EP2964808A1 - Thermomechanische, ermüdungsbeständige und abreibbare aluminiumbeschichtung - Google Patents

Thermomechanische, ermüdungsbeständige und abreibbare aluminiumbeschichtung

Info

Publication number
EP2964808A1
EP2964808A1 EP13877283.5A EP13877283A EP2964808A1 EP 2964808 A1 EP2964808 A1 EP 2964808A1 EP 13877283 A EP13877283 A EP 13877283A EP 2964808 A1 EP2964808 A1 EP 2964808A1
Authority
EP
European Patent Office
Prior art keywords
particles
aluminum
powder
boride
coating
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.)
Granted
Application number
EP13877283.5A
Other languages
English (en)
French (fr)
Other versions
EP2964808B1 (de
EP2964808A4 (de
Inventor
Christopher W. Strock
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of EP2964808A1 publication Critical patent/EP2964808A1/de
Publication of EP2964808A4 publication Critical patent/EP2964808A4/de
Application granted granted Critical
Publication of EP2964808B1 publication Critical patent/EP2964808B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F9/00—Making metallic powder or suspensions thereof
    • B22F9/02—Making metallic powder or suspensions thereof using physical processes
    • B22F9/06—Making metallic powder or suspensions thereof using physical processes starting from liquid material
    • B22F9/08—Making metallic powder or suspensions thereof using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying
    • B22F9/082—Making metallic powder or suspensions thereof using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying atomising using a fluid
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/04—Making non-ferrous alloys by powder metallurgy
    • C22C1/0408—Light metal alloys
    • C22C1/0416—Aluminium-based alloys
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/10—Alloys containing non-metals
    • C22C1/1036—Alloys containing non-metals starting from a melt
    • C22C1/1042—Alloys containing non-metals starting from a melt by atomising
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
    • C22C32/0047—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with carbides, nitrides, borides or silicides as the main non-metallic constituents
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
    • C22C32/0047—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with carbides, nitrides, borides or silicides as the main non-metallic constituents
    • C22C32/0073—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with carbides, nitrides, borides or silicides as the main non-metallic constituents only borides
    • 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
    • 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

