CN102985582A - Method for producing a rotor/stator seal of a gas turbine - Google Patents

Method for producing a rotor/stator seal of a gas turbine Download PDF

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Publication number
CN102985582A
CN102985582A CN2010800589980A CN201080058998A CN102985582A CN 102985582 A CN102985582 A CN 102985582A CN 2010800589980 A CN2010800589980 A CN 2010800589980A CN 201080058998 A CN201080058998 A CN 201080058998A CN 102985582 A CN102985582 A CN 102985582A
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CN
China
Prior art keywords
ceramic layer
seal section
sealing
turbine
housing parts
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Pending
Application number
CN2010800589980A
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Chinese (zh)
Inventor
J·O·彼得斯
V·蒂德曼
C·W·西里
D·施图恩茨
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Lufthansa Technik AG
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Lufthansa Technik AG
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Publication of CN102985582A publication Critical patent/CN102985582A/en
Pending legal-status Critical Current

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    • 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

Abstract

The invention relates to a method for applying a ceramic layer (21) to the sealing surfaces (4) of sealing segments (3) arranged on the inner circumference of a turbine housing part (1) of a rotor/stator seal of a gas turbine. According to the invention, the ceramic layer (21) is applied while the sealing segments (3) are in an installed state in the turbine housing part (1).

Description

Method for the manufacture of the rotor/stator sealing of internal combustion turbine
Technical field
The present invention relates to a kind of method for ceramic layer being applied on trim gas turbine rotor/seal stator section, that be arranged in the seal section on week in the turbine housing parts.
Background technology
In the jet engine of turbine, especially internal combustion turbine, for example aircraft, can lower efficiency in the caused leakage flow of rotor and the gap between the stator component of interactional and relative movement.For interspace loss is minimized, and and then so that fluid machinery in other words turbine keep high-level efficiency, need will be in machine running process the spinner blade of high speed rotating and the gap that surrounds between the housing seal face that belongs to stator of rotor keep ground less usually.This point existing problems because spinner blade can be when height be attached to not only because thermal load and since centrifugal force extend in radial direction, and the usually only very little thermal expansion of experience of housing, and and then the housing periphery to become large amplitude very little.Therefore, gap size is transformable in gas turbine operation.
In order to consider that these gap sizes change (US4,299,865) known so-called abrasion sealings (abradable seals).At this, the blade apical segment of rotor is made by a kind of mechanically resistant material or is had hard coat, and abrasion sealing or the running in seal section of institute (Einlaufdichtung) of stator is soft on every side.Under various running status, point of blade may occur and enter into seal stator section, and the material of sealing may occur wearing away, and can damaged blade.
Summary of the invention
The object of the present invention is to provide a kind of method that starts described type, the method can apply in mode simple and with low cost a wearing course (abradable seal), and is particularly suited for upgrading in the maintenance of internal combustion turbine or maintenance process or changing the rotor/stator sealing.
Propose according to the present invention, when seal section during being arranged in the turbine housing parts under the confined state, apply ceramic layer.
At first used in the present invention several terms are made an explanation.
Internal combustion turbine is a kind of fluid machinery, wherein can change the heat energy of the high temperature gas flow that produces by burning hydrocarbon or other motor spirit into mechanical energy.The present invention especially can be used for jet engine or the turboprop engine of aircraft.
The gas turbine component that the rotor/stator sealing moves relative to each other in sealing in rotatablely moving toward each other, especially can with respect to around the turbine housing circumference come the point of blade of canned rotor.
In the content of claim 1, term " turbine housing parts " refers to have or the fixing turbine components that surrounds the seal stator section of rotor.Relate in particular within the scope of the invention a kind of jet engine module, wherein arrange seal stator section.
Seal section is arranged on the interior week of turbine housing parts.Term " seal section " refers to parts detachable or that can change separately, and these parts are the sub-fraction in interior week of lining-up turbine housing respectively.A plurality of seal sections extend at the whole circumference of turbine housing parts, and jointly consist of seal stator section.
