EP2516688A1 - Procédé de fabrication d'un joint d'étanchéité de rotor/stator d'une turbine à gaz - Google Patents

Procédé de fabrication d'un joint d'étanchéité de rotor/stator d'une turbine à gaz

Info

Publication number
EP2516688A1
EP2516688A1 EP10787445A EP10787445A EP2516688A1 EP 2516688 A1 EP2516688 A1 EP 2516688A1 EP 10787445 A EP10787445 A EP 10787445A EP 10787445 A EP10787445 A EP 10787445A EP 2516688 A1 EP2516688 A1 EP 2516688A1
Authority
EP
European Patent Office
Prior art keywords
sealing
ceramic layer
housing part
segments
rotor
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Withdrawn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
EP10787445A
Other languages
German (de)
English (en)
Inventor
Jan Oke Peters
Volker Tiedemann
Christian W. Siry
Dietmar Stunz
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.)
Lufthansa Technik AG
Original Assignee
Lufthansa Technik AG
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 Lufthansa Technik AG filed Critical Lufthansa Technik AG
Publication of EP2516688A1 publication Critical patent/EP2516688A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00—Restoring or reconditioning objects
    • B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
    • B23P6/007—Repairing turbine components, e.g. moving or stationary blades, rotors using only additive methods, e.g. build-up welding
    • 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
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • 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
    • C23C4/18—After-treatment
    • 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
    • F01D11/122—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 with erodable or abradable material
    • 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
    • F01D5/005—Repairing methods or devices
    • 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
    • F05D2230/10—Manufacture by removing 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
    • F05D2230/312—Layer deposition by plasma 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
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • 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
    • F05D2300/21—Oxide ceramics
    • 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

