EP0484115A1 - Extrémité abrasive pour aube de turbine - Google Patents

Extrémité abrasive pour aube de turbine Download PDF

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Publication number
EP0484115A1
EP0484115A1 EP91309998A EP91309998A EP0484115A1 EP 0484115 A1 EP0484115 A1 EP 0484115A1 EP 91309998 A EP91309998 A EP 91309998A EP 91309998 A EP91309998 A EP 91309998A EP 0484115 A1 EP0484115 A1 EP 0484115A1
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EP
European Patent Office
Prior art keywords
abrasive particles
metal
particles
layer
abrasive
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Withdrawn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
EP91309998A
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German (de)
English (en)
Inventor
Roger Johnson Perkins
Robert Victor Hillery
Howard John Farr
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General Electric Co
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General Electric Co
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Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP0484115A1 publication Critical patent/EP0484115A1/fr
Withdrawn legal-status Critical Current

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    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D15/00—Electrolytic or electrophoretic production of coatings containing embedded materials, e.g. particles, whiskers, wires

Definitions

  • rubbing Contact of the blade tip with the shroud or stator life is frequently referred to as rubbing, and occurs most frequently during early engine life. These rubs are attributed primarily to transient thermal and mechanical strains occurring during rapid changes in thrust level due to fast heat-ups, fast cooldowns also referred to as reburst cycles and in reheats.
  • Thermal expansion results because the rotor has less cooling than the shroud. During rapid increases in thrust levels, at which time additional combustion is occurring, the rotor thermally expands faster than the shroud. Thus, a component of the overall expansion is attributed to the thermal expansion of the rotor in excess of the stator or shroud.
  • abrasive material is not a structural material, and because its weight imposes stresses on the blade substrate as the blade rotates at high speeds, it is desirable to maintain the abrasive layer to the minimum possible thickness while retaining abrasive capability.
  • structures such as described in Stalker et al., U.S. Pat. No. 4,232,995 and Eaton et al., U.S. Pat. No. 4,744,725, containing a single layer of abrasive particles embedded in a matrix are preferred to multi-layered tips such as described in Moyer, U.S. Pat. No. 3,199,836.
  • U.S. pat. No. 4,689,242 to Pike discloses another method of applying metal-coated ceramic particles to a metallic substrate. This method requires the deposition of a multiple layer coating on each particle, the layers comprising a first oxide layer and a second metal layer capable of diffusing into the article surface.
  • the substrate is coated with a binder solution consisting essentially of a low viscosity carrier liquid, a thermoplastic resin and metal particulates substantially smaller than the ceramic particles.
  • a single layer of the ceramic particles are then disposed on the coated substrate.
  • the article is then heated to diffuse a portion of the metal coating on each ceramic particle and to diffuse the particulates in a contact region into the metal coating and into the article surface, thus securely bonding each particle to the surface.
  • This process relies on capillary action to draw the metallic coated ceramic particles to the substrate surface as well as sintering to diffuse the metal from the coated particles and from the coating into the substrate surface while driving off the thermoplastic binder.
  • a matrix metal is applied over the sintered ceramic particles to fill in spaces between the particles. This matrix is then simultaneously heated and presses to eliminate any voids which may be present and to securely bond the matrix to the substrate by interdiffusion.
  • An advantage of the methods of the present invention is that thin coatings of materials containing abrasive particles may be applied to the surface of a metallic substrate without first precoating the abrasive particles.
  • the expensive and time consuming step of coating abrasive particles prior to bringing them in contact with the surface of the substrate can thus be eliminated.
  • Another advantage of the present invention is that a thin, abrasive tip having a very high volume fraction of hard, ceramic particles for cutting the stator or shroud of a turbine may be applied to a turbine blade tip, thereby reducing the total thickness of the abrasive tip on the blade, and which may subsequently be lost to oxidation, thereby further decreasing rotor diameter.
  • a further advantage of the methods of the present invention is that thin coatings of materials containing a single layer, or multiple layers of abrasive particles, each layer forming a distinct plane parallel to other planes or layers and to the substrate surface may be applied, if desired.
