EP2087149A2 - Aube pour compresseur ou turbine d'un turboréacteur, turboréacteur présentant une telle aube, et procédé de recouvrement d'une aube de turboréacteur - Google Patents

Aube pour compresseur ou turbine d'un turboréacteur, turboréacteur présentant une telle aube, et procédé de recouvrement d'une aube de turboréacteur

Info

Publication number
EP2087149A2
EP2087149A2 EP07846269A EP07846269A EP2087149A2 EP 2087149 A2 EP2087149 A2 EP 2087149A2 EP 07846269 A EP07846269 A EP 07846269A EP 07846269 A EP07846269 A EP 07846269A EP 2087149 A2 EP2087149 A2 EP 2087149A2
Authority
EP
European Patent Office
Prior art keywords
blade
boundary line
protective layer
aircraft engine
maximum
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Withdrawn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
EP07846269A
Other languages
German (de)
English (en)
Inventor
Thomas Uihlein
Wolfgang Eichmann
Falko Heutling
Markus Uecker
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP2087149A2 publication Critical patent/EP2087149A2/fr
Withdrawn legal-status Critical Current

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
    • 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
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • 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

Definitions

  • the invention relates to an aircraft engine with a compressor and at least one turbine, a blade for a compressor or a turbine of an aircraft engine and a method for coating a blade of an aircraft engine.
  • Layers of any kind often exert a negative influence on the fatigue strength and / or the service life of components. This is especially true for hard coatings against wear or corrosion, with the risk that cracks in the ceramic layers run quickly into the base material and lead to premature failure of the component.
  • Fig. Ia shows, in which a blade 101 with an airfoil 110, a blade root 112th , a platform 114 and an erosion control coating 116 is shown schematically.
  • a blade 101 with an airfoil 110, a blade root 112th , a platform 114 and an erosion control coating 116 is shown schematically.
  • the coating can be completely dispensed with and increased erosion or increased wear can be accepted.
  • the invention has for its object to provide compressor or turbine blades of aircraft engines with high corrosion and erosion resistance and good fatigue strength.
  • an aircraft engine with at least one compressor and at least one turbine is proposed.
  • the compressor as well as the turbine each have blades, namely compressor blades or turbine blades.
  • the blades each form an airfoil, which - as is usually the case with compressor blades or turbine blades - has a suction side and a pressure side.
  • At least a first of these airfoils is coated for the reduction of erosion or wear with a protective layer which is applied on at least one side of this first airfoil, ie on the pressure side and / or on the suction side, such that at least two, at a boundary line to each other forming abutting regions, of which a first region is provided with the protective layer such that the protective layer has a substantially constant first thickness in this first region, and of which a second region, in particular on the same side as the first region is free of the protective layer or is provided with the protective layer such that this protective layer in this second region has a substantially constant, deviating from the first thickness second thickness.
  • the boundary line separating the first area from the second area is designed such that at least two points of this boundary line exist, whose connecting line deviates from the boundary line course between these two points or non-coincident with the boundary line course between them is two points.
  • the first airfoil may be an airfoil of a turbine blade or an airfoil of a compressor blade.
  • at least one turbine blade and at least one compressor blade is a first blade or designed in accordance with the invention.
  • the first blade is designed according to the invention on its suction side and / or on its pressure side.
  • the blades of several, preferably all, turbine and / or compressor blades are configured as first blades or in erfmdungs- according manner.
  • the respective first and / or second region may be an area that extends to the outer edge of the airfoil, or an area that is essentially closed in itself.
  • the blade may in particular be a compressor blade or a turbine blade of an engine.
  • the blade may be configured to form a platform from which the airfoil protrudes.
  • the blade has in particular a blade root.
  • the invention may, for example, also refer to blisks or the like.
  • the blades or the blades formed in accordance with the invention are designed in one piece, and in particular have a blade root and an airfoil.
  • the blade is advantageously made of the same material, apart from the coating.
  • the blade may in particular be integrally formed, that is to say in particular such that an airfoil and a blade root (and possibly platform) are formed or produced from one part.
  • the blade at least on one side, namely suction side and / or pressure side, exactly two areas of the type mentioned, and thus exactly a borderline. It can also be provided that a plurality of regions of the aforementioned type and accordingly a plurality of boundary lines are provided on the suction side and / or pressure side.
  • the boundary line has curved sections. It can be provided that the boundary line is parabolic-shaped.
  • the blade may, for example, have a blade root, wherein the boundary line is designed parabolic in such a way that it is open in the direction of this blade root.
  • the position of the boundary line in dependence (in operation in an aircraft engine, in particular presumably, given) maximum Schwingungs endureeii (in the airfoil) and / or depending on (in operation in an aircraft engine, in particular, given ) Erosionsbelastept of the airfoil is selected, which are given at the leading and trailing edges of the blade or from the wide area extending on the suction side or pressure side or expected.
  • This can in particular be such that the areas addressed are selected such that the points at which the voltage maxima are given are in an area or respectively in a region in which no protective layer is provided, or a protective layer with a smaller thickness than elsewhere on the same side of the airfoil.
  • permanent voltages, dynamic voltages and residual stresses can be taken into account.
  • the anticipated stresses and / or erosion stresses mentioned can be determined, for example, by means of simulation and / or empirical values or in another suitable manner.
  • L total lattice length or axial position of the trailing edge in the middle of the duct with reference to the leading edge in the center of the duct
  • L 3 Axial position of the location of the maximum 1F vibration stress on the suction side relative to the leading edge.
  • two regions are provided on the pressure side which differ in the thickness of their protective layer or in that one protective layer is provided in one of these regions and in the other of these two regions no protective layer is given, for which these two areas are separated by a borderline:
  • the 1F oscillation voltage is in particular the oscillation voltage of the first bending oscillation.
  • the channel center is in particular substantially the middle between the surface of the platform facing the blade leaf and the housing located radially outside thereof in the radial direction; the channel center of a plurality of blades held in an aircraft engine on the same rotor or disc defines for the arrangement of these substantially a hollow cylindrical shape.