Seal section has trim, relates to those towards the face of rotor.According to the present invention, ceramic layer is applied on these trims.Within the scope of the invention, term " ceramic layer " all material that refers to have the stupalith composition and be fit to form so-called abrasion sealing.These ceramic layers are usually all based on ZrO 2, Al 2O 3And so on material and/or other metal oxide, transition metal oxide or rare earth oxide or mixed oxide.
According to the present invention, when seal section is being positioned at the turbine housing parts under the confined state among during, apply ceramic layer.This means, when seal section under the confined state, namely with during the turbine housing parts have formed the trim that the whole circumference at the turbine housing parts extends with being connected, apply ceramic layer.
Under confined state, carry out coating and have series of advantages.Only internal combustion turbine or jet engine must be disassembled to module layer on the one hand, needn't be expended ground and and then may produce into this locality and disassemble to the part layer.On the other hand under confined state when module layer carries out coating, can apply from the beginning unified in other words same (einheitlich) smooth ceramic layer on circumference.When usually being the part coating by prior art, because error is inevitable in subsequently fitting tight section process, on the circumferential direction of seal section adjacent one another are on transition or splicing position discontinuity can appear, thereby usually need to repair (for example grinding), with for the manufacture of trim smooth on whole circumference.In the prior art, must with thicker wearing course in other words running-in layer (Einlaufschicht) be applied on each seal section, in order to there are enough materials can be for requisite accurate grinding after the assembling.This point expends, and can raise the cost.In addition, needed thicker ceramic layer is easy to material and peels off in the prior art.
Alternatively in the prior art, may also will consider the discontinuity of trim on the whole circumference of stator, and armoring spinner blade tip may be cut among the ceramic layer when running of an engine first.So need again here thicker, the above-mentioned ceramic layer that peels off simplification arranged.
According to the present invention, particularly preferably apply ceramic layer by atmospheric plasma spraying (atmospheric plasma spray, APS).When plasma spraying, use beam-plasma, produce the heat energy of beam-plasma by the gaseous plasma that produces before compound.Material to be applied is joined in the beam-plasma as powder.Carrying out material in the atmospheric plasma spraying in common ambient atmosphere applies.Use the atmospheric plasma spraying as the method that is used for applying ceramic layer, it has special advantage: will be not usually very large turbine housing parts transfer in controlled normal atmosphere, for example vacuum chamber.The ceramic layer quality that can obtain in the atmospheric plasma spraying is enough to easily be used for according to purpose of the present invention.
The turbine housing parts of repeatedly having mentioned according to the inventive example as being the so-called high-pressure turbine shield stand of jet engine (High Pressure Turbine Shroud Support/HPT Shroud Support).According to the present invention may be good sealing function or the acquisition of less sealing-gap, especially can significantly improve the efficient of pressure turbine and and then fuel saving.The ceramic layer that applies according to the present invention preferably has 10 to 40Vol.-%, more preferably 20 to 30Vol.-% porosity.This porosity helps enough flexibly to form ceramic layer, and so that ceramic layer has so-called antiwear characteristic.Contact with this ceramic layer if spinner blade is most advanced and sophisticated, then in the following manner designing material pair or friction pair namely only or are mainly denuded the ceramic layer trim, and wearing and tearing can not occur or only occur wearing and tearing on a small quantity on point of blade.
In order to realize this porosity, but the stupalith that applies is applying the material that preferably contains some heat abstraction constantly.Described material especially can be a kind of polymkeric substance, for example polyester." but heat abstraction " means: when input heat energy, this material can disappear from ceramic layer to noresidue most of or fully, and stays the cavity of well format at this., in the situation of gaseous decomposition product volatilization, can realize removing by evaporation, distillation, thermolysis or burning.
