US20100028160A1 - Compressor blade leading edge shim and related method - Google Patents

Compressor blade leading edge shim and related method Download PDF

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Publication number
US20100028160A1
US20100028160A1 US12/222,067 US22206708A US2010028160A1 US 20100028160 A1 US20100028160 A1 US 20100028160A1 US 22206708 A US22206708 A US 22206708A US 2010028160 A1 US2010028160 A1 US 2010028160A1
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United States
Prior art keywords
shim
compressor blade
leading edge
tin
erosion
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
US12/222,067
Inventor
Jon C. Schaeffer
Surinder S. Pabla
David A. Helmick
Jeffrey Roberts
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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 US12/222,067 priority Critical patent/US20100028160A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ROBERTS, JEFFREY, SCHAEFFER, JON C., HELMICK, DAVID A., PABLA, SURINDER S.
Priority to EP09166070A priority patent/EP2161457A2/en
Priority to JP2009172612A priority patent/JP2010038156A/en
Priority to CN200910165831A priority patent/CN101639080A/en
Publication of US20100028160A1 publication Critical patent/US20100028160A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/005—Repairing methods or devices
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • 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
    • F05D2260/00—Function
    • F05D2260/95—Preventing corrosion
    • 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
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/228—Nitrides
    • F05D2300/2284—Nitrides of titanium
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49337—Composite blade

Definitions

  • This invention relates generally to turbine technology and, more specifically, to an article and a method for mitigating damage caused by compressor blade leading edge erosion and/or corrosion.
  • Turbine blades and particularly the leading edges of the turbine compressor blades or airfoils, are particularly susceptible to erosion and/or corrosion resulting from exposure to harsh environments. Repair and/or replacement of damaged turbine blades requires costly downtime that may not coincide with normal service intervals.
  • the invention relates to a compressor blade comprising an airfoil portion and a mounting portion; the airfoil portion having leading and trailing edges, the leading edge having an erosion or corrosion-resistant shim attached thereto.
  • the invention in another aspect, relates to a method of improving erosion or corrosion resistance at the leading edge of a compressor blade airfoil comprising: a) cleaning a leading edge portion of the compressor blade airfoil; and b) attaching one or more erosion or corrosion-resistant shims to the leading edge portion.
  • FIG. 1 is a perspective view of a compressor blade in accordance with an exemplary embodiment of the invention.
  • FIG. 2 is a section taken along the line 2 - 2 in FIG. 1 , but with the shim exaggerated in scale.
  • a vane or blade 10 e.g., a turbine compressor blade, includes an airfoil portion 12 and a dovetail mounting portion 14 .
  • the airfoil portion 12 has a leading edge 16 , a trailing edge 18 , a pressure side 20 and a suction side 22 .
  • leading edge 16 is most susceptible to erosion and/or corrosion due to incoming air flow (containing, for example, dry particles, salt fog, etc.) at the compressor inlet.
  • incoming air flow containing, for example, dry particles, salt fog, etc.
  • one or more shims 24 may be applied to the leading edge 16 of the airfoil portion.
