DE102007031932A1 - A blade - Google Patents
A blade Download PDFInfo
- Publication number
- DE102007031932A1 DE102007031932A1 DE102007031932A DE102007031932A DE102007031932A1 DE 102007031932 A1 DE102007031932 A1 DE 102007031932A1 DE 102007031932 A DE102007031932 A DE 102007031932A DE 102007031932 A DE102007031932 A DE 102007031932A DE 102007031932 A1 DE102007031932 A1 DE 102007031932A1
- Authority
- DE
- Germany
- Prior art keywords
- wear protection
- flow inlet
- ductile
- airfoil
- inlet edge
- 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- Withdrawn
Links
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
-
- 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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/04—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings of inorganic non-metallic material
- C23C28/044—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings of inorganic non-metallic material coatings specially adapted for cutting tools or wear applications
-
- 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
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic 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
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
-
- 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
-
- 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
- F05D2300/226—Carbides
-
- 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
- F05D2300/226—Carbides
- F05D2300/2262—Carbides of titanium, e.g. TiC
-
- 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
Die Erfindung betrifft eine Turbomaschinenschaufel (10), insbesondere eine Gasturbinenschaufel, mit einem eine Strömungseintrittskante (13) und eine Strömungsaustrittskante (14) aufweisenden Schaufelblatt (11), wobei sich zwischen der Strömungseintrittskante und der Strömungsaustrittskante eine Saugseite und Druckseite des Schaufelblatts erstreckt. Erfindungsgemäß ist das Schaufelblatt (11) zumindest im Bereich der Strömungseintrittskante (13) mit einer duktilen Verschleißschutzschicht beschichtet, wobei die duktile Verschleißschutzschicht in einer Metallmatrix eingelagerte keramische Hartpartikel aufweist.The invention relates to a turbomachine blade (10), in particular a gas turbine blade, having a blade (11) having a flow inlet edge (13) and a flow outlet edge (14), wherein a suction side and pressure side of the blade extend between the flow inlet edge and the flow outlet edge. According to the invention, the blade (11) is coated with a ductile wear protection layer at least in the area of the flow inlet edge (13), the ductile wear protection layer having ceramic hard particles embedded in a metal matrix.
Description
Die Erfindung betrifft eine Turbomaschinenschaufel, insbesondere eine Gasturbinenschaufel.The The invention relates to a turbomachine blade, in particular a Gas turbine blade.
Turbomaschinenschaufeln, wie z. B. Gasturbinenschaufeln, verfügen über einen Schaufelfuß und ein Schaufelblatt, wobei das Schaufelblatt eine Strömungseintrittskante und eine Strömungsaustrittskante aufweist, und wobei sich zwischen der Strömungseintrittskante und der Strömungsaustrittskante des Schaufelblatts eines Saugseite und eine Druckseite desselben erstreckt.Turbomachinery blades, such as As gas turbine blades, have a blade root and a Airfoil, wherein the airfoil has a flow inlet edge and a Flow outlet edge and wherein between the flow inlet edge and the Flow outlet edge the airfoil of a suction side and a pressure side thereof extends.
Im Betrieb können Turbomaschinenschaufeln, nämlich sowohl statorseitige Leitschaufeln als auch rotorseitige Laufschaufeln, durch Erosion, Vogelschlag oder auch Hagelschlag beschädigt werden. Hierzu ist es aus der Praxis bereits bekannt, zumindest auf das Schaufelblatt einer Turbomaschinenschaufel ein hartes Verschleißschutzsystem aufzutragen, wobei derartige Verschleißschutzsysteme vorzugsweise als Multilayer-Schichtsysteme ausgebildet sind, die mindestens eine relativ harte, keramische Schicht und mindestens eine relative weiche, metallische Schicht aufweisen, die wechselweise auf das Schaufelblatt aufgebracht sind. Dann, wenn infolge von Erosion, Vogelschlag oder Hagelschlag Partikel mit einem Auftreffwinkel von in etwa 90° auf das Schaufelblatt einer Turbomaschinenschaufel auftreffen, wie dies im Bereich der Strömungseintrittskante einer Turbomaschinenschaufel üblich ist, können sich in einem solchen Verschleißschutzsystem Risse ausbilden, die letztendlich zu einem Abplatzen des Verschleißschutzsystems im Bereich der Strömungseintrittskante führen. Nach dem Abplatzen des Verschleißschutzsystems von der Strömungseintrittskante ist dieselbe ungeschützt einem Verschleiß ausgesetzt, wodurch dieselbe abgetragen werden kann, was letztendlich zur Verkürzung der sogenannten Sehnenlänge des Schaufelblatts und damit zu aerodynamischen Verlusten führt.in the Can operate Turbomachinery blades, namely both stator-side vanes and rotor-side rotor blades, be damaged by erosion, bird strike or hail. For this it is already known from practice, at least on the Blade of a turbomachinery blade a hard wear protection system apply, with such wear protection systems preferably are formed as multilayer layer systems, the at least one relatively hard, ceramic layer and at least one relatively soft, metallic Layer having alternately applied to the airfoil are. Then, when due to erosion, bird strike or hailstorm particles with an impact angle of about 90 ° on the blade of a Turbomachinery blade hit, as in the area of the flow inlet edge a turbomachinery blade usual is, can yourself in such a wear protection system Cracks form, which ultimately leads to a chipping of the wear protection system in the area of the flow inlet edge to lead. After flaking off the wear protection system from the flow inlet edge is the same unprotected exposed to wear, whereby it can be removed, which ultimately leads to the shortening of so-called chord length of the blade and thus leads to aerodynamic losses.
Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde eine neuartige Turbomaschinenschaufel, insbesondere eine neuartige Gasturbinenschaufel, zu schaffen. Dieses Problem wird durch eine Turbomaschinenschaufel gemäß Anspruch 1 gelöst. Erfindungsgemäß ist das Schaufelblatt zumindest im Bereich der Strömungseintrittskante mit einer duktilen Verschleißschutzschicht beschichtet, wobei die duktile Verschleißschutzschicht in einer Metallmatrix eingelagerte keramische Hartpartikel aufweist.Of these, Based on the present invention, the problem is based a novel turbomachine blade, in particular a novel Gas turbine blade to create. This problem is caused by a Turbomachine blade according to claim 1 solved. According to the invention, the blade is at least in the region of the flow inlet edge with a ductile wear protection layer coated, wherein the ductile wear protection layer in a metal matrix having embedded ceramic hard particles.
Die Erfindung schlägt vor, das Schaufelblatt einer Turbomaschine zumindest im Bereich der Strömungseintrittskante mit einer duktilen, nicht rein keramischen sowie nicht rein metallischen Verschleißschutzschicht zu beschichten, wobei die duktile Verschleißschutzschicht in einer Metallmatrix eingelagerte keramische Hartpartikel umfasst. Eine solche duktile Verschleißschutzschicht neigt bei einem Auftreffwinkel von Partikeln um in etwa 90° nicht zur Rissbildung und damit nicht zum Abplatzen. Auf diese Art und Weise kann die Strömungseintrittskante einer Turbomaschine effektiv vor einem Verschleiß durch Erosion, Vogelschlag oder auch Hagelschlag geschützt werden.The Invention proposes before, the blade of a turbomachine at least in the area the flow inlet edge with a ductile, not purely ceramic and not purely metallic Wear protection layer to coat, wherein the ductile wear protection layer in a metal matrix embedded ceramic hard particles. Such a ductile Wear protection layer does not tend to crack at an angle of incidence of particles about 90 ° and so not to flake off. In this way, the Flow inlet edge of a Turbomachine effectively against erosion, bird strike or hailstorm protected become.
Der Begriff der "Turbomaschinenschaufel" ist im Sinne der vorliegenden Erfindung weitgefasst zu verstehen und bezieht sich insbesondere auf Turbomaschinenschaufeln im engen oder eigentlichen Sinne bzw. auf Strömungsprofile, wie z. B. Turbinenschaufeln, Verdichterschaufeln, Rotorblätter, Turboprop-Propeller, Hubschrauberflügel und der gleichen.Of the Concept of "Turbomachinery bucket" is in the sense of The present invention broadly understand and relates in particular on turbomachinery blades in narrow or actual Senses or flow profiles, such as Turbine blades, compressor blades, rotor blades, turboprop propellers, helicopter wing and the same.
Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung. Ausführungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigt:preferred Further developments of the invention will become apparent from the dependent claims and the following description. Embodiments of the invention without being limited to this to be closer to the drawing explained. Showing:
Die
Turbomaschinenschaufel
Erfindungsgemäß ist das
Schaufelblatt
Vorzugsweise weist die duktile Verschleißschutzschicht in einer Metallmatrix eingelagerte Carbidpartikel auf, insbesondere Carbidpartikel aus Titancarbid oder dergleichen.Preferably has the ductile wear protection layer in a metal matrix embedded carbide particles, in particular Carbide particles of titanium carbide or the like.