The stupalith of ceramic layer for example can be based on ZrO 2(zirconium dioxide) can utilize rare-earth oxide, for example Y 2O 3Perhaps other oxide compound mixes.The ceramic powder that is suitable for spraying for example can be based on YSZ (Yttria stabilized Zirconia (yttrium stable zirconium oxide)), and containing weight percent is 3 to 9%, be preferably 4 to 6% polyester, to be used for making the porosity of hope.Applicable powder for example can be bought the product that name is called Metco 2460NS from Sulzer Metco company.
According to the present invention, the thickness of the ceramic layer that applies can be between 0.1 to 0.7mm, more preferably between 0.1 to 0.5mm.Usually apply the coating of thickness in 0.2 to 0.4 or 0.2 to 0.3mm scope.
Within the scope of the invention, preferably before applying ceramic layer, the adhesive promoter layer is applied on the base material of seal section.The thickness of adhesive promoter layer is preferably 0.1mm or less.Described adhesive promoter layer is the MCrAlY layer preferably, and wherein M preferably is selected from a kind of metal or its composition of nickel, cobalt, iron group.Other element, for example hafnium or silicon can be added as so-called reactive element additive, in order to improve scale resistance and the work-ing life of adhesive promoter layer (Bond Coat).Equally preferably apply the adhesive promoter layer by plasma spraying.In case of necessity, can use vacuum plasma spray coating (low vacuum plasma spray, LVPS), however the atmospheric plasma spraying that preferred use has been stated.The material that is applicable to the adhesive promoter layer for example is equally can be from the particulate powders based on CoNiCrALY, for example Amdry 365-2 of Sulzer Metco company acquisition.
In the trim of the seal section (so-called HPT Shroud) of pressure turbine, usually there is cooling air hole, in order to reduce the thermal load of HPT Shroud.Within the scope of the invention advantageously: the described cooling air hole of sealing before applying ceramic layer and possible adhesive promoter layer or other layer, block or be not reduced with not allowing in cross section to prevent cooling air hole.According to a kind of flexible program of the present invention, before applying ceramic layer (and preferred also before applying adhesive promoter layer or other possible middle layer) but temporarily seal these cooling air holes with the material of heat abstraction." but heat abstraction " means: applying ceramic layer and repairing (such as grinding etc.) and afterwards, can by the thermal load that occurs at that time this material be removed by thermal treatment or when turbine turns round first.Particularly can become preferred gaseous decomposition product to carry out heat abstraction by evaporation, distillation or thermolysis.The preferred complete or most of noresidue of this heat abstraction realizes.
But the material of heat abstraction is polymkeric substance or plastics preferably.Preferably, utilize monomer, oligopolymer and/or be used for subsequently that the prepolymer of sclerosis forms, still unhardened mixture seals cooling air hole.According to the present invention, can or preferably bring out sclerosis by light or ultraviolet radiation by heat.UV cured or the photo-hardening plastics of preferred use more preferably use acrylate and/or methacrylic ester.For example can be epoxy acrylate, urethane acrylate, polyester acrylate, polyether acrylate and organic silicon acrylic ester.Corresponding photo-hardening plastics are familiar with by those skilled in the art.Preferably, be designed for viscosity and the characteristic of the still unhardened mixture of sealing cooling air hole, thereby can apply reliably viscose glue, and it can or can only not flowed away in acceptable mode before sclerosis.For example can applicable plastics or tackiness agent have been bought from the Dymax Europe GmbH company in Frankfort.
Sealed cooling air hole according to the present invention before applying ceramic layer, this has been avoided under the prior art condition after applying ceramic layer usually necessity to expend ground auger and has opened cooling air hole.This mode with the cooling air hole sealing is particularly advantageous aspect of the present invention; the applicant also requires this point is protected in case of necessity in the content of the explanation of the seal section that each is taken apart, and it no longer is in the turbine housing parts under confined state.
