CN106637030A - Thermal barrier coating stripping method and thermal barrier coating repair method - Google Patents
Thermal barrier coating stripping method and thermal barrier coating repair method Download PDFInfo
- Publication number
- CN106637030A CN106637030A CN201510713943.3A CN201510713943A CN106637030A CN 106637030 A CN106637030 A CN 106637030A CN 201510713943 A CN201510713943 A CN 201510713943A CN 106637030 A CN106637030 A CN 106637030A
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- China
- Prior art keywords
- thermal barrier
- barrier coating
- masking
- undercoating
- cooling holes
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Classifications
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- 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
- C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
- B24B1/00—Processes of grinding or polishing; Use of auxiliary equipment in connection with such processes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention provides a thermal barrier coating stripping method and a thermal barrier coating repair method. According to the present invention, the thermal barrier coating stripping method is used for a gas turbine member, wherein a cooling hole is formed on a member main body, and a thermal barrier coating comprising an outer coating and an inner coating is formed on the surface of the member main body; and the thermal barrier coating stripping method comprises: a local outer coating stripping process (S11), wherein at least the outer coating around the cooling hole is stripped through machining treatment; a shielding process (S12), wherein the part being subjected to outer coating stripping in the local outer coating stripping process is shielded; a main outer coating stripping process (S13), wherein the outer coating is stripped through sand blasting treatment after the shielding process; and an inner coating stripping process (S2), wherein the inner coating is striped through machining treatment after the main outer coating stripping process.
Description
Technical field
The present invention relates to a kind of thermal barrier coating stripping means and thermal barrier coating method for repairing and mending.
Background technology
The various gas turbine components for protecting gas turbine are needed from the high-temperature gas in gas turbine
Impact.Therefore, the various technologies used in gas turbine component.For example, to such as movable vane, quiet
Leaf is so exposed to the component in the burning gases of high temperature, and on the surface of member body thermal boundary is implemented with
Coating (Thermal Barrier Coating：TBC).Also, in order to protect such component from
The impact of the burning gases of high temperature, is provided with for blowing out on the blade body of the turbo blade of component
The Cooling Holes of cooling air.
TBC processes over time and corroded by the burning gases of high temperature, it is therefore desirable to repaired.
Repair by first peeling off the TBC for generating erosion etc., then apply TBC again and carry out.
In the past, for example in the case of stator blade, form what is be made up of alloy on the surface of blade body
Undercoating and the external coating that is made up of barrier materials such as ceramics are used as TBC.And, peeling off TBC
In the case of, first external coating is peeled off by sandblasting, then pass through pickling and be made up of alloy to peel off
Undercoating (patent document 1).
Citation
Patent document 1：Japanese Unexamined Patent Publication 2008-240563 publications
However, Cooling Holes are formed with the surface of blade body, therefore in the stripping of conventional TBC
In operation, in pickling, solvent is entered inside blade body, and accessory is deteriorated because of solvent, therefore is needed
Pull down the accessory inside blade body.Furthermore, it is desirable to carry out the cleaning of the solvent used in pickling,
The post processing of solvent.So, the stripping process of conventional TBC needs multiple treatment process.
The content of the invention
It is an object of the invention to provide a kind of compared with the past thermal barrier coating is peeled off short-term is interior
Stripping means.
For solving the scheme of problem
First method is related to a kind of thermal barrier coating stripping means, its be be formed with member body it is cold
But hole and being formed with the surface of the member body applies with external coating and internally coated thermal boundary
The thermal barrier coating stripping means of the gas turbine component of layer, wherein, the thermal barrier coating stripping means is held
The following operation of row：Local external coating stripping process, is peeled off at least described cold by machining processes
But the external coating around hole；Masking operation, to peeling off in the local external coating stripping process
Implement masking in the position of the external coating；Main external coating stripping process, after the masking operation,
The external coating is peeled off by blasting treatment；And undercoating stripping process, in the main external coating
After stripping process, the undercoating is peeled off by machining processes.
In the thermal barrier coating stripping means, the solvent of pickling will not be entered inside gas turbine component,
Therefore, it is possible to omit the operation related to pickling such that it is able in the interior stripping for realizing thermal barrier coating of short-term
From.
Based on second method thermal barrier coating stripping means in the first way, wherein, outside the local
The machining processes of coating stripping operation are bonded-abrasive working process.
