20% less or 40% less.
  • the exemplary as-applied coating has a cohesive bond strength of 500-3000 psi (3.5-20.7 MPa), more particularly 750-2000 psi (5.2-13.8 MPa). Bond strength may be influenced/adjusted by: spray parameters (primary gas flow, secondary gas flow, nozzle size, power, standoff distance, and the like); composition (ratios described above). This bond strength is in the usual range for a desirable balance between erosion resistance and abradability at high interaction rates.
  • Target maximum Vickers micro-hardness of a coating cross section is 400 or more desirably 300 with a 50g load (in any location when 100 randomly located indents are made on the cross section).
  • the test is performed with a sample infiltrated with epoxy mounting material. This affects the measurement, especially at the loosely connected areas, much less at the areas of interest where there is more metal.
  • small fugitive size may limit the size and related strength or hardness of the high metal concentration regions of the coating.
  • the fugitive may be removed leaving enhanced porosity.
  • removal may comprise a thermal burn-off.
  • removal may comprise thermal decomposition or dissolution.
  • first, second, and the like in the following claims is for differentiation within the claim only and does not necessarily indicate relative or absolute importance or temporal order. Similarly, the identification in a claim of one element as “first” (or the like) does not preclude such "first” element from identifying an element that is referred to as “second” (or the like) in another claim or in the description.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Electromagnetism (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Powder Metallurgy (AREA)
EP17183877.4A 2016-07-29 2017-07-28 Procédés et appareil de fabrication de bande de frottement abradable de joint d'air externe Active EP3276039B8 (fr)

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US15/223,443 US20180030586A1 (en) 2016-07-29 2016-07-29 Outer Airseal Abradable Rub Strip Manufacture Methods and Apparatus

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EP3640229B1 (fr) 2018-10-18 2023-04-05 Rolls-Royce Corporation Revêtements de barrière résistants aux cmas
DE102020126082A1 (de) 2020-10-06 2022-04-07 Forschungszentrum Jülich GmbH Verfahren zur Herstellung einer Beschichtung sowie Beschichtung

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4299865A (en) 1979-09-06 1981-11-10 General Motors Corporation Abradable ceramic seal and method of making same
US4386112A (en) 1981-11-02 1983-05-31 United Technologies Corporation Co-spray abrasive coating
GB2152079A (en) * 1983-12-27 1985-07-31 United Technologies Corp Porous metal structures made by thermal spraying fugitive material and metal
US4696855A (en) 1986-04-28 1987-09-29 United Technologies Corporation Multiple port plasma spray apparatus and method for providing sprayed abradable coatings
WO2009155702A1 (fr) * 2008-06-25 2009-12-30 Sanjeev Chandra Système et procédé de projection d'oxygaz basse température et procédé permettant de déposer des couches à l'aide de ceux-ci
WO2011008719A1 (fr) * 2009-07-14 2011-01-20 Praxair S.T. Technology, Inc. Systeme de revetement pour reduction des jeux dans des machines tournantes
US20110243715A1 (en) * 2010-03-30 2011-10-06 Strock Christopher W Abradable turbine air seal
US8562290B2 (en) 2010-04-01 2013-10-22 United Technologies Corporation Blade outer air seal with improved efficiency
US8777562B2 (en) 2011-09-27 2014-07-15 United Techologies Corporation Blade air seal with integral barrier
WO2015053948A1 (fr) * 2013-10-09 2015-04-16 United Technologies Corporation Revêtement en alliage d'aluminium dotés d'inhibiteurs de corrosion de type terres rares et métaux de transition

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4299865A (en) 1979-09-06 1981-11-10 General Motors Corporation Abradable ceramic seal and method of making same
US4386112A (en) 1981-11-02 1983-05-31 United Technologies Corporation Co-spray abrasive coating
GB2152079A (en) * 1983-12-27 1985-07-31 United Technologies Corp Porous metal structures made by thermal spraying fugitive material and metal
US4696855A (en) 1986-04-28 1987-09-29 United Technologies Corporation Multiple port plasma spray apparatus and method for providing sprayed abradable coatings
WO2009155702A1 (fr) * 2008-06-25 2009-12-30 Sanjeev Chandra Système et procédé de projection d'oxygaz basse température et procédé permettant de déposer des couches à l'aide de ceux-ci
WO2011008719A1 (fr) * 2009-07-14 2011-01-20 Praxair S.T. Technology, Inc. Systeme de revetement pour reduction des jeux dans des machines tournantes
US20110243715A1 (en) * 2010-03-30 2011-10-06 Strock Christopher W Abradable turbine air seal
US8562290B2 (en) 2010-04-01 2013-10-22 United Technologies Corporation Blade outer air seal with improved efficiency
US8777562B2 (en) 2011-09-27 2014-07-15 United Techologies Corporation Blade air seal with integral barrier
WO2015053948A1 (fr) * 2013-10-09 2015-04-16 United Technologies Corporation Revêtement en alliage d'aluminium dotés d'inhibiteurs de corrosion de type terres rares et métaux de transition

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EP3276039B1 (fr) 2021-03-17
US20180030586A1 (en) 2018-02-01

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