  • the shim 24 substantially encloses the leading edge 16 , extending into both the pressure and suction sides 20 , 22 of the airfoil. Note that in FIG. 2 , the shim is shown in greatly exaggerated scale simply to facilitate an understanding of the invention.
  • One shim may extend along part or substantially the entire length of the leading edge, or alternatively, plural shim segments may be employed to reduce shear strain at the airfoil/shim interface.
  • the shim 24 has a thickness in a range of from 1 to 30 mils.
  • the shim or shims may be composed of corrosion-resistant compositions including Cr-rich materials such as Ni-25Cr sheet; Al-rich or Ti-rich materials. Alternatively, hard, erosion resistant materials such as TiN, Ti/TiN, TiN/CrN, NiCrWC, etc. may be employed.
  • the shim or shims could also be constructed of an erosion-resistant polymeric material such as polypropylene, or a corrosion-resistant tape, e.g., 3M Protective Polyurethane Tape, having a thickness of about 1-10 mils. It will be appreciated that the shim or shims may also be constructed of a suitable metal coated with an erosion or corrosion resistant material, i.e., using a powder form of the compositions mentioned above.
  • the shim or shims 24 in metal form may be attached to the leading edge 16 by any of several known techniques such as, for example, welding, brazing, soldering and/or by an adhesive film.
  • One suitable adhesive film is available under the name 3M Structural Adhesive Tape.
  • Additional adhesive material shown at 26 , 28 may be applied along the edges 30 , 32 of the metal shim in order to smooth out shim edges where they interface with the airfoil.
  • thermal expansion characteristics of the airfoil and shim should be matched to the extent possible to reduce the amount of cyclic straining, noting that in the front end of the machine temperature swings are relatively mild, i.e., from about 70° F. to about 400° F.
  • low temperature adhesive for attaching the metal shims, or for use as the shims themselves are advantageous in that no cutting is required, thus preserving the properties of the base metal.
  • shim preparation at the leading edge 16 Prior to the attachment of one or more shims 24 , surface preparation at the leading edge 16 is required through milling, shot-peening, grit blasting, vibratory finishing or combinations of the above.
  • a high pressure adhesive tape such as the 3M structural adhesive tape mentioned above
  • additional preparation is required for attachment of a shim by means of a high pressure adhesive tape such as the 3M structural adhesive tape mentioned above.
  • the facing surfaces of the shim and the airfoil leading edge may be rinsed, alkaline-degreased, etched, dried, primed and cured.
  • the blade may be placed in an autoclave, for example, for curing the adhesive.
  • the facing surfaces When utilizing a low temperature adhesive such as the 3M Protective Polyurethane Tape as the shim, the facing surfaces simply need to be rinsed and degreased prior to application of the tape.
  • a low temperature adhesive such as the 3M Protective Polyurethane Tape
  • shims described herein would be added to blades at the time of manufacture. On the other hand, they could be retrofitted to existing blades so long as the blades are in acceptable condition.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A method of improving an erosion resistance at the leading edge of a compressor blade includes: a) cleaning a leading edge portion of the compressor blade airfoil; and b) attaching one or more erosion or corrosion-resistant shims to the leading edge portion.

