EP1985803A1 - Verfahren zum Herstellen von beschichteten Turbinenlaufschaufeln - Google Patents

Verfahren zum Herstellen von beschichteten Turbinenlaufschaufeln Download PDF

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Publication number
EP1985803A1
EP1985803A1 EP07008237A EP07008237A EP1985803A1 EP 1985803 A1 EP1985803 A1 EP 1985803A1 EP 07008237 A EP07008237 A EP 07008237A EP 07008237 A EP07008237 A EP 07008237A EP 1985803 A1 EP1985803 A1 EP 1985803A1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
blade
turbine
airfoil
natural frequency
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Withdrawn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
EP07008237A
Other languages
German (de)
English (en)
French (fr)
Inventor
Fathi Ahmad
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP07008237A priority Critical patent/EP1985803A1/de
Priority to AT08736059T priority patent/ATE483097T1/de
Priority to EP08736059A priority patent/EP2137381B1/de
Priority to ES08736059T priority patent/ES2353358T3/es
Priority to PL08736059T priority patent/PL2137381T3/pl
Priority to MX2009010923A priority patent/MX2009010923A/es
Priority to DE502008001450T priority patent/DE502008001450D1/de
Priority to CA2684810A priority patent/CA2684810C/en
Priority to US12/596,780 priority patent/US8607455B2/en
Priority to CN2008800121475A priority patent/CN101663465B/zh
Priority to RU2009142996/06A priority patent/RU2430239C2/ru
Priority to PCT/EP2008/054338 priority patent/WO2008128902A1/de
Priority to JP2010504614A priority patent/JP2010525229A/ja
Publication of EP1985803A1 publication Critical patent/EP1985803A1/de
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • F01D5/288—Protective coatings for blades
    • 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
    • F01D5/14—Form or construction
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • F05D2230/10—Manufacture by removing material
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/19—Two-dimensional machined; miscellaneous
    • 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
    • Y10T29/49318—Repairing or disassembling
    • 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
    • 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
    • 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
    • Y10T29/49339—Hollow blade
    • 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
    • Y10T29/49718—Repairing
    • Y10T29/49721—Repairing with disassembling
    • Y10T29/49723—Repairing with disassembling including reconditioning of part
    • Y10T29/49725—Repairing with disassembling including reconditioning of part by shaping
    • Y10T29/49726—Removing material