In addition, theme of the present invention is: a kind of to gas turbine rotor/seal stator section, be arranged in the turbine housing parts on week the method that places under repair of the trim of seal section, may further comprise the steps:
A) provide the turbine housing parts that are disassembled, wherein seal section is arranged in the turbine housing parts under confined state,
B) material of the trim of removal seal section,
C) apply ceramic layer by each described method in the claim 1 to 12.
In addition, another theme of the present invention is: the method that is used for repairing internal combustion turbine, described internal combustion turbine have at least one rotor and rotor/stator sealing, be arranged in the seal section on week in the turbine housing parts, wherein between the trim of most advanced and sophisticated at spinner blade under the new state of described internal combustion turbine and described seal section, sealing-gap is set, said method comprising the steps of:
A) dismounting described internal combustion turbine and the turbine housing that is disassembled parts are provided, wherein said seal section is positioned under confined state among the described turbine housing parts,
B) material of the trim of the described seal section of removal,
C) apply ceramic layer by each described method in the claim 1 to 12, thereby form than the less sealing-gap of sealing-gap under new state.
According to these two aspects of the present invention, relate generally to a kind of repair method, wherein again make pointedly trim.The general character of claim 13 and 14 described repair methods is, places under repair at the turbine housing module layer, needn't continue to disassemble into part, and especially seal section is under the confined state.In addition, according to institute of the present invention, remove material from the trim of seal section, thereby realized that enough spaces are used for again applying ceramic layer according to method of the present invention.
According to another aspect of the present invention, before the method for executive basis invention, turbine housing parts or the internal combustion turbine repaired have metallic sealing section, neither ceramic seal face that apply according to the present invention, neither other type.According to another aspect of the present invention (the feature c of claim 14)), when placing under repair according to the present invention, make the sealing-gap less than the sealing-gap in the new state of internal combustion turbine.Therefore relate to a kind of method that can be used to improve gas turbine proficiency here.This point wherein should reduce fuel consumption and the CO of aircraft engine being importance of the present invention aspect the so-called Green Aviation (green aviation) 2Discharging.Below also will elaborate this aspect of the present invention.
Can use in internal combustion turbine according to repair method of the present invention, this internal combustion turbine has the ceramic seal face under new state, and wherein stipulates: the spinner blade tip can enter into these trims and cause abrasion of materials under some running status.When using the ceramic seal face, the point of blade of turbine vane has armor or usually based on the armor of cubic boron nitride (CBN) in the prior art.When using the ceramic layer that applies according to the present invention, then do not need this armor.
Equally also have the jet engine (for example General Electric CFM56 and CF6-80) that is used for aircraft, it has metallic sealing section.For these engines, should avoid by accurate control geometrical shape and manufacturing and assembling error: when first running-in or after a while when operation, rotor tip contacts with metallic sealing section.In order under all running statuses, reliably to avoid in these undesirable abrasion, usually need larger sealing-gap, can reduce the efficient of engine by the sealing gap.
According to the present invention, in this internal combustion turbine with metallic sealing section, also can ceramic layer be applied on the trim according to the described repair method of claim 14.Can completely or partially remove metallic sealing section in the method, thereby be used for applying the ceramic seal face according to the present invention in the sufficient space that provides in interior week of corresponding turbine housing parts.This ceramic seal face can so design and apply so that sealing-gap after ressembling internal combustion turbine less than the sealing-gap under the new state with metallic sealing section.Can reduce sealing-gap, because when applying the ceramic seal face according to the present invention, can allow that then point of blade enters into trim.This when entering in other words running-in when occuring, because it is secondary to enter into the material of point of blade of soft ceramic layer, therefore only denude this ceramic layer.If in metallic sealing section, when the undesirable operation state, point of blade does not enter into metallic sealing section in accordance with regulations, may also abrasion of materials can appear so on the spinner blade tip, thereby so that sealing-gap continues change greatly, and can not make it come back to the size of initial specification by repairing trim again.