  • Still a further advantage of the present invention is that a thin coating of materials containing abrasive particles may be applied to heat treatable substrates, such as nickel base superalloy turbine blade tips, while minimizing the exposure of the substrate to thermal treatments.
  • an improved method for applying an abrasive layer to a metallic substrate is provided.
  • the abrasive layer is comprised of abrasive particles having improved environmental resistance in a metal alloy matrix material.
  • the abrasive particles should be approximately coplanar and should have about the same aspect ratio, although different aspect ratios can be used.
  • the method for applying the abrasive layer to the metallic substrate comprises first selecting abrasive particles having about the same size and shape. The abrasive particles are then brought into physical contact with the substrate surface, while maximizing the volume fraction of particles on the surface. While the substrate to be coated and the abrasive particles are maintained in contact, a thin layer of a first metal is metallurgically deposited onto the surface of the substrate. This thin layer of metal forms a bond with the metallic substrate surface, while simultaneously entrapping the abrasive particles in position against the substrate surface, thereby adhering the abrasive particles to the surface.
  • this thin layer of the first metal is small in comparison to the size of the particles, the particles are not completely embedded in the thin layer by the deposition method.
  • a second metal layer which may be comprised of the same metal as the first metal layer, or which may be comprised of a second metal distinct from the metal of the first layer, is applied over both the first thin metal layer and the particles.
  • This second metal layer further has a distribution of fine alloying particles or powders which, following a heat treatment, forms on the metal substrate an abrasive layer having abrasive particles embedded in a substantially homogeneous or near homogeneous alloy metal matrix.
  • Fig. 1 is a cross-sectional view of a turbine blade having a tip formed of a single layer of substantially cubic-shaped abrasive particles embedded in a metal matrix.
  • Fig. 2 is a cross-sectional view of a piece of felt having an adhesive layer with abrasive particles applied, prior to removing excess particles.
  • Fig. 3 is a cross-sectional view of a piece of felt having an adhesive layer with abrasive particles applied, after removing excess particles.
  • Fig. 4 is a cross-sectional view of particle-bearing felt in physical contact with a turbine blade tip.
  • Fig. 5 is a cross-sectional view of particle-bearing felt in contact with a turbine blade tip after application of a a thin metal layer to the blade particle interface.
  • Fig. 6 is a cross-sectional view of a turbine blade tip having a thin metal layer bonded to the tip, with particles embedded in the layer and adhering to the tip as the adhesive-layered felt is peeled from the tip.
  • Fig. 7 is a cross-sectional view of a turbine blade tip after the adhesive-layered felt has been removed from the tip, but prior to deposition of the metal matrix.
  • Fig. 8 is a cross-sectional view of a turbine blade having an environmentally-resistant material which underlies the abrasive tip.
  • Fig. 9 is a cross-sectional view of a turbine blade having a tip formed of two layers of substantially cubic-shaped abrasive particles of substantially the same size embedded in a metal matrix.
  • An abrasive tip is applied to the tip of a turbine blade, such as those used in aircraft engine applications.
  • the tip is used to maintain a minimal clearance between the blade and the adjacent shroud or stator.
  • the tip rubs against the shroud, particularly during fast heat-ups and reburst cycles. Later in engine life, rub primarily occurs as a result of maneuvering loads. It is thus desirable for the abrasive tip to have a cutting ability while being held to the minimum practical thickness. Also, because of the harsh environment, it is desirable for the blade tip to have good environmental resistance.
  • the metal removal mechanisms involved in the removal of adjacent shroud material by the turbine blade tip during engine operation are unique because of the high temperatures, high surface speeds and low incursion rates associated with engine operation. Such conditions preclude the machining of chips which is the optimum stock removal route in conventional machining technology.
  • Blade tip speeds may be as high as about 1400 feet per second.
  • blade incursion on the shroud may be as high as 2 mils per incursion. There may be about a 4x10 ⁇ 9 to 8x10 ⁇ 9 inch incursion of the blade into the shroud per revolution of the bladed rotor during an incursion. At these tip speeds and incursion rates, no large metal chips are formed.
