EP1468170A1 - Verfahren zur frequenzveränderung von schaufeln für thermische strömungsmaschinen - Google Patents
Verfahren zur frequenzveränderung von schaufeln für thermische strömungsmaschinenInfo
- Publication number
- EP1468170A1 EP1468170A1 EP03700009A EP03700009A EP1468170A1 EP 1468170 A1 EP1468170 A1 EP 1468170A1 EP 03700009 A EP03700009 A EP 03700009A EP 03700009 A EP03700009 A EP 03700009A EP 1468170 A1 EP1468170 A1 EP 1468170A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- blades
- frequency
- changing
- 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.)
- Granted
Links
Classifications
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
-
- 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
- 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
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
- F05D2230/311—Layer deposition by torch or flame spraying
-
- 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
- F05D2230/90—Coating; Surface treatment
Definitions
- the invention relates to the field of thermal flow machines. It relates to a method for changing the frequency of blades, in particular turbine blades, which are already largely ready for use in the turbomachine.
- the performance of a gas turbine is essentially determined by the mass flows processed, such as fuel and air.
- the quality of the blading has an impact on the level of efficiency of a gas turbine.
- the blade dimensions e.g. B. the chord length, the blade height, the curvature, the profile, the twist and the Blade spacing determines the most suitable flow data of a stage for the turbine, e.g. inflow and outflow angle, pressure ratio, gas velocity and quantity.
- the aim of the invention is to avoid the disadvantages of the prior art mentioned.
- the invention is based on the object of developing a method for changing the frequency of blades, in particular turbine blades, which can be used quickly and easily in blades which are already ready for use. Because of the high aerodynamic sensitivity of the blades, the changes in the airfoil profile should only be very small.
- this object is achieved in a method according to the preamble of claim 1 in that a metallic coating made of a material identical to the base material is applied in the area of the blade tip to the already ready-to-use blade, the thickness of the coating being at the trailing edge and in a radial direction Continuously tapered towards the blade root.
- the advantages of the invention consist in the fact that with the method according to the invention it is possible, very quickly in the case of turbine blades, what differences between the theoretical frequency calculation during the design phase and the actual difference measured frequency to change the frequency. This can prevent the components from failing during machine operation due to resonance excitation.
- the metallic coating is applied to the airfoil by means of a flame spraying process.
- the flame spraying process can be used relatively universally. Material thicknesses can be realized in relatively wide areas.
- Fig. 1 is a side view of a gas turbine blade
- FIG. 2 shows a section along the line II-II in FIG. 1.
- FIGS. 1 and 2 The invention is explained in more detail below using an exemplary embodiment and FIGS. 1 and 2.
- Fig. 1 shows a side view of a blade 1 of a gas turbine.
- the guide vane 1 consists of an airfoil 2, a blade root 3 and a platform 4 arranged between them, from which the airfoil 2 extends integrally.
- the blade root 3 is used for attachment the turbine blade 1 in a turbine rotor, not shown.
- the airfoil 2 has a pressure side 5 and a suction side 6 (not visible in FIG. 1), which adjoin one another at an outlet edge 7, and a blade tip 9.
- Fig. 1 the view of the pressure side 5 of the airfoil 2 is shown.
- FIG. 2 shows a section along the plane II-II of FIG. 1.
- the inner contour of the blade 1, which has an internal cooling system is not shown in FIG. 2.
- the ready-to-use blade 2 is provided with a metallic one prior to installation on the blade tip 9 Cover 8 provided.
- the coating (8) consists of a material identical to the base material.
- the metal is preferably applied to the airfoil 2 by means of a flame spray process known per se. It is important that the thickness of the metallic coating 8 tapers continuously at the trailing edge 7 and in the radial direction towards the blade root 3.
- the method according to the invention is inexpensive and can be implemented in a very short time.