  • the borderline may also be related to allowable repair areas for apertures or patches. In addition, this may mean that no stripping is necessary in the course of repair work, if the erosion-prone areas coincide with the permissible repair areas and these are mechanically removed anyway with the used layers. Ie. The recoating is then possible without previous stripping.
  • the layer is preferably a multilayer layer.
  • voltages in particular voltage maxima
  • the determination of the voltages or voltage maxima can, for example, be based on empirical values or on the basis of calculations or empirically or in another way.
  • an erosion load is determined which the bucket is likely to be exposed to during operation. This can be done, for example, based on empirical values.
  • areas of the blade of the blade are determined which are not to be coated or compared to other areas of the blade with a reduced layer thickness, these determinations being carried out depending on the determined voltages or the erosion load.
  • the blade or the blade is coated, taking into account the determination of the areas of the blade of the blade, which are not coated or with reduced layer thickness.
  • the method according to the invention can be carried out with respect to the pressure side of an airfoil and / or with respect to the suction side of an airfoil.
  • z. B. multilayer coatings with little effect on the fatigue strength are used and / or the layers only in the transition region from the platform to the airfoil, where there is little erosion attack and / or in areas where voltage maxima of the vibration are omitted.
  • the voltage maxima can be determined.
  • an overlay with an erosion image on a simulation program for particle erosion such as CFX5 of the company ANSYS done.
  • areas can be determined which should not be coated or less. It can also be provided that subsequently these areas are shaded, which can be done for example by known to those skilled devices or procedures.
  • particle simulation programs empirically determined (simulation) images of already known components can be used.
  • the stripping step before recoating is dispensed with if permissible repair areas coincide with optimized coating areas and the area of the erosion attack.
  • Fig. Ia a known design
  • FIG. 1 b shows an exemplary design according to the invention in a schematic view
  • FIG. 2 shows a blade in a schematic view with schematically and exemplarily added zones of different levels of erosion stress
  • Fig. 3 shows an exemplary inventive blade from its suction side.
  • FIG. 1 a shows a modified design of a blade 1 of an aircraft engine, wherein the design already mentioned in the introduction according to FIG. 1 a has a conventional coating surface and the design according to FIG. 1 b is an exemplary design according to the invention.
  • the blade 1 has an airfoil 10, a blade root 12 partially shown in this figure, and a platform 14.
  • the platform 14 separates the airfoil 10 from the blade root 12.
  • the airfoil 10 has a coating 16 on its pressure side and / or on its suction side.
  • the airfoil 10 has a coating 16 on its suction side and / or pressure side. At least a first region 18 and a second region 20 are formed on the addressed suction side and / or pressure side of this airfoil 10, with this first region and this second region abutting one another at a boundary line 22.
  • the first region 18 the already mentioned coating or protective layer 16 is provided, and the second region 20 is free of such a protective layer.
  • the first region 18 and the second region 20 each have a protective layer, wherein these two protective layers or regions 18, 20 differ by the thickness of their protective layer. This may in particular be such that in the first region 18 the protective layer or coating is thicker than in the second region 20.
  • the boundary line 22 according to FIG. 1b In contrast to the design according to FIG. 1 a, in which the local boundary line 122 between the first 118 and second region 120 lies completely on a straight line, at the boundary line 22 according to FIG. 1b at least two points of this boundary line 22, whose connecting distance from deviates from the boundary line between the two points.
  • the boundary line 22 according to FIG. 1b is not located completely on a straight line.
  • the boundary line 22 according to FIG. 1b is curved here, in particular parabolic, designed. As clearly shown in FIG. 1b, the curvature is concave there or the parabolic shape in the direction of the blade root 12 or the platform 14 is open.
  • the parabolic shape here can have a profile according to the formula 1 or according to the formula 2.
  • the erosion attack in the design according to FIG. 1 b is reduced, in particular due to the formation of the protective layer or coating surface there.
  • FIG. 2 schematically shows a blade as well as an exemplary erosion load over the blade length or blade height.
  • This erosion stress can be determined, for example, from a particle simulation program or empirical experience or the like.
  • the exemplary erosion load shown in FIG. 2 is such that the airfoil 10 is subjected to little to no erosion stress in an area 80 located near the bucket 12, and, if necessary, stepped with increasing distance from the blade root 12 - Is exposed to an increasing erosion load, which can be roughly divided into a region 82 with average erosion load and a region 84 with high to very high erosion load.
  • Fig. 3 shows schematically an exemplary inventive airfoil 10, in view of the suction side.
  • Shown schematically on the blade 10 in FIG. 3 is a tension profile which can presumably occur during operation of the blade or of the blade 10 in a compressor or a turbine of an aircraft engine.
  • the stress profile can be determined, for example, empirically or from empirical values, or can be calculated or determined in another suitable manner.
  • the reference numeral 24 indicates the maximum 1F oscillation voltage at the leading edge.
  • the reference numeral 26 indicates the maximum 1F oscillation voltage at the trailing edge and the reference numeral 28 indicates the maximum 1F oscillation voltage on the suction side.
  • a coating 16 is provided in the radially outer region or in the first region 18.
  • the second region 20 is uncoated or slightly coated or provided with a thinner coating than the first region 18.
  • the first region 18 is separated from the second region 20 by a boundary line 22 or abut the regions 18 and 20 at this boundary line 22, wherein the boundary line 22 having the parameters indicated in the legend in Fig. 3 has a course which is formed according to the formula 1 given above.
  • the zero point of the graph or of the corresponding coordinate system may lie at the point indicated by IDLE in FIG. 3 or at the point mentioned above.
  • blades can be loaded by bending and torsional modes under stresses such as pumps or flutter with the highest intensities.
  • the maxima of these modes are often located in the lower half of the sheet. In these areas, no layer boundary should run or it is expedient if there is no layer boundary in these areas, or at least the layer thickness is reduced or it is expedient if the layer thickness is at least reduced.
  • a boundary line in particular a parabola or a parabola
  • a boundary line which distinguishes areas which can be coated without and with restriction, as is the case, for example, in an advantageous embodiment of the invention.
  • hl Measured height over hub cut (see picture) of the location of the maximum IF swing voltage at the leading edge
  • h2 Gem. height above hub intersection of the location of the maximum 1F vibration stress at the trailing edge
  • h3 Gem. Height above hub section of the location of the maximum 1 F swing voltage on the suction side

