EP2284246A1 - Revêtement de turbomachine - Google Patents

Revêtement de turbomachine Download PDF

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Publication number
EP2284246A1
EP2284246A1 EP10169196A EP10169196A EP2284246A1 EP 2284246 A1 EP2284246 A1 EP 2284246A1 EP 10169196 A EP10169196 A EP 10169196A EP 10169196 A EP10169196 A EP 10169196A EP 2284246 A1 EP2284246 A1 EP 2284246A1
Authority
EP
European Patent Office
Prior art keywords
coating
turbomachinery
graphite
dovetail
slot
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.)
Withdrawn
Application number
EP10169196A
Other languages
German (de)
English (en)
Inventor
David Vincent Bucci
Paul Stephen Dimascio
Surinder S. Pabla
Jesse C. Moses
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.)
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
Publication of EP2284246A1 publication Critical patent/EP2284246A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • C—CHEMISTRY; METALLURGY
    • C10—PETROLEUM, GAS OR COKE INDUSTRIES; TECHNICAL GASES CONTAINING CARBON MONOXIDE; FUELS; LUBRICANTS; PEAT
    • C10M—LUBRICATING COMPOSITIONS; USE OF CHEMICAL SUBSTANCES EITHER ALONE OR AS LUBRICATING INGREDIENTS IN A LUBRICATING COMPOSITION
    • C10M125/00—Lubricating compositions characterised by the additive being an inorganic material
    • C10M125/02—Carbon; Graphite
    • C—CHEMISTRY; METALLURGY
    • C10—PETROLEUM, GAS OR COKE INDUSTRIES; TECHNICAL GASES CONTAINING CARBON MONOXIDE; FUELS; LUBRICANTS; PEAT
    • C10M—LUBRICATING COMPOSITIONS; USE OF CHEMICAL SUBSTANCES EITHER ALONE OR AS LUBRICATING INGREDIENTS IN A LUBRICATING COMPOSITION
    • C10M103/00—Lubricating compositions characterised by the base-material being an inorganic material
    • C10M103/02—Carbon; Graphite
    • C—CHEMISTRY; METALLURGY
    • C10—PETROLEUM, GAS OR COKE INDUSTRIES; TECHNICAL GASES CONTAINING CARBON MONOXIDE; FUELS; LUBRICANTS; PEAT
    • C10M—LUBRICATING COMPOSITIONS; USE OF CHEMICAL SUBSTANCES EITHER ALONE OR AS LUBRICATING INGREDIENTS IN A LUBRICATING COMPOSITION
    • C10M111/00—Lubrication compositions characterised by the base-material being a mixture of two or more compounds covered by more than one of the main groups C10M101/00 - C10M109/00, each of these compounds being essential
    • C10M111/02—Lubrication compositions characterised by the base-material being a mixture of two or more compounds covered by more than one of the main groups C10M101/00 - C10M109/00, each of these compounds being essential at least one of them being a non-macromolecular organic compound
    • C—CHEMISTRY; METALLURGY
    • C10—PETROLEUM, GAS OR COKE INDUSTRIES; TECHNICAL GASES CONTAINING CARBON MONOXIDE; FUELS; LUBRICANTS; PEAT
    • C10M—LUBRICATING COMPOSITIONS; USE OF CHEMICAL SUBSTANCES EITHER ALONE OR AS LUBRICATING INGREDIENTS IN A LUBRICATING COMPOSITION
    • C10M111/00—Lubrication compositions characterised by the base-material being a mixture of two or more compounds covered by more than one of the main groups C10M101/00 - C10M109/00, each of these compounds being essential
    • C10M111/04—Lubrication compositions characterised by the base-material being a mixture of two or more compounds covered by more than one of the main groups C10M101/00 - C10M109/00, each of these compounds being essential at least one of them being a macromolecular organic compound
    • C—CHEMISTRY; METALLURGY
    • C10—PETROLEUM, GAS OR COKE INDUSTRIES; TECHNICAL GASES CONTAINING CARBON MONOXIDE; FUELS; LUBRICANTS; PEAT
    • C10M—LUBRICATING COMPOSITIONS; USE OF CHEMICAL SUBSTANCES EITHER ALONE OR AS LUBRICATING INGREDIENTS IN A LUBRICATING COMPOSITION
    • C10M2201/00—Inorganic compounds or elements as ingredients in lubricant compositions
    • C10M2201/04—Elements
    • C10M2201/041—Carbon; Graphite; Carbon black
    • C10M2201/0413—Carbon; Graphite; Carbon black used as base material
    • C—CHEMISTRY; METALLURGY
    • C10—PETROLEUM, GAS OR COKE INDUSTRIES; TECHNICAL GASES CONTAINING CARBON MONOXIDE; FUELS; LUBRICANTS; PEAT
    • C10M—LUBRICATING COMPOSITIONS; USE OF CHEMICAL SUBSTANCES EITHER ALONE OR AS LUBRICATING INGREDIENTS IN A LUBRICATING COMPOSITION
    • C10M2201/00—Inorganic compounds or elements as ingredients in lubricant compositions
    • C10M2201/10—Compounds containing silicon
    • C10M2201/102—Silicates
    • C10M2201/1023—Silicates used as base material
    • C—CHEMISTRY; METALLURGY
    • C10—PETROLEUM, GAS OR COKE INDUSTRIES; TECHNICAL GASES CONTAINING CARBON MONOXIDE; FUELS; LUBRICANTS; PEAT
    • C10N—INDEXING SCHEME ASSOCIATED WITH SUBCLASS C10M RELATING TO LUBRICATING COMPOSITIONS
    • C10N2030/00—Specified physical or chemical properties which is improved by the additive characterising the lubricating composition, e.g. multifunctional additives
    • C10N2030/06—Oiliness; Film-strength; Anti-wear; Resistance to extreme pressure
    • C—CHEMISTRY; METALLURGY
    • C10—PETROLEUM, GAS OR COKE INDUSTRIES; TECHNICAL GASES CONTAINING CARBON MONOXIDE; FUELS; LUBRICANTS; PEAT
    • C10N—INDEXING SCHEME ASSOCIATED WITH SUBCLASS C10M RELATING TO LUBRICATING COMPOSITIONS
    • C10N2040/00—Specified use or application for which the lubricating composition is intended
    • C10N2040/12—Gas-turbines
    • C—CHEMISTRY; METALLURGY
    • C10—PETROLEUM, GAS OR COKE INDUSTRIES; TECHNICAL GASES CONTAINING CARBON MONOXIDE; FUELS; LUBRICANTS; PEAT
    • C10N—INDEXING SCHEME ASSOCIATED WITH SUBCLASS C10M RELATING TO LUBRICATING COMPOSITIONS
    • C10N2050/00—Form in which the lubricant is applied to the material being lubricated
    • C10N2050/14—Composite materials or sliding materials in which lubricants are integrally molded