Description

    BACKGROUND OF THE INVENTION
  • This invention relates generally to turbine technology and, more specifically, to an article and a method for mitigating damage caused by compressor blade leading edge erosion and/or corrosion.
  • Compressor blade leading edge erosion/corrosion is a common problem in turbine engines. Turbine blades, and particularly the leading edges of the turbine compressor blades or airfoils, are particularly susceptible to erosion and/or corrosion resulting from exposure to harsh environments. Repair and/or replacement of damaged turbine blades requires costly downtime that may not coincide with normal service intervals.
  • It would be advantageous, therefore, to develop techniques or processes to mitigate the incidence or damage caused by erosion and/or corrosion of blade leading edges.
    • BRIEF DESCRIPTION OF THE INVENTION
  • In accordance with one exemplary but nonlimiting embodiment, the invention relates to a compressor blade comprising an airfoil portion and a mounting portion; the airfoil portion having leading and trailing edges, the leading edge having an erosion or corrosion-resistant shim attached thereto.
  • In another aspect, the invention relates to a method of improving erosion or corrosion resistance at the leading edge of a compressor blade airfoil comprising: a) cleaning a leading edge portion of the compressor blade airfoil; and b) attaching one or more erosion or corrosion-resistant shims to the leading edge portion.
  • The invention will now be described in more detail in connection with the drawings identified below.
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • FIG. 1 is a perspective view of a compressor blade in accordance with an exemplary embodiment of the invention; and
  • FIG. 2 is a section taken along the line 2-2 in FIG. 1, but with the shim exaggerated in scale.
    •  DETAILED DESCRIPTION OF THE INVENTION
  • With reference to FIG. 1, a vane or blade 10, e.g., a turbine compressor blade, includes an airfoil portion 12 and a dovetail mounting portion 14. The airfoil portion 12 has a leading edge 16, a trailing edge 18, a pressure side 20 and a suction side 22.
  • It is the leading edge 16 that is most susceptible to erosion and/or corrosion due to incoming air flow (containing, for example, dry particles, salt fog, etc.) at the compressor inlet.
  • In accordance with a non-limiting exemplary embodiment of this invention, one or more shims 24 may be applied to the leading edge 16 of the airfoil portion. With further reference to FIG. 2, the shim 24 substantially encloses the leading edge 16, extending into both the pressure and suction sides 20, 22 of the airfoil. Note that in FIG. 2, the shim is shown in greatly exaggerated scale simply to facilitate an understanding of the invention. One shim may extend along part or substantially the entire length of the leading edge, or alternatively, plural shim segments may be employed to reduce shear strain at the airfoil/shim interface.
  • In a preferred configuration, the shim 24 has a thickness in a range of from 1 to 30 mils. The shim or shims may be composed of corrosion-resistant compositions including Cr-rich materials such as Ni-25Cr sheet; Al-rich or Ti-rich materials. Alternatively, hard, erosion resistant materials such as TiN, Ti/TiN, TiN/CrN, NiCrWC, etc. may be employed. The shim or shims could also be constructed of an erosion-resistant polymeric material such as polypropylene, or a corrosion-resistant tape, e.g., 3M Protective Polyurethane Tape, having a thickness of about 1-10 mils. It will be appreciated that the shim or shims may also be constructed of a suitable metal coated with an erosion or corrosion resistant material, i.e., using a powder form of the compositions mentioned above.
  • The shim or shims 24 in metal form may be attached to the leading edge 16 by any of several known techniques such as, for example, welding, brazing, soldering and/or by an adhesive film. One suitable adhesive film is available under the name 3M Structural Adhesive Tape. Additional adhesive material shown at 26, 28, may be applied along the edges 30, 32 of the metal shim in order to smooth out shim edges where they interface with the airfoil.
  • In any event, thermal expansion characteristics of the airfoil and shim should be matched to the extent possible to reduce the amount of cyclic straining, noting that in the front end of the machine temperature swings are relatively mild, i.e., from about 70° F. to about 400° F. In this regard, low temperature adhesive for attaching the metal shims, or for use as the shims themselves, are advantageous in that no cutting is required, thus preserving the properties of the base metal.
  • Prior to the attachment of one or more shims 24, surface preparation at the leading edge 16 is required through milling, shot-peening, grit blasting, vibratory finishing or combinations of the above. For attachment of a shim by means of a high pressure adhesive tape such as the 3M structural adhesive tape mentioned above, additional preparation is required. For example, the facing surfaces of the shim and the airfoil leading edge may be rinsed, alkaline-degreased, etched, dried, primed and cured. After the shim is applied by means of the adhesive tape, the blade may be placed in an autoclave, for example, for curing the adhesive.
  • When utilizing a low temperature adhesive such as the 3M Protective Polyurethane Tape as the shim, the facing surfaces simply need to be rinsed and degreased prior to application of the tape.
  • It is contemplated that the shims described herein would be added to blades at the time of manufacture. On the other hand, they could be retrofitted to existing blades so long as the blades are in acceptable condition.
  • While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.

Claims (19)