  • metal may be removed from the shroud by secondary adhesive wear, that is, wear due to welding of contacting asperities.
  • a turbine blade 10 having a dovetail end 12 and a tip end 14 is depicted.
  • An abrasive tip 16 comprised of a metal matrix material 18 and preferrably a single layer of abrasive particles 20 of approximately the same size is attached to tip end 14 which forms the substrate.
  • the abrasive particles 20 are oxidation-resistant, corrosion-resistant and preferrably non-conducting. These particles are preferrably alumina, Sialon, Si3N4 or refractory metal carbides such as chromium carbide, tantalum carbide, niobium carbide or tungsten carbide.
  • the abrasive particles 20 should be generally cubic or cuboidal in shape, thereby having an aspect ratio of about 1, although other shapes may be used. If other shapes are used, the particles should have the same aspect ratio.
  • the cubic shaped particles are preferred because this configuration provides for optimum packing density of particles on the blade tip, thus maximizing their volume fraction.
  • the size of the particles may vary from about 2 mils to about 15 mils on an edge, with the edge size being approximately the same (ie. about ⁇ 1 mil) in the size selected, although particles having an edge size of about 5-6 mils are most preferred.
  • cubic or cuboidal particles may be made by any effective process, it has been found that the Sol-Gel process produces a high concentration of cuboidal or cubic particles of the desired size. Materials produced by this proprietary process may be obtained from the 3-M Co. or the Norton Co.
  • a piece of felt 30 having an adhesive layer 32 on one surface 34 is brought into contact with selected abrasive particles 20.
  • Abrasive particles 20 adhere to adhesive layer 32 on one surface 34 of felt 30.
  • Abrasive particles 20 may form more than one layer over adhesive layer 32 as shown in Fig. 2. Because only a single layer of particles is preferred, excess particles may be removed from the felt by any known method, such as by shaking or blowing with an air stream sufficient to remove particles not contacting the adhesive without affecting those in contact with the adhesive, resulting in a single layer of abrasive particles 20 adhering to adhesive layer 32 as shown in Fig. 3.
  • particles 20 are brought into physical contact with tip end 14 of blade 10.
  • a thin layer of metal 36 is metallurgically deposited onto tip 14.
  • a fixture (not shown) be used. The fixture holds the blade in contact with the particles adhering to felt layer 30 during deposition of layer 36.
  • the force applied to assure solid contact between the tip 14 and the particles 20 may be supplied by gravity, by spring loading, clamping, or by any other suitable means.
  • Layer of metal 36 applied on the substrate, at tip 14 of Fig. 5, physically is located between tip 14, to which it is metallurgically attached, and adhesive layer 32 on felt layer 30.
  • Thin metal layer 36 also at least partially entraps abrasive particles 20 thereby causing them to adhere to tip 14 after removal of the adhesive-containing layer, identified as felt in this example.
  • Application of thin metal layer 36 may be accomplished by any deposition process which permits metal to contact the substrate tip 14 without affecting the physical contact between particles 20 and tip 14.
  • One method of applying metal layer 36 is by electroless plating metal into the region between tip 14 and adhesive layer 32.
  • the preferred method of application is complete immersion of blade tip 14 in an electroplating bath.
  • Tip 14 of blade 10 is then electroplated, preferrably with a metal selected from the group consisting of nickel or cobalt.
  • the thickness of metal layer 36 after electroplating is from about 0.1 to about 0.6 mils. Because the abrasive particles 20 are non-conducting in the preferred embodiment, no metal is deposited on them as a result of electroplating.
  • felt layer 30 having adhesive layer 32 may be removed from contact with abrasive particles 20. Because particles 20 are mechanically trapped by metal layer 36, felt layer 30 may be peeled back. However, other methods of removal of particles 20 from adhesive layer 32 may be utilized, so long as the bond between particles 20 and metal layer 36 remains undisturbed. For example, a suitable solvent may be introduced between felt layer 30 and metal layer 36 to dissolve adhesive layer 32, thereby allowing removal of felt layer 30.