Definitions

  • the invention relates to a method for applying a ceramic layer to the sealing surfaces of arranged on the inner circumference of a turbine housing part sealing segments of a rotor / stator seal of a gas turbine.
  • turbomachinery in particular gas turbines, such as ⁇ example as jet engines of airplanes, reduce leakage through gaps between cooperating and moving relative to each rotor and stator components efficiency.
  • gas turbines such as ⁇ example as jet engines of airplanes
  • the gap is thus variable in the operation of the gas turbine
  • inlet seals abradable seals
  • US 4,299,865 so-called inlet seals.
  • the blade tips of the rotor are made of a hard material or with a hard Layer provided and formed the inlet seal of the surrounding stator relatively soft. In various operating conditions, it can then be a run-in of the
  • Shovel tips come into the stator seal and a material removal of the inlet seal take place without damaging the blades takes place.
  • the invention has for its object to provide a method of the type mentioned, which allows a simple and inexpensive application of an inlet layer (abradable seal) and in particular for a renewal or replacement of a rotor / stator seal in the course of maintenance or repair a gas turbine is suitable. According to the invention it is provided that the application of the Ke ⁇ ramik für takes place while the sealing segments are in the installed state in the turbine housing part.
  • a gas turbine is a flow machine in which the thermal energy produced by combustion of a Kohlenwas ⁇ hydro- or other fuels hot gas stream is converted into mechanical energy.
  • the invention is particularly applicable to jet or Turboproptrieb ⁇ plants of aircraft.
  • a rotor / stator seal seals in a rotational movement relative to each other running components of the gas turbine against ⁇ each other, in particular the blade tips of a rotor against the circumference of a surrounding turbine housing.
  • turbine housing part designates that part of the turbine which has or holds the stator seal surrounding the rotor.
  • it may in particular be a module of a jet engine in which the stator seal is arranged.
  • Dichtseg ⁇ elements are arranged on the inner circumference of this turbine housing part.
  • the term sealing segments called de- mountable or individually replaceable parts, each dress a fraction of the inner circumference of the turbine housing from ⁇ .
  • a plurality of sealing segments extending over the entire circumference of the turbine housing portion and bil ⁇ det together the stator seal.
  • the sealing segments have sealing surfaces, which are those surfaces which face the rotor.
  • a ceramic layer is applied on these sealing surfaces according to the invention.
  • the term ceramic layer designates in the context of the invention all materials which have a proportion of ceramic materials and are suitable for forming a so-called abradable seals (inlet seal).
  • these ceramic layers are based on materials such as ZrÜ 2 , Al 2 O 3 and / or other metal, transition metal or rare earth oxides or
  • the application of the ceramic layer, while the sealing segments are in the installed state in the turbine housing part takes place.
  • This coating in the installed state has a number of advantages.
  • the gas turbine or the jet engine ⁇ factory must be disassembled only to the module level, the time-consuming and therefore costly disassembly down to the item level ⁇ eliminated.
  • On the other in a coating in the fitted state at the module level from the outset a uniform wear will be ⁇ equalized over the periphery of ceramic layer.
  • unavoidable tolerances in the course of the downstream installation of the sealing segments lead to inequalities at the transitional or abutting points in the circumferential direction of adjoining sealing segments, so that, as a rule, post-processing (for example Grinding) is required to produce a leveled over the entire circumference sealing surface.
  • the ceramic layer is carried out according to the invention particularly preferably by atmospheric plasma spray (APS).
  • APS atmospheric plasma spray
  • a plasma jet is used, the thermal energy is he witnesses ⁇ by the recombination of a gas plasma previously generated.
  • the Ma ⁇ TERIAL is supplied as a powder.
  • the material is applied in a normal ambient atmosphere.
  • the use of atmospheric plasma spraying as a method of applying the ceramic layer has the particular advantage that the usually quite large turbine housing parts do not have to be transferred in a controlled At ⁇ gas atmosphere such as a vacuum chamber.
  • the achievable at atmospheric plasma spraying quality of the ceramic layer is sufficient for the purposes OF INVENTION ⁇ to the invention without further ado.
  • the turbine housing portion already mentioned several times may be ER inventively example, a so-called High Pressure Turbine Shroud Support (HPT shroud support) ⁇ a jet engine.
  • HPT shroud support High Pressure Turbine Shroud Support
  • the ceramic layer applied according to the invention preferably has a porosity of 10 to 40% by volume, more preferably 20 to 30% by volume.
  • a sol ⁇ che porosity contributes to the ceramic layer sufficiently soft to shape and give it to run-known companies.
  • the material or friction pair should be designed in such a way that finally or predominantly the ceramic layer sealing surface is removed and no or only a slight wear on the blade tip occurs.
  • the egg contains ⁇ NEN portion of a thermally removable substance to ceramic material ⁇ placed at the time of application. It can play, be a polymer as ⁇ a polyester in particular. Thermally removable loading indicates that the substance escapes in the supply of thermal energy far ⁇ substantially or completely without residue from ceramics ⁇ layer while leaving behind cavities in the form of pores. The removal can be done by evaporation, sublimation or thermal decomposition or combustion with the escape of gaseous decomposition products.
  • suitable spray-on ceramic powders may be based on YSZ (yttria stabilized zirconia) and may contain 3 to 9 wt%, preferably 4 to 6 wt% polyester to produce the desired porosity.
  • a suitable powder is available, for example, from Sulzer Metco under the designation Metco 2460 NS.
  • the thickness of the applied ceramic layer may Invention ⁇ accordance more preferably between 0.1 and 0.7 mm, 0.1 and 0.5 mm. Frequently layers are applied in the range 0.2 to 0.4 or 0.2 to 0.3 mm.
  • an adhesion promoter layer is present prior to the application of the ceramic layer the substrate of the sealing segments is applied.
  • the thickness of the adhesive layer is preferably 0.1 mm or we ⁇ niger.
  • M is a metal selected from the group nickel, cobalt, iron, or combination ⁇ nations thereof is.
  • Other elements such as hafnium or silicon as so-called reactive element additions can be added to increase the oxidation resistance and lifetime of the bonding agent layer (bond coat).