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un turboréacteur présentant un compresseur et au moins une turbine, ledit compresseur et ladite turbine présentant, respectivement, des aubes (1) munies chacune d'une pale (10) formant un côté aspiration et un côté compression, au moins une première (10) de ces pales (10) étant recouverte, en vue de réduire l'érosion ou l'usure, d'une couche protectrice (16) qui est appliquée sur au moins un côté de la pale (10), de façon qu'il se forme au moins deux zones (18, 20) se rencontrant mutuellement en une ligne de délimitation (22), une première zone (18) étant munie de la couche protectrice (16), de telle façon que la couche protectrice (16) présente, dans cette première zone (18), une première épaisseur sensiblement constante, et une seconde zone (20) étant exempte de la couche protectrice (16) ou étant munie de la couche protectrice (16), de façon que la couche protectrice (16) dans cette seconde zone (20) présente une seconde épaisseur, sensiblement constante, se différenciant de la première épaisseur. L'invention est caractérisée en ce qu'il existe au moins deux points de ladite ligne de délimitation (22), dont le parcours de jonction se différencie de la trajectoire de la ligne de délimitation entre ces deux points.
EP07846269A 2006-11-03 2007-10-27 Aube pour compresseur ou turbine d'un turboréacteur, turboréacteur présentant une telle aube, et procédé de recouvrement d'une aube de turboréacteur Withdrawn EP2087149A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006051813A DE102006051813A1 (de) 2006-11-03 2006-11-03 Schaufel für einen Verdichter oder eine Turbine eines Flugtriebwerks, Flugtriebwerk mit einer solchen Schaufel sowie Verfahren zum Beschichten einer Schaufel eines Flugtriebwerks
PCT/DE2007/001933 WO2008055471A2 (fr) 2006-11-03 2007-10-27 Aube pour compresseur ou turbine d'un turboréacteur, turboréacteur présentant une telle aube, et procédé de recouvrement d'une aube de turboréacteur