  • thermo- mechanical fatigue (TMF) resistant aluminum abradable coating which has particular utility as an outer air seal .
  • Compressor efficiency is related to blade tip clearance and outer air seal roughness. Coatings for the fan and the low pressure compressor are typically applied on titanium or iron based parts. The coefficient of thermal expansion (CTE) mismatch between the aluminum coating and the base metal (the titanium or iron) is almost a factor of two. This may lead to high
  • thermo- mechanical fatigue cracking and coating spallation With many thermal cycles from room temperature and back, the result is thermo- mechanical fatigue cracking and coating spallation.
  • Blades that mate with an aluminum seal may be titanium- or iron-based. During rub interaction, under certain conditions, metal is transferred to the blade tips. This may cause localized wear of the seal in what is known as record groove patterns. The result is increased average tip clearance and increased roughness in the air flow direction.
  • an aluminum coating having a
  • an aluminum coating to be deposited on a substrate having a first coefficient of thermal expansion which aluminum coating broadly comprises an aluminum matrix, particles of a material having a low thermal expansion coefficient incorporated into the matrix; and the particles bonding sufficiently we 11 to the aluminum matrix to carry a portion of the mechanical load .
  • the particles are selected from the group consisting of carbides, borides, oxides , and combinations thereof .
  • the particles are aluminum boride particles .
  • the particles are titanium boride particles .
  • the titanium boride particles have a ratio of titanium to boron in the range of 1:1 to 1:4.
  • the particles are present in an amount from 1.0 to 33 vol% .
  • the particles are present in an amount of from 10 to 25 vol%
  • the particles are present in an amount of 15 to 20 vo 1% .
  • the aluminum coating further comprises a pore making
  • the pore making material is selected from the group consisting of hexagonal boron nitride, polyester and Lucite .
  • the part providing step comprises providing a part formed from a titanium based alloy or an iron based alloy.
  • the powder forming step comprises forming a powder containing particles selected from the group consisting of oxide material, a carbide, a boride, and combinations thereof.
  • the powder forming step comprises forming the powder to have from 1.0 to 33 vol% of the particles.
  • the powder forming step comprises forming the powder to have from 10 to 25 vol% of the particles.
  • the powder forming step comprises forming the powder to have from 15 to 20 vol% of the particles.
  • the powder forming step comprises using titanium boride particles .
  • the powder forming step comprises using aluminum boride particles .
  • the process further comprises adding a pore making material to the powder .
  • the process further comprises melt atomization of a boride containing aluminum alloy and quenching the boride containing aluminum alloy during atomization to form particles of a metastable solid solution.
  • the process further comprises subjecting the aluminum coating to a heat treatment in the range of from 1100 to 1200 degrees Centigrade for 2.0 hours.
  • a process for forming an aluminum alloy matrix containing fine particles which broadly comprises the steps of: melt atomizing a boride containing aluminum alloy; and quenching the boride containing aluminum alloy during atomization to form particles of a metastable solid solution.
  • thermo-mechanical fatigue resistant aluminum abradable coating are set forth in the following detailed description.
  • the substrate to which the aluminum coating described herein may be applied may be formed from a titanium alloy or from an iron based alloy.
  • the substrate may be a fan casing or a casing for a compressor section of gas turbine engine.
  • the aluminum coating has an aluminum matrix formed from an aluminum alloy such as an aluminum-silicon alloy.
  • the aluminum coating further includes fine particles in the range of 20 nm to 5 microns mean particle diameter of a low coefficient of thermal expansion (cte) material, which is defined as having a cte that is lower than that of the aluminum matrix, which are incorporated into the aluminum matrix.
  • the fine particles may be in the range of from 20 nm to 2 microns in mean particle size.
  • the inclusion of the fine particles of a low coefficient of thermal expansion material results in hardening, strengthening and coefficient of thermal expansion reduction.
  • the fine particles to be incorporated into the aluminum coating may be fine particles selected from the group consisting of an oxide material, a boride, a carbide, and combinations thereof. Only those particles which bond sufficiently well to the aluminum matrix material and are capable of carrying a portion of the mechanical load and which act as a composite material are used in the aluminum coating described herein.
  • the fine particles may be boride particles, such as aluminum boride particles and titanium boride
  • Aluminum boride particles form high aspect ratio platelets when precipitated at a temperature of below about 650 degrees Centigrade. When aluminum boride particles are used, the technique used to manufacture the aluminum coatings must contain sufficient heating of the alloy constituents to fully dissolve any A1B12 which tends to form at temperatures between 650 degrees
  • A1B12 Centigrade and 1550 degrees Centigrade depending on boron concentration.
  • the formation of A1B12 during cooling may be suppressed by quenching to below 650 degrees
  • Centigrade This can bed one by rapid cooling of the melt or passively as one of the characteristics of thermal spray coating in which molten particles are quench cooled upon impact with a surface. If desired, the thermal spray coating may be subsequently heat treated to a temperature of up to 650 degrees Centigrade.
  • Aluminum boride is a desirable candidate due to its low cost, high thermal conductivity, low coefficient of thermal expansion, and good adhesion to the matrix.
  • Aluminum boride at 20 vol% has been shown to increase the strength of aluminum by 80%.
  • Titanium boride is also a desirable candidate for the aluminum coating.
  • the titanium boride particles may be incorporated into the aluminum matrix by precipitation from a quenched metastable solid solution.
  • the titanium boride may have a ratio of titanium to boron which ranges from 1:1 to 1:4. It is also possible to include the titanium boride particles by mechanical alloying, agglomeration with the matrix alloy in a thermal spray feed stock powder, pressed and sintered.
  • borides such as titanium boride or aluminum boride
  • they may be present in a range of from 1.0 vol% to 33 vol%, balance aluminum matrix.
  • the boride particles may be present in an amount from 10 to 25 vol% .
  • the boride particles may be present in an amount from 15 to 20 vol% .
  • the borides may be dissolved in melt
  • melt atomization of a boride containing aluminum alloy that quenches during
  • precipitation of undesirable phases may be suppressed as a result of rapid cooling rates.
  • other powder manufacturing routes that result in powder with undesirable phases may be melted and solutionized during the spray coating operation. Either way, molten or softened particles may then be quench cooled during deposition.
  • titanium boride precipitates from a metastable quenched structure to form precipitates in the 20nm to 2.0 micron size range, depending on subsequent heat treat temperature. The heat treatment could be heating the aluminum coating at 625 to 650 degrees Centigrade for 2.0 hours .
  • Carbides which may be used include those in the covalent and interstitial carbide groups with prime candidates being silicon carbide and titanium carbide.
  • the aluminum matrix with fine particles is formed into a powder with the fine particles is formed into a powder so that it can be applied on the substrate by a spray process such as thermal spraying.
  • the fine particles may be included in the particles forming the aluminum matrix material by agglomeration, alloying and precipitation, or ball milling and cold working.
  • the amount of fine particles is a function of the desired coefficient of thermal expansion for the aluminum coating. Also, considerations of through thickness thermal gradient may be taken into account.
  • the aluminum coating may be applied to the substrate by thermally spraying the matrix material with the incorporated fine particles. If desired, a pore making fugitive or soft filler material may also be added to the matrix material while it is being sprayed.
  • the fugitive or soft filler material do not affect the coefficient of thermal expansion of the aluminum coating. To affect the coefficient of thermal expansion, the filler material would have to both bond with the aluminum matrix and have sufficient elastic modulus to at least partially elastically constrain the aluminum matrix.
  • the elastic modulus of the filler material may be higher than that of aluminum.
  • Fugitives and fillers like hexagonal boron nitride, polyester, and Lucite are candidates for affecting the abradability of the aluminum coating and may be used to offset the strengthening of the matrix material by the fine particles.
  • Fugitives and soft fillers may be used at up to about 70 volume percent of the coating.
  • the fugitives and soft fillers may be present in an amount from 40 to 65 volume percent.
  • the coating may be made from an aluminum alloy containing 70.4 wt% aluminum, 13.8 wt% titanium, 9.6 wt% silicon, and 6.2 wt% boron and hexagon boron nitride to produce a coating of 40 volume % metal alloy, 50 volume % hBN and 10% porosity.
  • the titanium boride particles may be precipitated from a quenched metal alloy with heat treatment at 625 to 650 degrees Centigrade for 2.0 hours. [ 0041 ] While the aluminum coating particles are sprayed onto the substrate, the sprayed particles may be quenced by conduction of heat to the coating and
  • the substrate with the sprayed particles may be subjected to a heat treatment in the range of from 625 to 650 degrees Centigrade for 2.0 hours.
  • the benefits of the abradable coating described herein include reduced coefficient of thermal expansion and thermo-mechanical fatigue. This results in a more stable part shape with temperature change and improved coating durability.
  • the filler material also helps to reduce metal transfer to blades during low interaction rate sliding contact wear and result in tighter tip clearance and a smoother coating. As compared to choosing a conventional alloy that has a lower
  • the technique described herein does not increase the incipient melting point of the coating.
  • this is because the titanium and boride constituents fully precipitate as a high melting point phase.
  • the blade tip temperature, particularly of a titanium blade tip, during rub is still limited to the melting point of aluminum. This helps reduce the risk of a titanium fire .
  • thermo- mechanical fatigue resistant aluminum abradable coating There has been described herein a thermo- mechanical fatigue resistant aluminum abradable coating. While the coating has been described in the context of specific embodiments thereof, other unforeseeable alternatives, modifications, and variations may become apparent to those skilled in the art having read the foregoing description. Accordingly, it is intended to embrace those alternatives, modifications, and variations as fall within the broad scope of the appended claims.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP13877283.5A 2013-03-06 2013-12-30 Thermomechanische, ermüdungsbeständige und abreibbare aluminiumbeschichtung Active EP2964808B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201361773344P 2013-03-06 2013-03-06
PCT/US2013/078183 WO2014137464A1 (en) 2013-03-06 2013-12-30 Thermo-mechanical fatigue resistant aluminum abradable coating