Definitions

  • the invention is directed to surface treatments for rotating turbomachinery.
  • the invention is directed to surface treatments for gas turbine components that may exhibit stresses, and in further particularity, the invention is directed to surface treatments for gas turbine compressor blade components at their interface with compressor wheels, where they may exhibit stresses.
  • Previous gas turbine compressor blade component configuration may provide bare or non-treated compressor blades with an interface at the compressor wheel.
  • the compressor blade of the compressor may contact, or define an interface, against compressor wheels, such as but not limited to, CrMoV wheels. These areas of contact are at areas of high contact stresses between the elements. These stresses can lead to undesirable effects, such as but not limited to, fretting and galling. These undesirable effects, if left unaddressed, may lead to component failures and possible shutdown of related gas turbine units.
  • a coating for turbomachinery comprises graphite-based solid film lubricant material.
  • a coating for turbomachinery comprises graphite-based solid film lubricant material; where the turbomachinery comprises at least a wheel comprising a slot and a bucket comprising a dovetail, the coating is applied to at least one of the slot and the dovetail; and coating comprises at least one of: graphite-based dry film lubricants, metal filled resin based systems, silicate binder with graphite; and high temperature lubricating additives.
  • a method for coating for turbomachinery to provide at least one of crevice corrosion resistance and fretting resistance comprising providing a coating; and applying the coating to at least one of the slot and the dovetail; wherein the coating comprises graphite-based solid film lubricant material; the turbomachinery comprises at least a wheel comprising a slot and a bucket comprising a dovetail, the coating is applied to; and the coating comprises at least one of graphite-based dry film lubricants, metal filled resin based systems, silicate binder with graphite; and high temperature lubricating additives.
  • FIG. 1 is a perspective view of a portion of a turbine or compressor disc employing balancing apparatus, as embodied by the invention
  • FIG. 2 is a detailed side view of a portion of two adjacent compressor states, as embodied by the invention, which permits the radial insertion of balance weights after assembly of the adjacent stages;
  • FIG. 3 is a further side view of a portion of two adjacent compressor states, as embodied by the invention, which permits the radial insertion of balance weights after assembly of the adjacent stages.
  • turbomachinery such as but not limited to, turbine wheels and compressor wheels, particularly for gas or steam turbines
  • the following embodiment is directed toward a compressor stage of a gas or steam turbine for concreteness of description. This description is not intended to limit the invention in any manner.
  • a compressor stage is conventionally fabricated with a wheel or disc affixed or integrally formed with an axial shaft.
  • Female dovetail regions are machined into the surface of the wheel and male dovetail regions of compressor blades are fitted into the female dovetails.
  • FIG. 1 Illustrated in FIG. 1 is a portion of a compressor 10, for example, a compressor of a gas turbine engine.
  • the compressor 10 includes an inlet; first stage bladed disk assembly 12 disposed upstream of and coaxially with a plurality of circumferentially spaced stator vanes 14 about an engine or compressor longitudinal centerline 16.
  • the bladed disk assembly 12 includes a plurality of circumferentially spaced rotor blades 18 attached to a rotor wheel or disk 20.
  • the blade 18 includes a relatively thin, solid airfoil portion 22 having a tip 24, a root 26, a leading edge 28, and a trailing edge 30.
  • the blade 18 further includes a generally rectangular platform 32 extending laterally outwardly from the airfoil root 26.
  • the platform 32 is relatively highly sloped, upwardly toward the tip 24, from the leading edge 28 to the trailing edge 30, and provides an inner airflow boundary in the compressor 10.
  • the platform 32 includes an upstream, forward end 34 and a downstream aft end 36, the aft end 36 being disposed at a radius greater than that of the forward end 34.
  • the blade 18 also includes a shank 38 extending coaxially from the airfoil 22 at the platform 32, and a conventionally shaped axial entry dovetail 40 extending from the shank 38.