  • abrasive particles 20 are in marked relief from thin metal layer 36 deposited over tip 14 as shown in Fig. 7. Because the bond between particles 20 and layer 36 is insufficient for the desired application, it is necessary to apply a matrix material over particles 20 before the abrasive tip can be effective in contact applications.
  • the metal matrix may be any metal or alloy, it is preferred that the metal matrix be a metal or alloy which includes prealloyed powder or particles. To accomplish the application of the metal matrix material, fine particles of prealloyed powder are mixed in an electroplating solution of a metal or alloy. The fine prealloyed powder particles and solution readily flow into the space between the abrasive particles.
  • the prealloyed powder particles are selected and applied in the appropriate volume fraction with the plating solution so that the metal matrix, after a suitable thermal treatment has the desired chemical composition.
  • a suitable volume fraction of NiCrAlY or CoNiCrAlY powder particles up to about 60%, are mixed in a solution of cobalt and are subsequently entrapped in a matrix of cobalt.
  • CoCrAlY particles are mixed in a solution of nickel and are subsequently entrapped in a matrix of nickel.
  • the turbine blade tip is heat treated so that the metal matrix having the entrapped powder particles is homogenized by a diffusion heat treatment, thereby yielding a homogeneous matrix having the desired chemical composition.
  • the second metal or alloy having fine prealloyed powder particles is deposited over thin metal layer 36 and abrasive particles 20 to form a metal containing fine prealloyed powder particles surrounding abrasive particles 20, preferably using co-electrodeposition.
  • Co-electrodeposition developed by Bristol Aerojet Limited, is described in U.S. Patent No. 4,305,792 incorporated herein by reference.
  • the article to be coated is placed in a barrel together with the particles, and the barrel is placed in a plating bath and rotated therein.
  • the barrel has an opening covered by a cover which is pervious to the plating solution, but impervious to the particles.
  • the article is thus flowed over by solution within the barrel which can have a high concentration of particles, but there are no particles in the part of the bath outside the barrel.
  • the process may be electroless or electrolytic.
  • the depositing of the matrix of this invention may be accomplished by any suitable co-electrodeposition technique.
  • This second metal is applied over the abrasive particles in relief and the first thin metal layer 36. It is applied as a fine powder-containing plating solution in which the solution preferably is selected from the group of Co, and Ni, and is usually the same metal as the first thin layer
  • the prealloyed, fine powder in the plating solution is a MCrAlY powder wherein M is an element selected from the group of Co, Ni and combinations thereof.
  • the second metal and particles may completely envelop particles 20 or may leave abrasive particles 20 in slight relief as shown in Fig. 1.
  • the preferred thickness of second metal matrix 18 is approximately 60 to 70% of the average size of abrasive particles 20. For example, when the preferred particle size of about 5 to 6 mils is selected, the preferred second metal deposit thickness is from about 3 to about 4.5 mils.
  • the preferred method of depositing second containing fine prealloyed powder particles (not shown) over abrasive particles 20 and thin layer 36 to form abrasive tip 16 is by co-electrodeposition.
  • a single layer of abrasive particles 20 is enveloped in a first thin metal layer 36 on top of which is deposited a second metal matrix 18 having prealloyed fine powder or particles (not shown).
  • a second metal matrix 18 having prealloyed fine powder or particles (not shown).
  • the homogenizing is accomplished by a homogenizing thermal treatment which must be for a sufficient time and at a sufficient temperature to achieve a substantially uniform alloy composition throughout the metal matrix 18 and thin metal layer 36 applied onto tip end 14, without adversely affecting the substrate material.
  • the volume fraction of pre-alloyed powder is typically about 60% the co-electrodeposited materials, the metal solution comprising the balance. This volume fraction will vary depending upon the final desired composition of the metal matrix, the metal solution composition and the alloy powder composition.
  • second metal matrix 18 may be Ni or Co, containing a MCrAlY powder, both the metal and powder selected so as to be compatible with thin metal layer 36.