  • the primer layer is preferably also applied by plasma spraying. Possibly.
  • a suitable material for the adhesion promoter layer is, for example, a CoNiCrALY-based fine-grained powder, likewise available from Sulzer Metco, such as, for example, Amdry 365-2.
  • cooling air holes available to reduce the thermal load on the HPT Shrouds. It may be advantageous in the context of the invention to close these cooling air holes prior to application of the ceramic layer and any adhesion promoter layers or other layers in order to prevent the cooling air holes are closed or reduced in cross-section impermissibly. According to a variant of the He-making ⁇ such cooling holes are before applying the ceramic layer (and preferably also before the application of an adhesive layer or other possible intermediate layers) is temporarily closed with a thermally removable material.
  • Thermally removable means that, following the application of the key, Ramik Mrs and any post-processing such as ⁇ example loops or the like can be removed by a heat treatment or in a first turbine run is removed by the then occurring heat load.
  • the thermal removal can be carried out in particular by evaporation, sublimation or thermal decomposition to preferably gaseous decomposition products. It is preferably carried out completely or largely without residue.
  • Preferred thermally removable materials are polymers or plastics. It is preferred that thede Kunststoffboh ⁇ ments are sealed with a not yet cured mixture of monomers, oligomers and / or prepolymers, which are then brought to cure.
  • the curing can be induced according to the invention by heat or preferably by light or UV radiation.
  • UV or light-curing plastics more preferably acrylates and / or methacrylates.
  • these may be epoxy acrylates, urethane acrylates, polyester acrylates, polyether acrylates and silicone acrylates.
  • Corresponding light-curing plastics are familiar to the person skilled in the art.
  • the viscosity and composition of the Ver ⁇ circuit of the cooling air holes not yet hardened overall premix is preferably of the form that a secure appli- cation of a viscous gel is possible and this does not flow away, or only in an unacceptable way even before curing.
  • Suitable plastics and adhesives are at ⁇ play as available from Dymax Europe GmbH, Frankfurt.
  • the invention further relates to a method for repair of sealing surfaces of the inner circumference of a Turbinenge housing part arranged sealing segments of a rotor / stator seal a gas turbine, comprising the steps: provide the disassembled Turbinengeha seteils, wherein the sealing segments in the Einbauzu ⁇ stood in the turbine housing part are, b) removing material from the sealing surfaces of the sealing segments, c) applying a ceramic layer by means of a procedural ⁇ proceedings according to any one of claims 1 to 12th
  • Another object of the invention is a method for repairing a gas turbine, the at least one rotor and arranged on the inner circumference of a turbine housing part
  • Sealing segments of a rotor / stator seal wherein in the new state of the gas turbine, a sealing gap between the Ro ⁇ torulatelspitzen and the sealing surfaces of the sealing segments is provided, with the steps: a) dismantling the gas turbine and provide the disassembled turbine housing part, wherein the Sealing segments are in the installed state in the turbine housing part,
  • the focus is on a repair process in which a targeted new production of the sealing surfaces takes place.
  • the repair is carried out at the level of the turbine housing module without further ⁇ re decomposition into the individual parts, ie in particular with the sealing segments in the installed state. Further erfindungsge ⁇ Gurss will wear off of the sealing surfaces of the sealing segments material, so that space is created for the Neuaufmine a ceramic layer according to the inventive method.
  • the repaired turbine housing parts or gas turbines before carrying out the method according to the invention a metallic sealing surface, so neither a inventively brought ⁇ or otherwise ceramic-like sealing surface.
  • a sealing gap at a according to the invention carried out repair is smaller than the sealing ⁇ gap in the new state of the gas turbine. It is thus a method by which the efficiency of a gas turbine can be increased.
  • Green Aviation in which the fuel consumption and CO 2 emissions from aircraft engines to be reduced. This aspect of the invention will be explained in more detail below.
  • the repair methods of the invention are useful in gas turbines, which have a ceramic sealing ⁇ surface when new and for which it is intended that the blade tips of the rotor enter in certain operating states in these sealing faces and cause material removal.
  • the blade tips of the turbine blades are often provided with an armor or on the basis of cubic Bohrnitrid (CBN).
  • CBN cubic Bohrnitrid
  • a ceramic layer may be listed on the sealing surface ⁇ accordance with the repair method of claim 14 even when such a gas turbine having metallic sealing surfaces be brought.
  • the metallic sealing surface is completely or partially removed, so that on the inner circumference of the corresponding turbine housing part space is available for the inventive application of a ceramic sealing surface.
  • This can be designed and applied so that after reassembly of the gas turbine, the sealing gap is lower than in the new state with me ⁇ tallischer sealing surface. The reduction of the sealing gap is possible since, in the case of the ceramic sealing surface applied according to the invention, a running-in of the blade tips into the
  • Sealing surface can be tolerated. If such Einlau ⁇ fen takes place, is unmarried ⁇ Lich removed this ceramic layer due to the material combination of the incoming tip into the soft ceramic layer. If, in unfavorable operating conditions, an unintentional run-in of the blade tip in the metal sealing surface occurs in the case of a metallic sealing surface, the blade tips of the rotors may also come to a material removal , so that the sealing gap is further enlarged and also due to a restoration of the sealing surface can not be brought back to the originally intended level.
  • the use of the atmospheric plasma spraying in the execution of the method according to the invention has the advantage whe- ren a relatively low process temperature ⁇ structure. Since the plasma jet relatively little thermal energy contributes to the coated sealing segments over ⁇ , a possible delay of the assembled components is avoided. As will be explained below in the exemplary embodiment, it is possible during the coating to rotate the module with the built-in sealing segments, so that the exposure time of the plasma jet to a single sealing segment is relatively low and the corresponding one Segment may cool during further rotation of the module before it comes into contact with the plasma jet again.