When implementing the method according to this invention, use the atmospheric plasma spraying to have the smaller advantage of technological temperature.Since beam-plasma only with fewer thermal energy transfer to the seal section for the treatment of coating, therefore can avoid the possible distortion of built-up member generation.As following also will explain in an embodiment, module is rotated with the seal section that assembles, thereby beam-plasma is fewer for the action time of each seal section, and corresponding seal section continues can cool off during the rotation in module, and after this it contacts with beam-plasma again.
Description of drawings
Below embodiments of the invention will be described with reference to the accompanying drawings.Wherein show:
Fig. 1 shows the sectional view of internal combustion turbine section;
Fig. 2 shows the vertical view of turbine housing;
Fig. 3 shows the interaction of be in operation turbine vane and trim;
Fig. 4 is schematically illustrated in the procedure of processing when implementing according to of the present invention the repairing;
Fig. 5 is schematically illustrated in the operation when removing seal face materials in the set-up procedure of the inventive method;
Fig. 6 has schematically shown coating process of the present invention;
Fig. 7 show according to the present invention possible reduce sealing-gap;
Fig. 8 shows the characteristic that the rotor/stator sealing according to the present invention structure is in operation.
Embodiment
Fig. 2 shows turbine housing 1 with vertical view, arranges the admittance section 2 that is used for seal section 3 in the interior week of turbine housing.The seal section 3 of splicing has trim 4 at its radially inner periphery mutually on the circumference of turbine housing 1.
In Fig. 1, schematically shown the rotationally symmetric axis of internal combustion turbine with Reference numeral 5.On rotor disk 6, at circumference a plurality of turbine blades 7 (spinner blade or rotating vane) are set with distributing.The radially outer tip of turbine blade 7 seals with respect to the trim 4 of seal section 3, and surrounds sealing-gap 8 with it, and the sealing gap can be calculated by stator radius 9 and the difference of rotor radius 10.The air flow line of internal combustion turbine is flow through in arrow 11 expressions.
Fig. 3 a also shows the original state shown in Fig. 1.Seal section 3 has metallic sealing section in this embodiment.Cooling air hole in the Reference numeral 13 mark seal sections 3.
In engine operation, may be owing to causing turbine blade 7 to enter among the trim of seal section 3 with the rotor eccentricity square shown in 12 among thermal expansion and/or Fig. 3 b.By described enter in seal section 3, to form enter groove 14 shown in Fig. 3 c, and blade length 15 can reduce because of the abrasion of materials on turbine blade 7 tips.Form the sealing-gap 8a that increases; The efficient of engine reduces.
Fig. 4 has schematically shown the flow process according to repair method of the present invention.Fig. 4 a shows the original state of seal section 3 before repairing, and has wherein usually denuded a certain amount of trim 4, also may exist in case of necessity do not illustrate among Fig. 4 a enter groove (referring to the Reference numeral 14 among Fig. 3 c).
Occur under the confined state of seal section in turbine housing 1 in the whole repair procedures shown in Fig. 4, shown in Figure 2 such as it.For clarity, in Fig. 4, only show a unique seal section.
Fig. 5 has schematically shown from the trim 4 of seal section 3 and has removed material.For this purpose, grinding tool 15 can lean against on the trim 4 and rotate.Substitute grinding, also can use other removal method, for example milling or corrosion.In Fig. 4 b, schematically shown the effect that material is removed.
Then clean trim to be applied 4, cleaning preferably includes oil removing, uses deionized water (VE-wasser) flushing, and is for example carrying out drying under 120 ℃ of temperature, carries out in case of necessity drying under the condition of the air pressure that reduces.
Plasma-coated in order to prepare, implement so-called activation sandblast (Aktivierungsstrahlen).For this purpose, use the Al of 36 orders (Mesh) granularity 2O 3Sand-blast material.Following sandblast parameter is applicable to activate sandblast:
15 rev/mins of speed of rotation, twice vertical stroke, spraying pressure 1.6bar, nozzle distance 200mm, 45 ° of spray angles.Should avoid sand-blast material to enter among the cooling air hole 13 at this.