  • thin metal layer 36 is selected from the group consisting of Ni and Co
  • the metal of the second metal matrix is also selected from the group Ni and Co
  • MCrAlY alloy powder is chosen such that M is selected from the group of elements consisting of Co and Ni.
  • first metal layer 36 and the second metal are the same element, either both Ni or both Co, and M of the MCrAlY is the remaining element (i.e., when second metal is Co, the powder is NiCrAlY) or a combination of Ni and Co i.e., NiCoCrAlY.
  • the blade After application of a first cobalt thin layer 36 by electrodeposition and fine CoNiCrAlY powders in a second cobalt layer over the first thin layer by co-electrodeposition, thereby surrounding abrasive particles 20 on the tip of a Rene′ 80 turbine blade, the blade is heat treated in an inert gas atmosphere or vacuum for about 4 -8 hours at about 1925-1950°F.
  • the metal composition is initially essentially 100% Co and incidental elements which do not adversely affect the composition while the composition of the prealloyed CoNiCrAlY powder is, by weight, about about 54% Ni, about 32% Cr, about 13.5% Al, about 0.8 Y, and incidental elements which do not adversely affect the alloy powder.
  • the heat treatment substantially homogenizes the metal matrix 18 surrounding abrasive particles 20, so that the composition of metal matrix 18 after heat treatment is, by weight, about 31-33% Ni, about 19-22% Cr, about 7-9% Al, about 0.35-0.65% Y, and the balance Co and small amounts of incidental elements which do not adversely affect the alloy.
  • the blade After application of a first cobalt thin layer 36 by electrodeposition and fine CoNiCrAlY powders in a second cobalt layer by co-electrodeposition over the first thin layer, thereby surrounding abrasive particles 20 on the tip of a Rene′ N5 turbine blade, the blade is heat treated in an inert gas atmosphere or vacuum for about 2-4 hours at about 1975-2050°F.
  • the metal composition is initially essentially 100% Co and incidental elements which do not adversely affect the alloy, while the composition of the fine prealloyed powder is, by weight, about about 54% Ni, about 32% Cr, about 13.5% Al, about 0.8 Y, and incidental elements which do not adversely affect the alloy powder.
  • the heat treatment substantially homogenizes metal matrix 18 surrounding the abrasive particles, so that the composition of metal matrix 18 after heat treatment is, by weight, about 31-33% Ni, about 19-22% Cr, about 7-9% Al, about 0.35-0.65% Y, and the balance Co and small amounts of incidental elements which do not adversely affect the alloy.
  • a first cobalt thin layer 36 by electrodeposition After application of a first cobalt thin layer 36 by electrodeposition, and fine powders having a composition by weight of about 20% Co, 10.2% Al, 10.7% Ta, 11.3 % Cr, 2.5% Hf, 4.7% Re, 0.2% C, 8.3% W and the balance Ni and incidental impurities in a second nickel layer by co-electrodeposition over the first thin layer, thereby surrounding abrasive particles 20 on the tip of a Rene′ N5 turbine blade, the blade is heat treated in an inert gas atmosphere or vacuum for about 2-4 hours at about 2000-2075°F. This heat treatment substantially homogenizes metal matrix 18, thin layer 36 and the fine powder so that the composition of the metal matrix after heat treatment is the composition of Rene′ 142, Table 1.
  • the blade After application of a first cobalt thin layer 36 by electrodeposition, and fine powders having a composition by weight of about 6.7% Co, 10% Al, 8.3% Ta, 15% Cr, 1.5% Hf, 2.5% Mo, 2.3% Re, 0.03% Zr and the balance Ni and incidental impurities in a second nickel layer by co-electrodeposition over the first thin layer, thereby surrounding abrasive particles 20 on the tip of a Rene′ N5 turbine blade, the blade is heat treated in an inert gas atmosphere or vacuum for about 2-4 hours at about 2000-2075°F.