  • Fig. 1 a cross section through a gas turbine section; 2 shows a plan view of the turbine housing;
  • FIG. 5 shows schematically the procedure for a material removal from the sealing surfaces in the course of the preparation of the method according to the invention
  • FIG. 2 shows a turbine housing 1 in plan view
  • the reference numeral 5 schematically shows the axis of rotational symmetry of the gas turbine.
  • Distributed on the rotor disk 6 are a plurality of turbine blades 7 (rotor blade or rotor blades) distributed over the circumference.
  • the radially outwardly pointing tips of the turbine blade 7 seal against the sealing surfaces 4 of the sealing segments 3 and close with these a sealing gap 8, which is calculated from the difference of the stator radius 9 and the rotor radius 10 radius.
  • the arrow 11 indicates the Rich ⁇ direction of the gas flowing through the gas turbine gas stream.
  • FIG. 3a shows the initial state also shown in FIG.
  • the sealing segment 3 has a metallic sealing surface in this embodiment.
  • Reference numeral 13 denotes cooling air holes in the sealing segment 3.
  • FIG. 4 shows schematically the flow of a SEN invention shown repair procedure.
  • FIG. 4a shows the initial state of a sealing segment 3 before the repair, in which a certain removal of the sealing surface 4 has taken place as a rule; if necessary, an inlet not shown in FIG. 4a (see reference numeral 14 in FIG. 3c) can also be present.
  • Figure 4 The entire repair process shown in Figure 4 takes place in the installed state of the sealing segments in the turbine housing 1, as shown in Figure 2.
  • Figure 4 for clarity only a single sealing segment is provided ⁇ represents respectively.
  • Figure 5 shows schematically a removal of material from the sealing surfaces 4 of the sealing segments 3.
  • a grinding tool 15 is rotated for this purpose against the sealing surfaces 4. Instead of grinding, other removal methods such as milling or eroding can be used.
  • the result of the material removal is shown schematically in FIG. 4b.
  • the cleaning includes degreasing, rinsing with deionized water and drying, for example at 120 ° C, optionally under reduced pressure ⁇ air.
  • a so-called activation beam is performed.
  • Al20 3- Strahlgut the grain size mesh 36 is used.
  • the following beam parameters are suitable for the activation beam: Rotation speed 15min -1 , two vertical strokes, jet pressure 1.6 bar, nozzle distance 200 mm, spray angle 45 °. It should be avoided that blasting material enters the cooling air holes 13.
  • the applied activation layer is shown schematically at 16 in FIG. 4c.
  • a temporary closing of the cooling air channels 13 will usually be useful.
  • a light-curable PU-based plastic either punctiform by means of a pipette or a similar application instrument or with the aid of shaping masking aids such.
  • a bonding agent layer 18 shown schematically in FIG. 4e is applied.
  • a CoNiCrALY-based fine powder (Amdry 365-2) is applied by atmospheric plasma spraying.
  • FIG. 6 shows schematically how a coating unit 19 with a plasma jet 20, by relative movement with respect to the turbine housing 1, covers the entire circumference of FIG.
  • the following coating parameters are used: Hub 1, 3, 6% vertical speed of the robot, Rotati ⁇ ons Norwegian 27min -1.
  • the thickness of the adhesion promoter layer applied in this way is preferably 0.03 to 0.05 mm.
  • a erosi ⁇ onsfeste ceramic intermediate layer using a Ke ⁇ ramikpulvers such as Praxair 1484 may be applied to the adhesion promoter layer.
  • the inventive soft ceramic ⁇ layer (abradable coating) is applied with the coating unit 19th
  • the layer is shown schematically at 21 in FIG. 4f.
  • the coating material used is Metco 2460 NS. The following coating parameters are used:
  • the ceramic layer 21 is typically applied in a thickness of 0.2 to 0.7 mm.
  • the sealing surfaces 4 of the sealing segments 3 are ground down to the desired stator radius. Possibly caused by the plastic plug 17 unevenness of the sealing surface 4 such as Materialhö ⁇ cker be removed. After grinding, the plastic plugs 17 project up to the sealing surface 4, as shown schematically in FIG. 4g.
  • the plastic plugs 17 are thermally decomposed either by a separate heat treatment or when the engine is put into operation for the first time and are essentially recycled. Stand free from the cooling air holes 13.
  • the ready-to-operate state produced in this way is shown schematically in FIG . 4h.
  • Figure 7 shows the invention possible reduction of a sealing gap and thus increasing theidesgra ⁇ of a jet engine within the so-called
  • FIG. 7 a shows the original state in which the turbine blades 7 run against a metallic sealing surface 4 of the sealing segments 3. There is a relatively large sealing gap 8 is required to occur through the leakage currents and efficiency losses.
  • FIG. 7b shows the state after application of a porous ceramic layer 21 according to the method according to the invention. Due to its porosity of about 30% by volume, this layer is relatively soft.
  • the sealing gap 8b can be reduced here compared to ⁇ over the initial state.
  • the sealing gap 8 may be of the order of 0.5 to 2 mm, the amount of the reduced sealing gap 8b may be 0.1 to 0.4, preferably 0.1 to 0.3, more preferably 0.1 to 0.2 mm be lower.
  • a sealing gap reduction to 0.2 mm in the high pressure turbine of an engine can play at ⁇ as the fuel consumption and the CO 2 - reduce emissions by about 0.3%.
  • FIG. 8 shows diagrammatically a run-in of turbine blades 7 into the sealing surface 4 of a sealing segment 3 which is possible during operation of the engine.
  • an inlet notch schematically indicated by 14 in FIG. 8b is created. Since this inlet notch in the soft ceramic layer 21 ent ⁇ stands, there is no or only a very small Ma Material removal at the top of the turbine blade 7, so that the radial length 15 remains substantially unchanged.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un procédé d'application d'une couche de céramique (21) sur les surfaces d'étanchéité (4) de segments d'étanchéité (3) d'un joint d'étanchéité de rotor/stator d'une turbine à gaz agencés sur la périphérie intérieure d'une partie de carter de turbine (1). Selon l'invention, l'application de la couche de céramique (21) a lieu tandis que les segments d'étanchéité (3) se trouvent, à l'état monté, dans la partie de carter de turbine (1).
EP10787445A 2009-12-23 2010-12-06 Procédé de fabrication d'un joint d'étanchéité de rotor/stator d'une turbine à gaz Withdrawn EP2516688A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009060570A DE102009060570A1 (de) 2009-12-23 2009-12-23 Verfahren zum Herstellen einer Rotor/Statordichtung einer Gasturbine
PCT/EP2010/068948 WO2011076549A1 (fr) 2009-12-23 2010-12-06 Procédé de fabrication d'un joint d'étanchéité de rotor/stator d'une turbine à gaz