  • the blade 18 can be formed from any appropriate material, suitable for a turbine component blade.
  • the compressor blade can comprise at least one of graphite, graphite containing materials, and other such carbon fiber materials.
  • the blade 18 of the turbomachinery may be formed of a superalloy, such as a precipitation hardenable, nickel-based alloy (Inconnel 718), or from stainless steel materials.
  • a superalloy such as a precipitation hardenable, nickel-based alloy (Inconnel 718), or from stainless steel materials.
  • the wheel or disk 20 includes a plurality of axially disposed circumferentially spaced slots 42 in an outer perimeter 44 thereof which are complementary in shape to the blade dovetails 40, and which receive the dovetails 40 for attaching the blades 18 thereto.
  • Air 46 is suitably channeled through the blades 18 and the vanes 14 and is compressed thereby.
  • a coating 50 is applied to at least one of the bladed disk assembly 12 and the slot 42.
  • the coating 50 is applied to the bladed disk assembly 12 surfaces in the slot 42, as embodied by the invention; however, the coating 50 can be the wheel slot 42.
  • a coating 50 can be applied to either or both adjacent surfaces, of the bladed disk assembly 12 and/or the slot 42.
  • coatings 50 can be difficult due to geometry of these components.
  • some coatings can cause crevice corrosion issues on such materials.
  • coatings 50 as embodied by the invention, comprise a graphite-based solid film lubricant coating.
  • the coating 50 can comprise at least one of graphite based dry film lubricants or metal filled resin based systems that can be applied to at least one of the bladed disk assembly 12 and the wheel slot 42.
  • These coating materials as embodied by the invention, can be used to lower friction coefficients and reduce wear between the bladed disk assembly 12 and the wheel slot 42.
  • the coating 50 as embodied by the invention, provides at least one of anti-fretting resistance and resistance to crevice corrosion.
  • the coating 50 may comprise graphite materials, and it is within the scope of the invention that the coating comprises graphite grease. Moreover, the coating 50, as embodied by the invention, may comprise molybdenum grease, either alone or in combination with other graphite-based solid film lubricant coating materials.
  • materials for the coating include limited to products, such as but not limited to, lubricants; dry lubricants; lubricants and bonding materials in a suitable solvent, an oil-soluble; sulfonate surfactant/wetting agent (for example SurfKote® LOB-1800-G from HOHMAN PLATING & MFG. INC.); titanium containing lubricants, such as but not limited to, Alumazite ZDA (from Tiodize Co., Inc.) and combinations thereof.
  • the coatings comprise a lubricating material, which can be combined with other components that provide desired material characteristics.
  • one non-limiting coating material can comprise silicate binder with graphite and other high temperature lubricating additives. Other additives can be desired dependent on the intended use of the blade, the environment of the blade and associated turbomachinery.
  • the coating 50 are preferably applied to a compressor blade dovetail 40 of the blade 18 where it contacts the wheel slot 42.
  • the coating 50 can be applied to any pressure face surfaces of the dovetail 40 and/or the slot 42, if needed.
  • the coating 50 is applied at a thickness in range from about 0.0005" to about 0.002".
  • the coating 50 can be applied at a thickness, which can prevent galling, seizing and fretting of the dovetail base metal/substrate.
  • the coating 50 can be applied by any appropriate coating process.
  • Exemplary coating processes include, but are not limited to, painting; deposition, such as but not limited to, physical vapor deposition, plasma-enhanced chemical vapor deposition, and chemical vapor deposition; sputtering, such as etching and chemical sputtering; powder coating; air plasma spray, cold spraying, electroplating; and combinations thereof.
  • the blades with the coating provide an anti fretting coating solution that will not cause crevice corrosion.
  • the coating 50 can be applied and coat superalloy substrates, such as a GTD450 blade, which can be difficult since coatings on GTD450 experience crevice corrosion issues.
  • the blades with the coating, as embodied by the invention can run as designed with high contact stresses, which may occur as a result of the operation of the turbomachinery. Further, as embodied by the invention, the coated component should not fail with the same fallout rate in the un-coated version.