In the thermal barrier coating stripping means, abrasive particle is fixed on the mother metal of grinding tool, therefore, it is possible to anti-
Only abrasive particle is entered inside gas turbine component from Cooling Holes.
Based on Third Way thermal barrier coating stripping means in a second manner, wherein, the fixed mill
Grain working process be using the process of grinder, and in the bonded-abrasive working process with the table
The radius of curvature in face matchingly changes the grinding part of the grinder.
In the thermal barrier coating stripping means, turbine component can be ground using the planar portions of grinder
Member body surface, therefore, it is possible to prevent the damage on the surface for being excessively ground the member body for causing
Wound.
In fourth way, after the main external coating stripping process and the undercoating stripping process
Before, the masking removing step for removing the masking is performed.
In the thermal barrier coating stripping means, the undercoating around Cooling Holes in undercoating stripping process
Also peel off, therefore, it is possible to prevent the internally coated remaining around Cooling Holes.
Based on 5th mode thermal barrier coating stripping means in the first way, wherein, carry out tempering face
Color process, so as to peel off the undercoating of the remaining, is made in temper color process by heat treatment
The undercoating discoloration of remaining in undercoating stripping process.
In the thermal barrier coating stripping means, the undercoating of remaining is peeled off, therefore, it is possible to reduce undercoating
Remaining.
Based on 6th mode thermal barrier coating stripping means in the first way, wherein, the combustion gas wheel
Mechanism member is stator blade.
In the thermal barrier coating stripping means, by the thermal barrier coating for peeling off stator blade, can protect and be easy to
It is exposed to impact of the stator blade in the burning gases of high temperature from the burning gases of high temperature.
7th mode is related to a kind of thermal barrier coating method for repairing and mending, and it is on the surface of the member body
The thermal barrier coating for being formed with the gas turbine component with external coating and internally coated thermal barrier coating is repaiied
Compensating method, wherein, the thermal barrier coating method for repairing and mending performs following operation：Appoint in the first to six mode
Thermal barrier coating stripping means described in one；Masking pin insertion operation, is implementing the thermal barrier coating stripping
After method, by the masking pin insertion Cooling Holes；Thermal barrier coating formation process, in the masking
After pin insertion operation, on the surface of the member body thermal barrier coating is formed；And masking pin goes
Except operation, after the thermal barrier coating formation process, the masking pin is removed.
In the thermal barrier coating method for repairing and mending, thermal barrier coating is formed to Cooling Holes insertion masking pin, because
Even if this implements thermal barrier coating can also readily insure that the opening of Cooling Holes.
Eighth mode based on the thermal barrier coating method for repairing and mending of the 7th mode, wherein, in the masking
In pin removing step, the masking pin ashing is made by heat treatment.
In the thermal barrier coating method for repairing and mending, it is ashed masking pin, therefore, it is possible to simply remove masking
Pin.
9th mode based on the thermal barrier coating method for repairing and mending of the 7th mode, wherein, it is described masking pin
For the elastomer of silicon class.
The thermal barrier coating method for repairing and mending can be embedded in Cooling Holes in adeciduate mode and sealing is high,
On the other hand, can be simply ashed.
Invention effect
In a mode of the present invention, the solvent of pickling will not be entered inside gas turbine component, because
This can omit the operation related to pickling, can be in the interior stripping for realizing thermal barrier coating of short-term.
Description of the drawings
Fig. 1 is the schematic sectional view of the gas turbine of embodiment involved in the present invention.
Fig. 2 is the major part stereogram of the stationary blade row of embodiment involved in the present invention.
Fig. 3 is the stereogram of the stator blade of embodiment involved in the present invention.
Fig. 4 is the side view of the insert (insert) of embodiment involved in the present invention.
Fig. 5 is the V-V line sectional views of Fig. 3.
Fig. 6 is the repair procedure of the repair procedure to reference example and embodiment involved in the present invention
The explanatory diagram being compared.
Fig. 7 is the stereogram (one) of the mending course of the stator blade of embodiment involved in the present invention.
Fig. 8 is the stereogram (its two) of the mending course of the stator blade of embodiment involved in the present invention.
Fig. 9 is the flow chart of the stripping process of the thermal barrier coating of embodiment involved in the present invention.