Die
zumindest im Bereich der Strömungseintrittskante
Da
eine solche duktile Verschleißschutzschicht
jedoch bei Auftreffwinkeln von weniger als 90° schnell abgetragen werden kann,
ist das Schaufelblatt
Nach
einer ersten Alternative ist das Schaufelblatt
Nach
einer zweiten Alternative der Erfindung ist das Schaufelblatt
Es
ist jedoch auch möglich,
dass größere Bereiche
des Schaufelblatts
Nach
einer dritten Alternative ist es möglich, dass das Schaufelblatt
Mit
der hier vorliegenden Erfindung ist es möglich, sämtliche Bereiche eines Schaufelblatts
Claims (7)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102007031932A DE102007031932A1 (en) | 2007-07-09 | 2007-07-09 | A blade |
PCT/DE2008/001042 WO2009006871A2 (en) | 2007-07-09 | 2008-06-21 | Turbomachine blade with weaar-resistant layer |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102007031932A DE102007031932A1 (en) | 2007-07-09 | 2007-07-09 | A blade |
Publications (1)
Publication Number | Publication Date |
---|---|
DE102007031932A1 true DE102007031932A1 (en) | 2009-01-15 |
Family
ID=40121341
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE102007031932A Withdrawn DE102007031932A1 (en) | 2007-07-09 | 2007-07-09 | A blade |
Country Status (2)
Country | Link |
---|---|
DE (1) | DE102007031932A1 (en) |
WO (1) | WO2009006871A2 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102008056741A1 (en) * | 2008-11-11 | 2010-05-12 | Mtu Aero Engines Gmbh | Wear protection layer for Tial |
WO2010051803A1 (en) * | 2008-11-10 | 2010-05-14 | Mtu Aero Engines Gmbh | Anti-erosion layer for aerodynamic components and structures and method for the production thereof |
DE102012200491A1 (en) * | 2012-01-13 | 2013-07-18 | Lufthansa Technik Ag | Gas turbine blade for an aircraft engine and method of coating a gas turbine blade |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9587645B2 (en) | 2010-09-30 | 2017-03-07 | Pratt & Whitney Canada Corp. | Airfoil blade |
US8871297B2 (en) | 2010-09-30 | 2014-10-28 | Barry Barnett | Method of applying a nanocrystalline coating to a gas turbine engine component |
US9429029B2 (en) | 2010-09-30 | 2016-08-30 | Pratt & Whitney Canada Corp. | Gas turbine blade and method of protecting same |
US9427835B2 (en) | 2012-02-29 | 2016-08-30 | Pratt & Whitney Canada Corp. | Nano-metal coated vane component for gas turbine engines and method of manufacturing same |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4904542A (en) * | 1988-10-11 | 1990-02-27 | Midwest Research Technologies, Inc. | Multi-layer wear resistant coatings |
EP0589072A1 (en) * | 1992-09-21 | 1994-03-30 | Asea Brown Boveri Ag | Turbocharger for heavy fuel operation |
US5486096A (en) * | 1994-06-30 | 1996-01-23 | United Technologies Corporation | Erosion resistant surface protection |
DE4439950C2 (en) * | 1994-11-09 | 2001-03-01 | Mtu Muenchen Gmbh | Metallic component with a composite coating, use, and method for producing metallic components |
US6095755A (en) * | 1996-11-26 | 2000-08-01 | United Technologies Corporation | Gas turbine engine airfoils having increased fatigue strength |
GB2319783B (en) * | 1996-11-30 | 2001-08-29 | Chromalloy Uk Ltd | A thermal barrier coating for a superalloy article and a method of application thereof |
EP1541810A1 (en) * | 2003-12-11 | 2005-06-15 | Siemens Aktiengesellschaft | Use of a thermal barrier coating for a part of a steam turbine and a steam turbine |
FR2884550B1 (en) * | 2005-04-15 | 2010-09-17 | Snecma Moteurs | PIECE FOR PROTECTING THE EDGE OF A BLADE |
US20070099027A1 (en) * | 2005-10-28 | 2007-05-03 | Anand Krishnamurthy | Wear resistant coatings |
EP2129812B1 (en) * | 2007-03-27 | 2013-04-17 | Alstom Technology Ltd | Turbomachine blade with erosion and corrosion protective coating and method of manufacturing the same |
-
2007
- 2007-07-09 DE DE102007031932A patent/DE102007031932A1/en not_active Withdrawn
-
2008
- 2008-06-21 WO PCT/DE2008/001042 patent/WO2009006871A2/en active Application Filing
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2010051803A1 (en) * | 2008-11-10 | 2010-05-14 | Mtu Aero Engines Gmbh | Anti-erosion layer for aerodynamic components and structures and method for the production thereof |
DE102008056741A1 (en) * | 2008-11-11 | 2010-05-12 | Mtu Aero Engines Gmbh | Wear protection layer for Tial |
DE102012200491A1 (en) * | 2012-01-13 | 2013-07-18 | Lufthansa Technik Ag | Gas turbine blade for an aircraft engine and method of coating a gas turbine blade |
DE102012200491B4 (en) * | 2012-01-13 | 2015-05-28 | Lufthansa Technik Ag | Gas turbine blade for an aircraft engine and method of coating a gas turbine blade |
US9624781B2 (en) | 2012-01-13 | 2017-04-18 | Lufthansa Technik Ag | Gas turbine blade for an aircraft engine and method for coating a gas turbine blade |
Also Published As
Publication number | Publication date |
---|---|
WO2009006871A2 (en) | 2009-01-15 |
WO2009006871A3 (en) | 2009-03-26 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
8139 | Disposal/non-payment of the annual fee | ||
R119 | Application deemed withdrawn, or ip right lapsed, due to non-payment of renewal fee |
Effective date: 20110201 |