EP3307989B1 - Gasturbinenschaufel oder verdichterschaufel mit anti-fretting-beschichtung im schaufelfussbereich und rotor - Google Patents

Gasturbinenschaufel oder verdichterschaufel mit anti-fretting-beschichtung im schaufelfussbereich und rotor Download PDF

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Publication number
EP3307989B1
EP3307989B1 EP15751016.5A EP15751016A EP3307989B1 EP 3307989 B1 EP3307989 B1 EP 3307989B1 EP 15751016 A EP15751016 A EP 15751016A EP 3307989 B1 EP3307989 B1 EP 3307989B1
Authority
EP
European Patent Office
Prior art keywords
blade
rotor
area
compressor
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.)
Active
Application number
EP15751016.5A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3307989A1 (de
Inventor
Ronald Wallstabe
Toni Kreibich
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 Energy Global GmbH and Co KG
Original Assignee
Siemens AG
Siemens 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 Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to PL15751016T priority Critical patent/PL3307989T3/pl
Publication of EP3307989A1 publication Critical patent/EP3307989A1/de
Application granted granted Critical
Publication of EP3307989B1 publication Critical patent/EP3307989B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • 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
    • F04D29/34—Blade mountings
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • the invention relates to a gas turbine blade or a compressor blade, which has a polymer coating in the fastening area, and a rotor.
  • a rotor blade is positively connected in the groove area or fastening area to a wheel disk via a corresponding groove.
  • the rotor blades are assembled and disassembled in the axial direction of the groove.
  • rotor blades are loaded both by the centrifugal force, depending on the blade weight and the rotor speed, and by the aerodynamic forces. These forces have to be absorbed in the contact area between the blade root and the wheel disk groove, the so-called wing area.
  • the following damage mechanisms can occur on the compressor blade roots and wheel disk grooves in the area of the wing flanks: "Fretting” and / or “Fretting Fatigue”, as well as local adhesion / cold welding and as a result material transfer with subsequent "Scoring / Galling "while dismantling the shovel.
  • the last-mentioned damage mechanisms can make it difficult to dismantle rotor blades, which is necessary for maintenance purposes.
  • the coatings that have hitherto generally been used to reduce or prevent "fretting" findings are metallic, e.g. CuNiIn or NiTiCr.
  • the methods used for this are, for example, cold gas spraying, flame spraying and plasma spraying, such as HVOF - "High Velocity Oxygen Fuel Spray” or APS.
  • U.S. 4,790,723 discloses, for example, a gas turbine blade that has at least one airfoil area with a polymer coating at the blade root.
  • the object is achieved by a turbine or compressor blade according to claim 1 and a rotor according to claim 3.
  • Figure 1 shows part of a rotor 1 which has a wheel disk 4 with a groove area 13 within the wheel disk 4, in which 13 a turbine blade 6 or a compressor blade 6 is arranged. A blade root 7 of the blade 6 is introduced in the groove area 13.
  • a blade 10 of the blade 6 protrudes beyond an outer surface 29 of the wheel disk 4.
  • the blade root 7 has a lower region 20 which is slightly convexly curved.
  • the more strongly curved area 23 is followed by a supporting flank area 24 which comes into contact with the wheel disk 4.
  • the wing area 24 is designed to be flat.
  • the supporting flank area 24 is optionally followed by a further end area 26, which can be configured in various ways and here runs perpendicular to the surface 29 of the wheel disk 4.
  • the polymer coating 25 then preferably extends over the entire axial length of the blade root 7.
  • An inner surface 22 of the groove area 13 can also have a polymer coating, that is to say the wheel disk 4. This polymer coating can be present in addition to the polymer coating 25 of the blade 6. It then also preferably extends over the entire axial length of the groove area 13.
  • This coating is preferably based on one or more fluoropolymers, e.g. Polytetrafluoroethylene (PTFE), perfluoroalkoxy (PFA), perfluoroethylene propylene (FEP).
  • PTFE Polytetrafluoroethylene
  • PFA perfluoroalkoxy
  • FEP perfluoroethylene propylene
  • one or more solid lubricants can also preferably be present, which are embedded in the matrix of the polymer coating 25 of the blade 6 or of the groove area 13.
  • these coating systems can reduce the energy input through relative movement between the components rotor blade and wheel disk groove and reduce or prevent possible “fretting” and thus also "fretting fatigue”.
  • the limiting factor for the proposed polymer-based coating 25 is the use temperature. In the case of compressors, depending on the compressor parameters, this allows only the use in the front compressor stages and, in the case of turbines, depending on the turbine parameters, only the use in the rear turbine stages. An expansion of the area of application by increasing the operating temperature could be achieved through future developments.
  • the inventive activity lies in the application of polymer-based coating systems in the area of the compressor rotor blades 6, on the one hand to reduce or prevent “fretting” and “fretting fatigue” and, on the other hand, to prevent adhesion / cold welding over the entire service life and thus the following secondary damage to prevent during dismantling.
  • a long-term separating effect between the rotor blade 6 and the wheel disk groove 13 in the wing flank area 24 is made possible and the bearing behavior is improved.
  • FIG 2 a turbine blade 6 or compressor blade 6 is shown three-dimensionally. Since in particular, as described above, the wing area 24 is damaged, only this area is coated with a polymer 25.
  • the polymer coating 25 preferably extends over the entire axial length of the supporting flank region 24 and can also encompass the entire foot region 20, 23, 24, 26.
  • the polymer coating 25 for the blade root 7 or the groove area 13 can be fluoropolymer-based and also in particular contain one or more solid lubricants.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP15751016.5A 2015-08-19 2015-08-19 Gasturbinenschaufel oder verdichterschaufel mit anti-fretting-beschichtung im schaufelfussbereich und rotor Active EP3307989B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL15751016T PL3307989T3 (pl) 2015-08-19 2015-08-19 Łopatka turbiny gazowej albo łopatka sprężarki z powłoką anty-frettingową w obszarze podstawy łopatki i wirnik

