EP2161457A2 - Cale de bord d'attaque d'aube de compresseur et procédé associé - Google Patents

Cale de bord d'attaque d'aube de compresseur et procédé associé Download PDF

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Publication number
EP2161457A2
EP2161457A2 EP09166070A EP09166070A EP2161457A2 EP 2161457 A2 EP2161457 A2 EP 2161457A2 EP 09166070 A EP09166070 A EP 09166070A EP 09166070 A EP09166070 A EP 09166070A EP 2161457 A2 EP2161457 A2 EP 2161457A2
Authority
EP
European Patent Office
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.)
Withdrawn
Application number
EP09166070A
Other languages
German (de)
English (en)
Inventor
Jon C. Schaeffer
Surinder S. Pabla
David A. Helmick
Jeffrey Roberts
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 EP2161457A2 publication Critical patent/EP2161457A2/fr
Withdrawn legal-status Critical Current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.
  • a vane or blade e.g., a turbine compressor blade
  • 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 Figure 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.

Landscapes

  • 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)
EP09166070A 2008-07-31 2009-07-22 Cale de bord d'attaque d'aube de compresseur et procédé associé Withdrawn EP2161457A2 (fr)

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP2161457A2 true EP2161457A2 (fr) 2010-03-10

Family

ID=41558615

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09166070A Withdrawn EP2161457A2 (fr) 2008-07-31 2009-07-22 Cale de bord d'attaque d'aube de compresseur et procédé associé

Country Status (4)

Country Link
US (1) US20100028160A1 (fr)
EP (1) EP2161457A2 (fr)
JP (1) JP2010038156A (fr)
CN (1) CN101639080A (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3513060B1 (fr) 2016-09-13 2020-03-11 Polytech A/S Pale d'éolienne comprenant un couvercle de protection

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FR2942267B1 (fr) * 2009-02-19 2011-05-06 Turbomeca Temoin d'erosion pour roue de compresseur
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US8425196B2 (en) * 2011-01-28 2013-04-23 General Electric Company Wind turbine blades with a hardened substrate construction
US8906181B2 (en) * 2011-06-30 2014-12-09 United Technologies Corporation Fan blade finishing
US20130045105A1 (en) * 2011-08-17 2013-02-21 Howard Daniel Driver Wind turbine blade and method of protecting the same
US10260351B2 (en) * 2012-03-16 2019-04-16 United Technologies Corporation 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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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3513060B1 (fr) 2016-09-13 2020-03-11 Polytech A/S Pale d'éolienne comprenant un couvercle de protection
US10907618B2 (en) 2016-09-13 2021-02-02 Polytech A/S Wind turbine blade including protective cover

Also Published As

Publication number Publication date
JP2010038156A (ja) 2010-02-18
US20100028160A1 (en) 2010-02-04
CN101639080A (zh) 2010-02-03

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