Figure 10 is the major part section view of the mending course of the stator blade of embodiment involved in the present invention
Figure (one).
Figure 11 is the major part section view of the mending course of the stator blade of embodiment involved in the present invention
Figure (its two).
Figure 12 is the major part section view of the mending course of the stator blade of embodiment involved in the present invention
Figure (its three).
Figure 13 is the major part section view of the mending course of the stator blade of embodiment involved in the present invention
Figure (four).
Figure 14 is the major part section view of the mending course of the stator blade of embodiment involved in the present invention
Figure (its five).
Figure 15 is the use of the explanation of the overburden operation of the grinder of embodiment involved in the present invention
Figure.
Figure 16 is the use of the undesirable stripping of the grinder of embodiment involved in the present invention and makees
The explanatory diagram of industry.
Description of reference numerals：
10 gas turbines
20 compressors
30 burners
40 turbines
41 turbine rotors
42 armature spindles
43 stationary blade rows
431 first fixed blade rings
44 stator blades
441 first stator blades
44a blade parts
Guard ring on the outside of 44b
44c inner sides guard ring
44d Cooling Holes
44f undercoating
44g external coatings
44h blade bodies
44s surfaces
45 turbine rooms
46 rotating blade rows
47 movable vanes
48 inserts
48a Cooling Holes
48b ends
Inside 48c
49 segmentation rings
50 masking pins
50a leading sections
50b bottoms
50c is not inserted into part
50d bottom surfaces
60 adhesives
70 grinders
71 grinding parts
71a planar portions
71b ends
Specific embodiment
Hereinafter, embodiment involved in the present invention is illustrated with reference to Fig. 1～Figure 16.
First, the structure of the stator blade of turbo blade is illustrated.
As shown in figure 1, the gas turbine 10 of present embodiment possesses：Compressor 20, it is to air
It is compressed；Burner 30, it utilizes fuel to give birth in the combustion synthesis in air compressed by compressor 20
Into burning gases G；And turbine 40, it is driven by burning gases G.
Compressor 20 is had the compressor drum pivoted about with axis A and covers compression
The compressor room of machine rotor.Turbine 40 has：With the turbine rotor that axis A is pivoted about
41st, the turbine room 45 and multiple stationary blade rows 43 of turbine rotor 41 are covered.Compressor drum and whirlpool
Wheel rotor 41 forms gas turbine rotor, and is connected with generator GEN.
Turbine rotor 41 has the armature spindle 42 extended on axis direction Da and installed in this turn
Multiple rotating blade rows 46 on sub- axle 42.Multiple rotating blade rows 46 are arranged on axis direction Da.It is each dynamic
Blade row 46 is provided with the multiple movable vanes 47 arranged on the circumferential Dc of armature spindle 42.In multiple movable vanes
The upstream of the axis direction Da of row 46 is provided with stationary blade row 43.Each stationary blade row 43 is arranged on turbine room
45 inner side.Each stationary blade row 43 is provided with the multiple stator blades 44 arranged on circumferential Dc.Also,
The part that turbine 40 possesses the outer circumferential side of the movable vane 47 on the stream to burning gases G delimited
Segmentation ring 49.It should be noted that axis direction Da refers to the direction that axis A extends, week
The circumference of axis A is referred to Dc.
As shown in Fig. 2 stationary blade row 43 has multiple stator blades 44, stationary blade row 43 in circumferential Dc over-assembles
It is monolithically fabricated as ring-type.Each stator blade 44 possesses outside guard ring 44b, the turbine rotor of the side of turbine room 45
The inner side guard ring 44c of 41 sides and the blade part across outside guard ring 44b and inner side guard ring 44c
44a。
Fig. 3 illustrates the detailed construction of stator blade 44.Multiple Cooling Holes 44d are formed with blade part 44a.
In the inside of stator blade 44, the insert 48 being inserted and fixed shown in Fig. 4.On insert 48
It is formed with the multiple Cooling Holes 48a for discharging cooling air C.
Cooling air C is directed into first the inside 48c of insert 48 from the end 48b of insert 48.
Fig. 5 illustrates the V-V sectional views of Fig. 3.As shown in figure 5, being directed into the inside 48c of insert 48
Cooling air C by being discharged from Cooling Holes 48a, (the punching so as to being cooled down from inside stator blade 44
Hit cooling；impingement cooling).Meanwhile, from the cooling air C that Cooling Holes 48a is discharged
Discharge from the Cooling Holes 44d formed on blade part 44a, cooled down from outside stator blade 44.It is logical
Cross such cooling to protect stator blade 44 from the hot impact of burning gases.