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  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Oil, Petroleum & Natural Gas (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Chemistry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP10169196A 2009-07-17 2010-07-12 Revêtement de turbomachine Withdrawn EP2284246A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/504,837 US20130261034A1 (en) 2009-07-17 2009-07-17 Coating for turbomachinery

Publications (1)

Publication Number Publication Date
EP2284246A1 true EP2284246A1 (fr) 2011-02-16

Family

ID=42938408

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10169196A Withdrawn EP2284246A1 (fr) 2009-07-17 2010-07-12 Revêtement de turbomachine

Country Status (4)

Country Link
US (1) US20130261034A1 (fr)
EP (1) EP2284246A1 (fr)
JP (1) JP2011021602A (fr)
CN (1) CN101956727A (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2013217227A (ja) * 2012-04-05 2013-10-24 Mitsubishi Heavy Ind Ltd 燃料ガス圧縮機
CN106379541B (zh) * 2016-08-30 2018-07-17 金嵩 一种飞机起降轮上的驱动部件

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3793195A (en) * 1972-10-10 1974-02-19 Gen Electric Coated bearing surfaces
US5356545A (en) * 1991-01-15 1994-10-18 General Electric Company Curable dry film lubricant for titanium alloys
US5482637A (en) * 1993-07-06 1996-01-09 Ford Motor Company Anti-friction coating composition containing solid lubricants
EP1350817A1 (fr) * 2002-04-02 2003-10-08 Ford Motor Company Un revêtement à faible frottement et résistant à l'usure pour un objet
US20050176592A1 (en) * 2004-02-11 2005-08-11 Tenaris Ag Method of using intrinsically conductive polymers with inherent lubricating properties, and a composition having an intrinsically conductive polymer, for protecting metal surfaces from galling and corrosion
US20080145649A1 (en) * 2006-12-14 2008-06-19 General Electric Protective coatings which provide wear resistance and low friction characteristics, and related articles and methods

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6442563A (en) * 1987-08-11 1989-02-14 Toshiba Corp Thermal spraying method for preventing corrosion of metallic structure
US20060289088A1 (en) * 2005-06-28 2006-12-28 General Electric Company Titanium treatment to minimize fretting
US7506440B2 (en) * 2005-06-28 2009-03-24 General Electric Company Titanium treatment to minimize fretting
US7516547B2 (en) * 2005-12-21 2009-04-14 General Electric Company Dovetail surface enhancement for durability
US20080066288A1 (en) * 2006-09-08 2008-03-20 General Electric Company Method for applying a high temperature anti-fretting wear coating

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3793195A (en) * 1972-10-10 1974-02-19 Gen Electric Coated bearing surfaces
US5356545A (en) * 1991-01-15 1994-10-18 General Electric Company Curable dry film lubricant for titanium alloys
US5482637A (en) * 1993-07-06 1996-01-09 Ford Motor Company Anti-friction coating composition containing solid lubricants
EP1350817A1 (fr) * 2002-04-02 2003-10-08 Ford Motor Company Un revêtement à faible frottement et résistant à l'usure pour un objet
US20050176592A1 (en) * 2004-02-11 2005-08-11 Tenaris Ag Method of using intrinsically conductive polymers with inherent lubricating properties, and a composition having an intrinsically conductive polymer, for protecting metal surfaces from galling and corrosion
US20080145649A1 (en) * 2006-12-14 2008-06-19 General Electric Protective coatings which provide wear resistance and low friction characteristics, and related articles and methods

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
BEALL ET AL: "Solid film lubricants", METAL FINISHING, ELSEVIER, NEW YORK, NY, US, vol. 98, no. 1, 1 January 2000 (2000-01-01), pages 513 - 517, XP005093054, ISSN: 0026-0576 *
DEVINE, M.J., ET AL.: "Inorganic solid film lubricants", JOURNAL OF CHEMICAL AND ENGINEERING DATA, vol. 6, no. 1, 1961, pages 79 - 82, XP002606042 *

Also Published As

Publication number Publication date
CN101956727A (zh) 2011-01-26
JP2011021602A (ja) 2011-02-03
US20130261034A1 (en) 2013-10-03

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