Publications (1)

Publication Number Publication Date
EP2087149A2 true EP2087149A2 (fr) 2009-08-12

Family

ID=38931330

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07846269A Withdrawn EP2087149A2 (fr) 2006-11-03 2007-10-27 Aube pour compresseur ou turbine d'un turboréacteur, turboréacteur présentant une telle aube, et procédé de recouvrement d'une aube de turboréacteur

Country Status (5)

Country Link
US (1) US20100143110A1 (fr)
EP (1) EP2087149A2 (fr)
CA (1) CA2668298A1 (fr)
DE (1) DE102006051813A1 (fr)
WO (1) WO2008055471A2 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10174626B2 (en) * 2014-10-15 2019-01-08 Pratt & Whitney Canada Corp. Partially coated blade
DE102016215158A1 (de) * 2016-08-15 2018-02-15 Siemens Aktiengesellschaft Korrosions- und erosionsbeständiges Schutzschichtsystem und Verdichterschaufel
CN108388701B (zh) * 2018-01-30 2021-09-03 南京理工大学 一种无间隙双层金属机匣的弹道极限计算方法
DE102020210003A1 (de) 2020-08-06 2022-02-10 MTU Aero Engines AG Verfahren zum Reparieren eines integral beschaufelten Rotors

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA1217433A (fr) * 1983-08-29 1987-02-03 Westinghouse Electric Corporation Aube a revetement gradue pour turbine a combustion
US5490764A (en) * 1994-05-23 1996-02-13 General Electric Company Unshrouded blading for high bypass turbofan engines
US6129991A (en) * 1994-10-28 2000-10-10 Howmet Research Corporation Aluminide/MCrAlY coating system for superalloys
US6095755A (en) * 1996-11-26 2000-08-01 United Technologies Corporation Gas turbine engine airfoils having increased fatigue strength
US6048174A (en) * 1997-09-10 2000-04-11 United Technologies Corporation Impact resistant hollow airfoils
GB2346415A (en) * 1999-02-05 2000-08-09 Rolls Royce Plc Vibration damping
DE60231084D1 (de) * 2002-12-06 2009-03-19 Alstom Technology Ltd Verfahren zur selektiven Abscheidung einer MCrAlY-Beschichtung
DE102004001392A1 (de) * 2004-01-09 2005-08-04 Mtu Aero Engines Gmbh Verschleißschutzbeschichtung und Bauteil mit einer Verschleißschutzbeschichtung
EP1843265A1 (fr) * 2006-04-07 2007-10-10 Ansaldo Energia S.P.A. Procédé de détermination des surfaces d'érosion d'une machine à turbine

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
None *
See also references of WO2008055471A2 *

Also Published As

Publication number Publication date
DE102006051813A1 (de) 2008-05-08
WO2008055471A3 (fr) 2009-06-11
WO2008055471A2 (fr) 2008-05-15
CA2668298A1 (fr) 2008-05-15
US20100143110A1 (en) 2010-06-10

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