As shown in figure 5, stator blade 44 has metal blade body 44h, in blade body 44h
Surface 44s on be formed with the TBC44e comprising external coating 44g and undercoating 44f (thermal boundary apply
Layer).
By forming undercoating 44f between the surface 44s and external coating 44g of blade body 44h,
So as to relax the coefficient of thermal expansion differences between the surface 44s of blade body 44h and external coating 44g.It is logical
The mitigation of coefficient of thermal expansion differences is crossed, the stripping of external coating 44g can be suppressed.Undercoating 44f is metal
Binder course, such as alloy comprising Co, Ni, Cr, A1Y etc..Undercoating 44f is by spraying spray
Apply material and formed.
External coating 44g is layered on the surface of undercoating 44f.External coating 44g is by will be containing leading
The low ceramic sprayed on material of hot coefficient is sprayed on the surface of undercoating 44f and is formed.For example, outward
Coating 44g by the mixed-powder that toner is mixed with ceramic powders by being sprayed on undercoating 44f
Above formed.
TBC44e processes over time and burned gas G corrodes, it is therefore desirable to carry out TBC44e
Repairing.Especially as shown in figure 1, due to the temperature of burning gases G it is high, therefore in stator blade 44
In, the first stator blade 441 closest to the first fixed blade ring 431 of burner 30 is most vulnerable to erosion,
Therefore need to carry out the repairing of TBC44e.
Hereinafter, the method for repairing and mending of above-mentioned TBC44e is illustrated.
The repair procedure and repair procedure as a reference example of embodiments of the present invention are shown in Fig. 6.
In the repair procedure of reference example, after unloading the accessory inside the grade of insert 48 stator blade 44, lead to
Cross blasting treatment to peel off external coating 44g, undercoating 44f is peeled off by pickling.Next, right
The defect of weld part etc. is repaired, and is sequentially formed on the surface 44s of blade body 44h again new
Undercoating 44f and external coating 44g, so as to form TBC44e.Then, it is diffused hot place
After reason is as Ageing Treatment, installation fitting.
In the repair procedure of reference example, in blasting treatment, sand-blast material enters in meditation from Cooling Holes 44d
Inside leaf 44, it is therefore desirable to pull down the accessory inside stator blade 44.In addition, in the patcher of reference example
In sequence, in pickling, solvent is entered to inside stator blade 44, it is therefore desirable to pull down matching somebody with somebody inside stator blade 44
The accessory deteriorated because of solvent in part.And it is further desired that the solvent used in cleaning pickling.So,
The repair procedure of reference example is elongated during needing multiple treatment process, repairing required.
In the repair procedure of present embodiment, external coating 44g is peeled off by blasting treatment and (is applied outward
Layer sandblasting stripping process：S1), undercoating 44f is peeled off by bonded-abrasive processing, and (undercoating is shelled
From operation：S2), TBC44e is thus peeled off.It should be noted that now, accessory is not removed.
Here, bonded-abrasive processing is referred to using the grinding tool that abrasive particle is fixed with instrument mother metal
Processing.If peeling off undercoating 44f by bonded-abrasive processing, because abrasive particle is fixed on instrument mother
Material, thus abrasive particle will not from Cooling Holes enter gas turbine component inside.
Then, the defect of weld part etc. is repaired in the same manner as the repair procedure of reference example and (is repaired
Operation：S3), on the surface 44s of blade body 44h new undercoating 44f is sequentially formed again
And external coating 44g, so as to form TBC44e (coating operations：S4).Next, being diffused
Heat treatment is used as Ageing Treatment (diffusion heat treatments operation：S5).
The detailed content of external coating sandblasting stripping process S1 is shown in Fig. 7～Fig. 9.