1. A compressor blade comprising an airfoil portion and a mounting portion; the airfoil portion having leading and trailing edges, the leading edge having an erosion-resistant shim attached thereto.
2. The compressor blade of claim 1 wherein said shim is comprised of a material selected from a group comprising TiN, Ti/TiN, TiN/CrN, NiCrWC.
3. The compressor blade of claim 1 wherein the shim is composed at least in part of a composition selected from a group comprising Cr, Al or Ti-rich materials.
4. The compressor blade of claim 1 wherein the shim is comprised of a metal coated with an erosion or corrosion resistant material.
5. The compressor blade of claim 1 wherein said shim is attached by welding, brazing or soldering.
6. The compressor blade of claim 1 wherein said shim is attached by adhesive.
7. The compressor blade of claim 1 wherein said shim comprises plural shim segments.
8. The compressor blade of claim 1 wherein said shim is between about 1 and about 25 mils thick.
9. The compressor blade of claim 1 wherein said shim is made of a polymeric material.
10. The compressor blade of claim 9 wherein said polymeric material comprises polypropylene.
11. A method of improving an erosion/corrosion resistance at the leading edge portion of a compressor blade airfoil comprising:
a) preparing the leading edge portion of the compressor blade airfoil; and
b) attaching one or more shims to said leading edge portion.
12. The method of claim 11 wherein step (a) is carried out by milling, shot-peening, grit blasting, vibratory finishing or combinations thereof.
13. The method of claim 11 wherein said shim said shim is comprised of a material selected from a group comprising TiN, Ti/TiN, TiN/CrN, NiCrWC.
14. The method of claim 11 wherein the shim is composed at least in part of a composition selected from a Cr, Al or Ti-rich material.
15. The method of claim 11 wherein the shim is comprised of a metal coated with an erosion or corrosion resistant material.
16. The method of claim 11 wherein said shim is attached by welding, brazing or soldering.
18. The method of claim 11 wherein said shim is attached by adhesive.
19. The method of claim 11 wherein said shim is made of a polyurethane tape.
20. The method of claim 11 wherein said shim is made of a polymeric material.
US12/222,067 2008-07-31 2008-07-31 Compressor blade leading edge shim and related method Abandoned US20100028160A1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US12/222,067 US20100028160A1 (en) 2008-07-31 2008-07-31 Compressor blade leading edge shim and related method
EP09166070A EP2161457A2 (en) 2008-07-31 2009-07-22 Compressor blade leading edge shim and related method
JP2009172612A JP2010038156A (en) 2008-07-31 2009-07-24 Compressor blade leading edge shim and related method
CN200910165831A CN101639080A (en) 2008-07-31 2009-07-30 Compressor blade leading edge shim and related method

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Application Number Priority Date Filing Date Title
US12/222,067 US20100028160A1 (en) 2008-07-31 2008-07-31 Compressor blade leading edge shim and related method

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US20100028160A1 true US20100028160A1 (en) 2010-02-04

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US (1) US20100028160A1 (en)
EP (1) EP2161457A2 (en)
JP (1) JP2010038156A (en)
CN (1) CN101639080A (en)

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US20130045105A1 (en) * 2011-08-17 2013-02-21 Howard Daniel Driver Wind turbine blade and method of protecting the same
US20130239586A1 (en) * 2012-03-16 2013-09-19 Michael Parkin Fan blade and method of manufacturing same
US20140030497A1 (en) * 2012-07-30 2014-01-30 United Technologies Corporation Localized transitional coating of turbine components
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US10562241B2 (en) * 2016-04-05 2020-02-18 Rolls-Royce Plc Fan blade and method of manufacturing a fan blade
US10907483B2 (en) * 2014-04-07 2021-02-02 Mitsubishi Power, Ltd. Turbine blade, erosion shield forming method, and turbine blade manufacturing method
US11105210B2 (en) * 2015-09-28 2021-08-31 Safran Aircraft Engines Blade comprising a leading edge shield and method for producing the blade
US20220154685A1 (en) * 2019-03-08 2022-05-19 Siemens Gamesa Renewable Energy A/S Method of shaping an edge seal for a rotor blade add-on
US20220162947A1 (en) * 2020-11-25 2022-05-26 Mitsubishi Heavy Industries, Ltd. Steam turbine rotor blade
CN114542192A (en) * 2020-11-25 2022-05-27 三菱重工业株式会社 Steam turbine rotor blade, method for manufacturing steam turbine rotor blade, and method for modifying steam turbine rotor blade
US11454209B2 (en) * 2018-09-10 2022-09-27 Siemens Gamesa Renewable Energy A/S Method of providing an edge seal for a rotor blade add-on
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