Definitions

  • the invention relates to a method for producing a coated turbine blade in which a turbine blade is coated with at least one protective layer and wherein at least one recess is inserted into a blade tip of a blade of the turbine blade to adjust the natural frequency of the turbine blade.
  • a corrosion protection layer of the type MCrAlY is often applied to the cast turbine blade.
  • the application of the protective layer takes place in the region of its surface, which is exposed to the hot gas during operation of the gas turbine. This area includes both the airfoil and the platform of the turbine blade on which the airfoil forms.
  • a heat-insulating layer can also be applied in the abovementioned area in order to minimize the heat input from the hot gas into the base material of the turbine blade.
  • the turbine blades are designed such that their natural frequency deviates from the excitation frequencies of the stationary gas turbine. Therefore, during the development of the turbine blade, care is taken that the finished turbine blade as a whole meets the requirements for self-resonance.
  • the object of the invention is to provide a method for producing coated turbine blades whose natural frequency corresponds to the requirements for use within a stationary gas turbine.
  • the application of a corrosion layer to a turbine blade results in a significant increase in mass, which reduces the natural frequency of the turbine blade in question.
  • the natural frequency of the turbine blade comes close to one of the excitation frequencies, so that a harmful or life-shortening vibration excitation of the turbine blade or the blade during operation of the gas turbine is more likely.
  • Turbine blades which continuously experience vibrational excitation and oscillate continuously during operation of the gas turbine, have an increased risk of breakage and shortened life.
  • the load experienced by the turbine blade by vibrational excitation is also referred to as HCF stress (high cycle fatigue).
  • the invention proposes, in particular a used turbine blade, which has already consumed part of its life and by a so-called.
  • Refurbishment - refurbishment - to obtain a life extension to adapt for operation in the stationary gas turbine. Because the refurbishment often involves stripping a turbine blade and recoating in the aforementioned ranges, the refurbished turbine blade after coating is subjected to a natural frequency check, which may be improved by removing mass in the area of the blade tip of the blade. By removing the mass at the free end of the turbine blade, the natural frequency is shifted away from the excitation frequencies.
  • the holes can be a drilling depth of up to 50% of - based on the installation position of the turbine blade in a stationary gas turbine - radial extent of the blade. This is possible because in this area comparatively low mechanical loads occur in the airfoil and a weakening of the material cross-section is admissible despite the high centrifugal forces.
  • a plurality of bores are performed, which are distributed along the airfoil center line. It is envisaged that when a given mass is to be removed by drilling in the airfoil, rather a larger number of holes be provided with a small drilling depth than a small number of holes with a larger drilling depth.
  • the method may also be applied to a turbine blade having an internally coolable airfoil.
  • the holes are provided at the points of the blade, in which so-called support ribs between the suction side airfoil wall and the pressure-side airfoil wall open into this.
  • it can be provided that after the introduction of the holes whose openings are closed on the surface by means of a plug or a solder. The holes are not filled, so that a cavity remains.
  • the inventive method 10 is in FIG. 1 shown.
  • the method 10 of producing coated turbine blades comprises, in a first step 12, the coating of the turbine blade with a protective layer.
  • the protective layer is preferably a corrosion protection layer of the MCrAlY type.
  • a two-layer protective layer comprising, as a bondcoat, a layer of the MCrAlY type, on which a ceramic thermal barrier coating (TBC) has been applied further out. Since the turbine blade is cast as a rule and accordingly comprises a cast base body, by the application of the protective layer, in particular a corrosion protection layer whose mass is further increased.
  • the change in the natural frequency of the turbine blade that accompanies the mass increase can be compensated for by introducing recesses on the blade tip of the blade of the turbine blade in a second method step 14. It is provided that so many and such deep recesses are introduced into the end face of the blade of the turbine blade until the turbine blade meets the requirements of the natural frequency. It may be that despite the application of the method according to the invention, the natural frequency can not be strongly influenced enough that it meets the requirements. In this case, the turbine blade is not suitable for further use.
  • FIG. 2 a method 20 is shown in which used, ie already used in the operation of a stationary gas turbine turbine blades are partially replaced by a refurbishment process - the so-called refurbishment.
  • the refurbishment serves as a lifetime extending measure for the turbine blade.
  • a first method step 22 turbine blades are exposed to a hot gas of the gas turbine during their operation.
  • the work-up process comprises a step 24, in which optionally coated turbine blades are stripped. Decoating is required when, for example, there are intermediate or major cracks in the protective layer or when partial chipping or abrasion causes the actual layer thickness to shrink below a required minimum.
  • a subsequent optional step 26 cracks which may have occurred in the base material of the turbine blade are eliminated by known repair methods.
  • the turbine blade is then recoated with a single-layer or two-layer protective layer, after which drilling of holes in the end face of the blade tip in the direction of a blade root of the turbine blade to adjust the natural frequency can be drilled in a final step.
  • a turbine blade 40 is shown partially in perspective.
  • the turbine blade 40 comprises, as is known, a blade root which is not shown in cross-section in the manner of a fir tree and is adjoined by a blade platform (not shown).
  • a free-standing airfoil 42 Arranged on the blade platform is a free-standing airfoil 42, which is aerodynamically curved in a drop-shaped cross section.
  • the airfoil 42 includes a pressure side 44 and a suction side 46.
  • FIG. 3 only the blade tip 48 is shown, which is opposite to the attached to the platform end of the blade 42.
  • the aerodynamically curved airfoil 42 includes a blade centerline 50 that extends centrally between the suction side 46 and the pressure side 44 from a leading edge to a trailing edge.
  • the airfoil midline 50 is shown in phantom line style. Distributed along the airfoil mid-line 50, for example, four recesses in the form of bores 52 are provided, which extend from the end face of the airfoil 42 in the direction of Shovel foot of the turbine blade 40 extend. By means of the holes 52, the weight was reduced at the free end of the turbine blade 40, whereby the natural frequency has been shifted to higher frequencies.
  • FIG. 3 shows the cross-section through the airfoil 42 of a turbine blade 40 made by the method of the present invention.
  • the cut was placed in the area of the blade tip 48.
  • the turbine blade 40 according to FIG. 4 includes the molded base body 41, on the suction side and on the pressure side, a protective layer 54 has been applied.
  • the protective layer 54 has significantly increased the mass of the turbine blade 40, resulting in a change in the natural frequency to lower frequencies.
  • 42 bores 52 are introduced from the end face of the blade.
  • the holes 52 are provided at the locations in the airfoil 42 at which the support ribs 56 present in the interior connect to the pressure-side or suction-side blade wall 44, 46. It can also be provided to attach the bores 52 in the region of the trailing edge of the turbine blade 40, on which the suction-side pressure wall 46 unites with the pressure-side blade wall 44.
  • the invention thus proposes a method for producing coated turbine blades 40 whose frequency characteristic can be adapted to the required boundary conditions in a particularly simple manner.
  • the introduction of recesses into a blade tip 48 of the airfoil 42 of the turbine blade 40 takes place after the coating of the turbine blade 40.
  • a method is specified with which the vibration characteristic of the turbine blade set particularly simple and variable can be. Scrap of turbine blades 40 can thus be reduced.
  • already used turbine blades can be prepared in a refurbishment process so that they can be reused.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Application Of Or Painting With Fluid Materials (AREA)
EP07008237A 2007-04-23 2007-04-23 Verfahren zum Herstellen von beschichteten Turbinenlaufschaufeln Withdrawn EP1985803A1 (de)