  • the heat treatment substantially homogenizes metal matrix 18, thin layer 36 and the fine powder so that the composition of the metal matrix after heat treatment is the composition of PS6MY, see Table 1.
  • a first cobalt thin layer by electrodeposition and fine powders having a composition by weight of about 16.7% Co, 10.8% Al, 10% Ta, 30% Cr, 0.83% Hf, 3.3% Re, 0.07% C, 0.02% Zr and the balance Ni and incidental impurities in a second nickel layer by co-electrodeposition over the first thin layer, thereby surrounding abrasive particles 20 on the tip of a Rene′ N5 turbine blade, the blade is heat treated in an inert gas atmosphere or vacuum for about 2-4 hours at about 2000°-2075°F. This heat treatment substantially homogenizes metal matrix 18, thin layer 36 and the fine powders so that the composition of the metal matrix after heat treatment is the composition of BC-53, see Table 1.
  • particles 20 may optionally be coated with a coating, such as a diffusion barrier coating, prior to placing the particles in contact with adhesive layer 32.
  • a coating such as a diffusion barrier coating
  • nonconductive and nonsilicon-bearing particles such as alumina (Al2O3).
  • abrasive tip 16 will be removed from tip 14 of blade 10 in a relatively short time as compared to overall blade life.
  • the abrasive tip is applied by the process of the present invention over the environmentally resistant material, in which case the environmentally resistant material is substituted for the substrate in the above description of the invention.
  • a commonly used environmentally resistant material has a nominal composition of, by weight, of about 33% Ni, about 23% Cr, about 4% Al, about 0.5% C, about 3% W, about 33% Co, about 3% Ta, about 0.75% Si. along with incidental impurities.
  • This composition is described in U.S. Pat. No. 4,227,703 issued Oct. 14, 1980, which is hereby incorporated by reference.
  • this environmentally resistant undercoat is provided by way of example, and is not meant to limit application of the long life abrasive tip of the present invention solely over this environmentally resistant undercoat.
  • a turbine blade having an environmentally resistant layer 44 overlaying tip 14 is shown in Fig. 8.
  • the method of, the present invention can be used to apply multiple layers of particles, so that even if the initial layer of particles is worn off the tip, additional layers of particles remain so that additional material can be abraded from the shroud, if necessary.
  • a turbine blade 80 having an abrasive tip 82 with two rows of abrasive particles, 84 and 86 embedded in a metal matrix 88 is depicted.
  • Abrasive particles 84 in the layer closest to blade tip 90 are coplanar and parallel to the plane of abrasive particles 86 forming the layer furthest from blade tip 90.
  • particles 84 and 86 are shown as being about the same size, it may be desirable to size the particles such that particles 86 are larger, which is desirable during three-body-abrasive wear which occurs early in engine operation, while particles 84, which are smaller, will remain after the layer containing particles 86 has worn away. The smaller particles in the layer closer to the tip will be more effective during the adhesive wear phases which may occur during later stages of engine operation.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Organic Chemistry (AREA)
  • Electrochemistry (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Polishing Bodies And Polishing Tools (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Electroplating Methods And Accessories (AREA)
EP91309998A 1990-11-01 1991-10-30 Extrémité abrasive pour aube de turbine Withdrawn EP0484115A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US60796890A 1990-11-01 1990-11-01
US607968 1996-02-29

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EP0484115A1 true EP0484115A1 (fr) 1992-05-06

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JP (1) JPH04285198A (fr)