In Fig. 4 c, schematically show the active layer that is applied with 16.
Have greater than 0.2 or the ceramic layer of the bed thickness of 0.3mm if apply, usually should compatibly temporarily seal cooling air runner 13.For this purpose, perhaps point-like ground is by pipette or similarly apply utensil, the film of perhaps assisting, for example having the respective cut that basically conforms to cooling air hole by the mark of moulding, to be applied to based on the photo-hardening plastics of PU on the aperture of each cooling air hole 13, follow by light, ultraviolet radiation and/or heat so that plastic hardening.The plastic plug 17 with 13 sealings of cooling air runner that obtains schematically showing among Fig. 4 d.
In next step, be applied to the adhesive promoter layer 18 that schematically shows among Fig. 4 e.For this purpose, spray to apply particulate powders (Amdry 365-2) based on CoNiCrALY by atmospheric plasma.Fig. 6 schematically shows: the coated elements 19 with beam-plasma 20 is how by carrying out coating with respect to turbine housing 1 motion to the whole circumference of the trim 4 of seal section 3.Use following coating parameter:
1 stroke, the vertical speed of 3.6% robot, 27 rev/mins of speed of rotation.The thickness of the adhesive promoter layer that applies is preferably 0.03 to 0.05mm.
In the situation of using ceramic powder, for example Praxair 1484, can optionally corrosion resistant ceramic inter-layer be applied on the adhesive promoter layer.
Then utilize coated elements 19 to apply according to soft ceramic layer of the present invention (wearing course), in Fig. 4 f, schematically show this layer with 21.
Use Metco 2460NS as coated material.Use following coating parameter:
The 2mm single nozzle, 9 strokes, the vertical speed of 1.8% robot, 33 rev/mins of speed of rotation, 90 ° of spray angles.Usually apply ceramic layer 21 with 0.2 to 0.7mm thickness.
In next step, the trim 4 of seal section 3 is ground to required stator radius.At this, can remove may be because trim 4 irregularity degreees that plastic plug 17 causes, for example material projection.After grinding, plastic plug 17 is protruding to trim 4 shown in Fig. 4 g.
Perhaps by independent thermal treatment, perhaps when engine turns round first so that plastic plug 17 decomposes, and essentially no residually from cooling air hole 13 with its removal.Fig. 4 h has schematically shown the state that can put into operation of manufacturing like this.
Fig. 7 shows: may reduce sealing-gap according to the present invention, thereby improve the efficient of jet engine in the framework of so-called green aviation.Fig. 7 a shows turbine blade 7 with respect to the virgin state of metallic sealing section 4 runnings of seal section 3.Need larger sealing-gap 8, therefore leakage flow and loss in efficiency can occur.
Fig. 7 b shows according to method of the present invention and applies porous ceramic layer 21 state afterwards.Because it is about the porosity of 30Vol.-%, so this coating is soft.Here can reduce sealing-gap 8b with respect to original state.For example sealing-gap 8 can be in 0.5 to 2mm the order of magnitude, and the value of the sealing-gap 8b that reduces can be reduced to 0.1 to 0.4mm, preferred 0.1 to 0.3mm, more preferably 0.1 to 0.2mm.For example in the pressure turbine of engine, sealing-gap has been reduced 0.2mm, thus can be so that motor spirit consumption and CO 2Reducing exhaust emission about 0.3%.
Fig. 8 has schematically shown: turbine blade 7 may enter into the trim 4 of seal section 3 in running of an engine.Formed again among Fig. 8 b the groove that enters with 14 marks at this.Because this enters groove and is formed in the soft ceramic layer 21, therefore can the generating material abrasion on the tip of turbine blade 7 or the abrasion of materials amount few, thereby its radical length 15 is remained unchanged substantially.