Publications (3)

Publication Number Publication Date
EP2964808A1 true EP2964808A1 (de) 2016-01-13
EP2964808A4 EP2964808A4 (de) 2016-10-26
EP2964808B1 EP2964808B1 (de) 2019-05-01

Family

ID=51491755

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13877283.5A Active EP2964808B1 (de) 2013-03-06 2013-12-30 Thermomechanische, ermüdungsbeständige und abreibbare aluminiumbeschichtung

Country Status (3)

Country Link
US (1) US20160017474A1 (de)
EP (1) EP2964808B1 (de)
WO (1) WO2014137464A1 (de)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10697464B2 (en) * 2016-07-29 2020-06-30 Raytheon Technologies Corporation Abradable material
US20190186281A1 (en) * 2017-12-20 2019-06-20 United Technologies Corporation Compressor abradable seal with improved solid lubricant retention

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4836982A (en) * 1984-10-19 1989-06-06 Martin Marietta Corporation Rapid solidification of metal-second phase composites
US5196471A (en) * 1990-11-19 1993-03-23 Sulzer Plasma Technik, Inc. Thermal spray powders for abradable coatings, abradable coatings containing solid lubricants and methods of fabricating abradable coatings
EP1247941A1 (de) * 2001-04-03 2002-10-09 Siemens Aktiengesellschaft Gasturbinenschaufel
US8187720B2 (en) * 2005-11-14 2012-05-29 Lawrence Livermore National Security, Llc Corrosion resistant neutron absorbing coatings
US7754342B2 (en) * 2005-12-19 2010-07-13 General Electric Company Strain tolerant corrosion protecting coating and spray method of application
US8034153B2 (en) * 2005-12-22 2011-10-11 Momentive Performances Materials, Inc. Wear resistant low friction coating composition, coated components, and method for coating thereof
US8790789B2 (en) * 2008-05-29 2014-07-29 General Electric Company Erosion and corrosion resistant coatings, methods and articles

Also Published As

Publication number Publication date
WO2014137464A1 (en) 2014-09-12
EP2964808B1 (de) 2019-05-01
US20160017474A1 (en) 2016-01-21
EP2964808A4 (de) 2016-10-26

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