CA (1) CA2048804A1 (fr)

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WO2002068799A1 (fr) * 2001-02-28 2002-09-06 Mitsubishi Heavy Industries, Ltd. Moteur a combustion, turbine a gaz et couche de polissage
WO2002103165A1 (fr) * 2001-06-13 2002-12-27 Mitsubishi Heavy Industries, Ltd. Procede de formation d'une couche resistant a l'abrasion pour aubes en deplacement, couche resistant a l'abrasion et procede de regeneration de celle-ci, et turbine a gaz y relative
US6702553B1 (en) 2002-10-03 2004-03-09 General Electric Company Abradable material for clearance control
EP1460152A1 (fr) * 2003-03-21 2004-09-22 ALSTOM Technology Ltd Méthode de dépôt d'un revêtement étanche résistant à l'usure et système d'étanchéité
EP1674662A1 (fr) * 2004-12-23 2006-06-28 Siemens Aktiengesellschaft Electrolyte pour le dépôt d'un alliage et procédé de dépôt électrolytique
EP2096194A2 (fr) 2008-02-19 2009-09-02 Parker-Hannifin Corporation Revêtement protecteur pour joints métalliques
EP2105520A1 (fr) * 2008-03-25 2009-09-30 Kabushiki Kaisha Toshiba Procédé de revêtement et appareil d'électrolysation utilisé avec celui-ci
WO2009146684A2 (fr) * 2008-06-05 2009-12-10 Mtu Aero Engines Gmbh Dispositif à utiliser dans un procédé de fabrication d'une couche de protection et procédé de fabrication d’une couche de protection
WO2014074370A3 (fr) * 2012-11-06 2014-07-17 Siemens Energy, Inc. Bout de pale de turbine revêtu d'un abrasif
WO2014151101A1 (fr) 2013-03-15 2014-09-25 United Technologies Corporation Traitement de bout de pale de turbine pour des turbines à gaz industrielles
EP2851455A1 (fr) * 2013-09-18 2015-03-25 MTU Aero Engines GmbH Revêtement anti-usure fabriqué par procédé galvanique et son procédé de fabrication
WO2015041787A1 (fr) * 2013-09-19 2015-03-26 Siemens Energy, Inc. Pale de turbine à bouts de surface portante présentant des bouts coupants
GB2529854A (en) * 2014-09-04 2016-03-09 Rolls Royce Plc Rotary blade tip
EP3020931A1 (fr) * 2014-10-31 2016-05-18 United Technologies Corporation Revêtement de rotor abrasif présentant des caractéristiques de limitation de force de frottement
EP3056679A1 (fr) * 2015-02-12 2016-08-17 United Technologies Corporation Pointe de lame abrasive présentant une usure améliorée à taux d'interaction élevé
EP3095965A1 (fr) * 2015-05-20 2016-11-23 Rolls-Royce plc Composant de moteur à turbine à gaz
US10822967B2 (en) 2017-02-01 2020-11-03 Raytheon Technologies Corporation Wear resistant coating, method of manufacture thereof and articles comprising the same
US11299993B2 (en) 2019-10-28 2022-04-12 Honeywell International Inc. Rotor assembly for in-machine grinding of shroud member and methods of using the same
US11713681B1 (en) 2022-05-18 2023-08-01 Raytheon Technologies Corporation Fan blade repair systems and methods

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DE4121839C2 (de) * 1991-07-02 2003-01-09 Werner Hermann Wera Werke Werkzeug mit drehmomentübertragenden Arbeitsflächen und Verfahren zur Herstellung desselben
US5893915A (en) * 1996-04-18 1999-04-13 Microsoft Corporation Local font face selection for remote electronic document browsing
JP2003148103A (ja) 2001-11-09 2003-05-21 Mitsubishi Heavy Ind Ltd タービンおよびその製造方法
DE60231084D1 (de) * 2002-12-06 2009-03-19 Alstom Technology Ltd Verfahren zur selektiven Abscheidung einer MCrAlY-Beschichtung
WO2008135803A1 (fr) * 2007-05-04 2008-11-13 Mtu Aero Engines Gmbh Procédé de fabrication d'un revêtement abrasif sur un composant de turbine à gaz
US9957629B2 (en) * 2014-08-27 2018-05-01 Praxair S.T. Technology, Inc. Electroplated coatings
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US10428437B2 (en) 2013-09-18 2019-10-01 MTU Aero Engines AG Wear-resistant coating produced by electrodeposition and process therefor
EP2851455A1 (fr) * 2013-09-18 2015-03-25 MTU Aero Engines GmbH Revêtement anti-usure fabriqué par procédé galvanique et son procédé de fabrication
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