Claims (15)

1. one kind is used for ceramic layer (21) is applied to method on the trim (4) of the seal section (3) on the interior week rotor/stator sealing, that be arranged in turbine housing parts (1) of internal combustion turbine, it is characterized in that, when described seal section (3) during being arranged in described turbine housing parts (1) under the confined state, apply described ceramic layer (21).
2. method according to claim 1 is characterized in that, applies described ceramic layer (21) by atmospheric plasma spraying (APS).
3. method according to claim 1 and 2 is characterized in that, described ceramic layer (21) has 10 to 40Vol.-%, preferred 20 to 30Vol.-% porosity.
4. method according to claim 3 is characterized in that, described porosity is caused by the composition of the material that a part in the stupalith that applies can be removed.
5. method according to claim 4 is characterized in that, the material of energy heat abstraction is a kind of polymkeric substance, preferred polyester.
6. each described method in 5 according to claim 1 is characterized in that the stupalith of described ceramic layer contains ZrO 2
7. each described method in 6 according to claim 1 is characterized in that, the thickness of the ceramic layer that is applied in (21) is 0.1 to 0.7mm, preferred 0.1 to 0.5mm.
8. each described method in 7 according to claim 1 is characterized in that, before applying described ceramic layer, applies adhesive promoter layer (18).
9. method according to claim 8 is characterized in that, described adhesive promoter layer (18) has a kind of material based on CoNiCrAlY.
10. according to claim 8 or 9 described methods, it is characterized in that the thickness of described adhesive promoter layer (18) is 0.1mm or less.
11. each described method in 10 according to claim 1, it is characterized in that, apply described adhesive promoter layer (18) so and/or ceramic layer (21) before, utilize a kind of material (17) that can heat abstraction to seal the cooling air hole (13) that is present in the described trim (4).
12. method according to claim 11, it is characterized in that, described material (17) that can heat abstraction is a kind of plastics, UV cured or photo-hardening plastics preferably, further preferred acrylate plastics and/or the methacrylic ester plastics of using are more preferably the plastics that are selected from the group that is comprised of epoxy acrylate, urethane acrylate, polyester acrylate, polyether acrylate and organic silicon acrylic ester.
13. the method that the trim that is used for the seal section on the interior week rotor/stator sealing, that be arranged in the turbine housing parts of internal combustion turbine places under repair may further comprise the steps:
A) provide the turbine housing parts (1) that are disassembled, wherein said seal section (3) is arranged in described turbine housing parts (1) under confined state,
B) remove the material of the trim (4) of described seal section (3),
C) apply ceramic layer (21) by each described method in the claim 1 to 12.
14. method that is used for repairing internal combustion turbine, described internal combustion turbine has at least one rotor (6,7) and the rotor/stator sealing, be arranged in the seal section (3) on interior week of turbine housing parts (1), wherein between the trim (4) of most advanced and sophisticated at spinner blade under the new state of described internal combustion turbine and described seal section (3), sealing-gap (8) is set, said method comprising the steps of:
A) dismounting described internal combustion turbine and the turbine housing parts that are disassembled (1) are provided, wherein said seal section (3) is positioned under confined state among the described turbine housing parts (1),
B) remove the material of the trim (4) of described seal section (3),
C) apply ceramic layer (21) by each described method in the claim 1 to 12, thereby form than the less sealing-gap (8b) of sealing-gap (8) under new state.
15. according to claim 13 or 14 described methods, it is characterized in that the described seal section (3) of the turbine housing parts (1) that provide in a) in step has metallic sealing section (4).
CN2010800589980A 2009-12-23 2010-12-06 Method for producing a rotor/stator seal of a gas turbine Pending CN102985582A (en)

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DE102009060570.3 2009-12-23
DE102009060570A DE102009060570A1 (en) 2009-12-23 2009-12-23 Method for producing a rotor / stator seal of a gas turbine
PCT/EP2010/068948 WO2011076549A1 (en) 2009-12-23 2010-12-06 Method for producing a rotor/stator seal of a gas turbine

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