Priority Applications (13)

Application Number Priority Date Filing Date Title
EP07008237A EP1985803A1 (de) 2007-04-23 2007-04-23 Verfahren zum Herstellen von beschichteten Turbinenlaufschaufeln
AT08736059T ATE483097T1 (de) 2007-04-23 2008-04-10 Verfahren zum herstellen von beschichteten turbinenlaufschaufeln
EP08736059A EP2137381B1 (de) 2007-04-23 2008-04-10 Verfahren zum herstellen von beschichteten turbinenlaufschaufeln
ES08736059T ES2353358T3 (es) 2007-04-23 2008-04-10 Procedimiento para la producción de palas móviles de turbinas recubiertas.
PL08736059T PL2137381T3 (pl) 2007-04-23 2008-04-10 Sposób wytwarzania powlekanych łopatek wirnika turbiny
MX2009010923A MX2009010923A (es) 2007-04-23 2008-04-10 Procedimiento para producir alabe de turbina recubiertas y un anillo de cuchilla para un rotor de una turbina con flujo axial.
DE502008001450T DE502008001450D1 (de) 2007-04-23 2008-04-10 Verfahren zum herstellen von beschichteten turbinenlaufschaufeln
CA2684810A CA2684810C (en) 2007-04-23 2008-04-10 Method for the production of coated turbine moving blades
US12/596,780 US8607455B2 (en) 2007-04-23 2008-04-10 Method for the production of coated turbine moving blades and moving-blade ring for a rotor of an axial-throughflow turbine
CN2008800121475A CN101663465B (zh) 2007-04-23 2008-04-10 用于制造带有涂层的透平动叶片的方法
RU2009142996/06A RU2430239C2 (ru) 2007-04-23 2008-04-10 Способ изготовления снабженных покрытием лопаток турбины
PCT/EP2008/054338 WO2008128902A1 (de) 2007-04-23 2008-04-10 Verfahren zum herstellen von beschichteten turbinenlaufschaufeln und laufschaufelring für einen rotor einer axial durchströmten turbine
JP2010504614A JP2010525229A (ja) 2007-04-23 2008-04-10 被覆されたタービン動翼を製造するための方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07008237A EP1985803A1 (de) 2007-04-23 2007-04-23 Verfahren zum Herstellen von beschichteten Turbinenlaufschaufeln

Publications (1)

Publication Number Publication Date
EP1985803A1 true EP1985803A1 (de) 2008-10-29

Family

ID=38283287

Family Applications (2)

Application Number Title Priority Date Filing Date
EP07008237A Withdrawn EP1985803A1 (de) 2007-04-23 2007-04-23 Verfahren zum Herstellen von beschichteten Turbinenlaufschaufeln
EP08736059A Not-in-force EP2137381B1 (de) 2007-04-23 2008-04-10 Verfahren zum herstellen von beschichteten turbinenlaufschaufeln

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP08736059A Not-in-force EP2137381B1 (de) 2007-04-23 2008-04-10 Verfahren zum herstellen von beschichteten turbinenlaufschaufeln

Country Status (12)

Country Link
US (1) US8607455B2 (zh)
EP (2) EP1985803A1 (zh)
JP (1) JP2010525229A (zh)
CN (1) CN101663465B (zh)
AT (1) ATE483097T1 (zh)
CA (1) CA2684810C (zh)
DE (1) DE502008001450D1 (zh)
ES (1) ES2353358T3 (zh)
MX (1) MX2009010923A (zh)
PL (1) PL2137381T3 (zh)
RU (1) RU2430239C2 (zh)
WO (1) WO2008128902A1 (zh)