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/EP2015/069013 WO2017028912A1 (de) 2015-08-19 2015-08-19 Gasturbinenschaufel oder verdichterschaufel mit anti-fretting-beschichtung im schaufelfussbereich und rotor

Publications (2)

Publication Number Publication Date
EP3307989A1 EP3307989A1 (de) 2018-04-18
EP3307989B1 true EP3307989B1 (de) 2020-09-30

Family

ID=53879518

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15751016.5A Active EP3307989B1 (de) 2015-08-19 2015-08-19 Gasturbinenschaufel oder verdichterschaufel mit anti-fretting-beschichtung im schaufelfussbereich und rotor

Country Status (6)

Country Link
US (1) US11352893B2 (pl)
EP (1) EP3307989B1 (pl)
KR (1) KR102045389B1 (pl)
CN (1) CN107923251B (pl)
PL (1) PL3307989T3 (pl)
WO (1) WO2017028912A1 (pl)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019200356A1 (en) * 2018-04-12 2019-10-17 Resource West, Inc. Impeller for ambient water evaporators, and related system and method
DE102020212752A1 (de) 2020-10-08 2022-04-14 MTU Aero Engines AG Verfahren zum Herstellen eines Rotors für eine Strömungsmaschine, Rotor für eine Strömungsmaschine und Strömungsmaschine mit einem Rotor

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3133158C1 (de) * 1981-08-21 1982-12-16 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Pressflaechen-Zwischenlage aus Metall und Verfahren zur Herstellung derselben
US4790723A (en) * 1987-01-12 1988-12-13 Westinghouse Electric Corp. Process for securing a turbine blade
US4820126A (en) * 1988-02-22 1989-04-11 Westinghouse Electric Corp. Turbomachine rotor assembly having reduced stress concentrations
US5087174A (en) 1990-01-22 1992-02-11 Westinghouse Electric Corp. Temperature activated expanding mineral shim
US5356545A (en) * 1991-01-15 1994-10-18 General Electric Company Curable dry film lubricant for titanium alloys
US5160243A (en) * 1991-01-15 1992-11-03 General Electric Company Turbine blade wear protection system with multilayer shim
US5179153A (en) * 1991-09-09 1993-01-12 E. I. Du Pont De Nemours And Company Wear resistant polyimide composition
US5573377A (en) * 1995-04-21 1996-11-12 General Electric Company Assembly of a composite blade root and a rotor
US6102664A (en) * 1995-12-14 2000-08-15 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Blading system and method for controlling structural vibrations
US6290466B1 (en) * 1999-09-17 2001-09-18 General Electric Company Composite blade root attachment
FR2918703B1 (fr) * 2007-07-13 2009-10-16 Snecma Sa Ensemble de rotor de turbomachine
GB2452515B (en) 2007-09-06 2009-08-05 Siemens Ag Seal coating between rotor blade and rotor disk slot in gas turbine engine
FR2934873B1 (fr) * 2008-08-06 2011-07-08 Snecma Dispositif amortisseur de vibrations pour attaches d'aubes.
GB0911459D0 (en) * 2009-07-02 2009-08-12 Rolls Royce Plc An assembly providing contaminant removal
US20110142678A1 (en) * 2010-11-23 2011-06-16 General Electric Company Erosion protection coating for rotor blade of wind turbine
GB201106278D0 (en) * 2011-04-14 2011-05-25 Rolls Royce Plc Annulus filler system
US10519788B2 (en) * 2013-05-29 2019-12-31 General Electric Company Composite airfoil metal patch

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
CN107923251B (zh) 2020-09-08
PL3307989T3 (pl) 2021-03-08
CN107923251A (zh) 2018-04-17
US11352893B2 (en) 2022-06-07
KR102045389B1 (ko) 2019-11-15
WO2017028912A1 (de) 2017-02-23
KR20180041172A (ko) 2018-04-23
US20180245475A1 (en) 2018-08-30
EP3307989A1 (de) 2018-04-18

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