- the flame spraying method is particularly well suited, since it creates "soft" continuous transitions in the application thickness and the material 8 to be applied can be placed at the right places in a precisely limited manner without rework being necessary.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
Description
Claims
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH1042002 | 2002-01-22 | ||
CH00104/02A CH695461A5 (de) | 2002-01-22 | 2002-01-22 | Verfahren zur Frequenzveränderung von Schaufeln für thermische Strömungsmaschinen. |
PCT/CH2003/000022 WO2003062606A1 (de) | 2002-01-22 | 2003-01-16 | Verfahren zur frequenzveränderung von schaufeln für thermische strömungsmaschinen |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1468170A1 true EP1468170A1 (de) | 2004-10-20 |
EP1468170B1 EP1468170B1 (de) | 2010-12-15 |
Family
ID=27587778
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP03700009A Expired - Fee Related EP1468170B1 (de) | 2002-01-22 | 2003-01-16 | Verfahren zur frequenzveränderung von schaufeln für thermische strömungsmaschinen |
Country Status (5)
Country | Link |
---|---|
US (1) | US20050042384A1 (de) |
EP (1) | EP1468170B1 (de) |
CH (1) | CH695461A5 (de) |
DE (1) | DE50313322D1 (de) |
WO (1) | WO2003062606A1 (de) |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB0601837D0 (en) * | 2006-01-31 | 2006-03-08 | Rolls Royce Plc | An aerofoil assembly and a method of manufacturing an aerofoil assembly |
EP1985803A1 (de) | 2007-04-23 | 2008-10-29 | Siemens Aktiengesellschaft | Verfahren zum Herstellen von beschichteten Turbinenlaufschaufeln |
GB2450937B (en) * | 2007-07-13 | 2009-06-03 | Rolls Royce Plc | Component with tuned frequency response |
US20100028133A1 (en) * | 2008-07-30 | 2010-02-04 | General Electric Company | Turbomachine component damping structure and method of damping vibration of a turbomachine component |
DE102009033618A1 (de) | 2009-07-17 | 2011-01-20 | Mtu Aero Engines Gmbh | Verfahren zur Frequenzverstimmung eines Rotorkörpers einer Gasturbine und ein Rotor einer Gasturbine |
DE102009053247A1 (de) * | 2009-11-13 | 2011-05-19 | Mtu Aero Engines Gmbh | Verfahren zum Verändern einer Eigenfrequenz einer Schaufel für eine Strömungsmaschine |
EP2617945B1 (de) | 2012-01-23 | 2018-03-14 | MTU Aero Engines GmbH | Rotor für eine Strömungsmaschine sowie Verfahren zu dessen Herstellung |
US9145775B2 (en) * | 2012-03-02 | 2015-09-29 | United Technologies Corporation | Tapered thermal coating for airfoil |
US11002293B2 (en) | 2017-09-15 | 2021-05-11 | Pratt & Whitney Canada Corp. | Mistuned compressor rotor with hub scoops |
US10443411B2 (en) | 2017-09-18 | 2019-10-15 | 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 |
DE102022200711A1 (de) | 2022-01-24 | 2023-07-27 | Siemens Energy Global GmbH & Co. KG | Teilweise beschichtete Turbinenschaufel, Rotor und Verfahren |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3357850A (en) * | 1963-05-09 | 1967-12-12 | Gen Electric | Vibration damping turbomachinery blade |
US3758233A (en) * | 1972-01-17 | 1973-09-11 | Gen Motors Corp | Vibration damping coatings |
DE2558709C3 (de) * | 1975-12-24 | 1982-02-11 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Elastomere Dämpfungseinrichtung |
US4118147A (en) * | 1976-12-22 | 1978-10-03 | General Electric Company | Composite reinforcement of metallic airfoils |
CH630289A5 (de) * | 1977-05-09 | 1982-06-15 | Bbc Brown Boveri & Cie | Hochdaempfender verbundwerkstoff. |
DE4310896C1 (de) * | 1993-04-02 | 1994-03-24 | Thyssen Industrie | Verfahren zum Herstellen von verschleißfesten Kanten an Turbinenschaufeln |
US6213721B1 (en) * | 1993-11-09 | 2001-04-10 | Thomson Marconi Sonar Limited | Noise emission reduction |
US6059533A (en) * | 1997-07-17 | 2000-05-09 | Alliedsignal Inc. | Damped blade having a single coating of vibration-damping material |
GB2346415A (en) | 1999-02-05 | 2000-08-09 | Rolls Royce Plc | Vibration damping |
US6155789A (en) * | 1999-04-06 | 2000-12-05 | General Electric Company | Gas turbine engine airfoil damper and method for production |
-
2002
- 2002-01-22 CH CH00104/02A patent/CH695461A5/de not_active IP Right Cessation
-
2003
- 2003-01-16 DE DE50313322T patent/DE50313322D1/de not_active Expired - Lifetime
- 2003-01-16 EP EP03700009A patent/EP1468170B1/de not_active Expired - Fee Related
- 2003-01-16 WO PCT/CH2003/000022 patent/WO2003062606A1/de not_active Application Discontinuation
-
2004
- 2004-07-16 US US10/892,278 patent/US20050042384A1/en not_active Abandoned
Non-Patent Citations (1)
Title |
---|
See references of WO03062606A1 * |
Also Published As
Publication number | Publication date |
---|---|
EP1468170B1 (de) | 2010-12-15 |
US20050042384A1 (en) | 2005-02-24 |
CH695461A5 (de) | 2006-05-31 |
DE50313322D1 (de) | 2011-01-27 |
WO2003062606A1 (de) | 2003-07-31 |
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