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WO2014053185A1 (de) * 2012-10-05 2014-04-10 Siemens Aktiengesellschaft Verfahren zur aufbereitung einer gasturbinenschaufel sowie gasturbine mit derartiger schaufel
EP3187685A1 (de) * 2015-12-28 2017-07-05 Siemens Aktiengesellschaft Verfahren zum herstellen eines grundkörpers einer turbinenschaufel
EP3456921A3 (en) * 2017-09-18 2019-04-03 Pratt & Whitney Canada Corp. Compressor rotor with coated blades
US10837459B2 (en) 2017-10-06 2020-11-17 Pratt & Whitney Canada Corp. Mistuned fan for gas turbine engine
US10865806B2 (en) 2017-09-15 2020-12-15 Pratt & Whitney Canada Corp. Mistuned rotor for gas turbine engine
US11002293B2 (en) 2017-09-15 2021-05-11 Pratt & Whitney Canada Corp. Mistuned compressor rotor with hub scoops

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US9216491B2 (en) * 2011-06-24 2015-12-22 General Electric Company Components with cooling channels and methods of manufacture
US9249670B2 (en) 2011-12-15 2016-02-02 General Electric Company Components with microchannel cooling
US10982551B1 (en) 2012-09-14 2021-04-20 Raytheon Technologies Corporation Turbomachine blade
US11199096B1 (en) * 2017-01-17 2021-12-14 Raytheon Technologies Corporation Turbomachine blade
FR3067955B1 (fr) * 2017-06-23 2019-09-06 Safran Aircraft Engines Procede de positionnement d'une piece creuse
CN108757507A (zh) * 2018-05-03 2018-11-06 西北工业大学 一种带有可变弯度导流叶片的压气机
CN108730203A (zh) * 2018-05-03 2018-11-02 西北工业大学 一种带有可转导流叶片的压气机
JP7219829B2 (ja) * 2019-06-28 2023-02-08 シーメンス エナジー グローバル ゲゼルシャフト ミット ベシュレンクテル ハフツング ウント コンパニー コマンディートゲゼルシャフト モーダル周波数応答の調整を行うタービン翼形部

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WO2014053185A1 (de) * 2012-10-05 2014-04-10 Siemens Aktiengesellschaft Verfahren zur aufbereitung einer gasturbinenschaufel sowie gasturbine mit derartiger schaufel
US10215034B2 (en) 2012-10-05 2019-02-26 Siemens Aktiengesellschaft Method for treating a gas turbine blade and gas turbine having said blade
US10995625B2 (en) 2012-10-05 2021-05-04 Siemens Aktiengesellschaft Method for treating a gas turbine blade and gas turbine having said blade
EP3187685A1 (de) * 2015-12-28 2017-07-05 Siemens Aktiengesellschaft Verfahren zum herstellen eines grundkörpers einer turbinenschaufel
WO2017114644A1 (de) * 2015-12-28 2017-07-06 Siemens Aktiengesellschaft Verfahren zum herstellen eines grundkörpers einer turbinenschaufel
US10669857B2 (en) 2015-12-28 2020-06-02 Siemens Aktiengesellschaft Method for producing a base body of a turbine blade
US10865806B2 (en) 2017-09-15 2020-12-15 Pratt & Whitney Canada Corp. Mistuned rotor for gas turbine engine
US11002293B2 (en) 2017-09-15 2021-05-11 Pratt & Whitney Canada Corp. Mistuned compressor rotor with hub scoops
EP3456921A3 (en) * 2017-09-18 2019-04-03 Pratt & Whitney Canada Corp. Compressor rotor with coated blades
US10443411B2 (en) 2017-09-18 2019-10-15 Pratt & Whitney Canada Corp. Compressor rotor with coated blades
US10689987B2 (en) 2017-09-18 2020-06-23 Pratt & Whitney Canada Corp. Compressor rotor with coated blades
US10837459B2 (en) 2017-10-06 2020-11-17 Pratt & Whitney Canada Corp. Mistuned fan for gas turbine engine

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CA2684810A1 (en) 2008-10-30
EP2137381A1 (de) 2009-12-30
CN101663465A (zh) 2010-03-03
CA2684810C (en) 2013-02-05
PL2137381T3 (pl) 2011-04-29
WO2008128902A1 (de) 2008-10-30
CN101663465B (zh) 2013-07-31
DE502008001450D1 (de) 2010-11-11
ES2353358T3 (es) 2011-03-01
RU2430239C2 (ru) 2011-09-27
RU2009142996A (ru) 2011-05-27
EP2137381B1 (de) 2010-09-29
JP2010525229A (ja) 2010-07-22
US8607455B2 (en) 2013-12-17
ATE483097T1 (de) 2010-10-15
MX2009010923A (es) 2009-11-02
US20100129554A1 (en) 2010-05-27

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