Publications (1)

Publication Number Publication Date
EP2516688A1 true EP2516688A1 (fr) 2012-10-31

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP10787445A Withdrawn EP2516688A1 (fr) 2009-12-23 2010-12-06 Procédé de fabrication d'un joint d'étanchéité de rotor/stator d'une turbine à gaz

Country Status (4)

Country Link
EP (1) EP2516688A1 (fr)
CN (1) CN102985582A (fr)
DE (1) DE102009060570A1 (fr)
WO (1) WO2011076549A1 (fr)

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DE102011122549A1 (de) 2011-12-28 2013-07-04 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Reparatur einer Einlaufschicht eines Verdichters einer Gasturbine
GB201205663D0 (en) * 2012-03-30 2012-05-16 Rolls Royce Plc Effusion cooled shroud segment with an abradable system
JP6067869B2 (ja) * 2012-11-06 2017-01-25 シーメンス エナジー インコーポレイテッド タービンエアロフォイルのアブレイダブル皮膜システムおよび対応するタービンブレード
US9598973B2 (en) 2012-11-28 2017-03-21 General Electric Company Seal systems for use in turbomachines and methods of fabricating the same
DE102017207238A1 (de) * 2017-04-28 2018-10-31 Siemens Aktiengesellschaft Dichtungssystem für Laufschaufel und Gehäuse
CN108130504A (zh) * 2018-01-25 2018-06-08 无锡锡压压缩机有限公司 一种螺杆压缩机用陶瓷类转子及加工方法
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WO2011076549A1 (fr) 2011-06-30
CN102985582A (zh) 2013-03-20

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