In external coating sandblasting stripping process S1, as pre-treatment, as shown in Figure 7, for example, pass through
The bonded-abrasives such as milled processed are processed, and the scope stripping to about 10mm around Cooling Holes 44d is outer
Coating 44g (local external coating stripping process：S11).It should be noted that the reticulate pattern portion of Fig. 7 shows
Go out to have peeled off the part of external coating 44g.Then, as shown in figure 8, covering to Cooling Holes 44d
(masking operation：S12).The masking of Cooling Holes 44d is by the position for having peeled off external coating 44g
Cooling Holes 44d on paste masking tape M that is made up of plastics or stationery to carry out.Then, to leaf
The surface 44s of piece main body 44h overall external coating 44g carries out blasting treatment, peels off external coating 44g
(main external coating stripping process：S13).In the outer of the surface 44s entirety for having peeled off blade body 44h
After coating 44g, masking tape M (masking removing step is peeled：S14).
Therefore, in the external coating stripping process S11 of local, do not pass through to fix by blasting treatment
Abrasive machining peeling off the external coating 44g around Cooling Holes 44d, therefore, it is possible to suppress sand-blast material,
Abrasive particle is entered inside stator blade 44.
In addition, in main external coating stripping process S13, covering Cooling Holes 44d and carrying out at sandblasting
Reason, therefore, it is possible to suppress the sand-blast material when external coating 44g is peeled off to enter inside stator blade 44.
After masking tape M is peeled, in undercoating stripping process S2, such as by milled processed
Process to peel off the surface including the blade body 44h including around Cooling Holes 44d Deng bonded-abrasive
44s overall undercoating 44f.
Therefore, in the repair procedure of present embodiment, undercoating is peeled off by bonded-abrasive processing
44f, do not exist carries out the situation of pickling as the repair procedure of reference example, therefore, it is possible to omit with
The relevant operation of pickling, and solvent can be suppressed to enter the situation inside stator blade 44.In addition,
Stripping undercoating 44f after masking tape M is peeled, therefore, it is possible to peel off comprising around Cooling Holes 44d
Undercoating 44f is in the surface 44s of interior blade body 44h overall undercoating 44f.
As described above, in the stripping means of the TBC44e of present embodiment, it is suppressed that sand-blast material,
The situation that abrasive particle and the solvent of pickling are entered inside stator blade 44.Therefore, it is possible to omit and stator blade 44
The operation for pulling down correlation of internal accessory, can peel off at short notice compared with reference example
TBC44e。
Next, being described in detail to coating operation S4 and diffusion heat treatments operation S5.
In coating operation S4, masking pin (masking pin) is inserted respectively to multiple Cooling Holes 44d
50 (masking pin insertion operations：S41), sequentially form on the surface 44s of blade body 44h again
Undercoating 44f and external coating 44g (thermal barrier coating formation process：S42).Finally, by doubling as
Diffusion heat treatments operation S5 of masking pin removing step is come to blade body 44h implement heat treatments,
Carry out being ashed masking pin 50 while Ageing Treatment, so as to remove masking pin 50.
Figure 10～Figure 14 illustrates the main portion sectional view of the mending course of stator blade, and illustrates and blade
The sectional view in the surface 44s of main body 44h vertical direction.
Masking pin 50 used in masking pin insertion operation S41 is tapered in the material by silicon class of shape
The elastomer that material is constituted.In the present embodiment, using the screening of cone shape as shown in Figure 10
Cover pin 50.
In masking pin insertion operation S41, relative to the surface 44s of blade body 44h, from masking
The less leading section 50a of diameter of pin 50 inserts Cooling Holes 44d by pin 50 is covered.Masking pin 50
For elastic component, with cone shape, therefore Cooling Holes are pressed into by the way that pin 50 will be covered in insertion
44d, easily can be embedded in masking pin 50 in the way of not coming off from Cooling Holes 44d.Figure 10 shows
Go out the state that masking pin 50 is embedded in adeciduate mode for Cooling Holes 44d.
In masking pin insertion operation S41, by the way that pin 50 will be covered from the little leading section 50a of diameter
Insertion, so as to improve sealing of the masking pin 50 to Cooling Holes 44d.Therefore, in thermal barrier coating shape
Into in operation S42, the situation of the filmogen of TBC44e into Cooling Holes 44d can be suppressed.If
Suppress entrance of the filmogen to Cooling Holes 44d, then it is easy to ensure that thermal barrier coating formation process S42
Cooling Holes 44d afterwards.If in addition, suppressing entrance of the filmogen to Cooling Holes 44d, can press down
Membrane material is made to the entrance inside stator blade 44, can omit and be pulled down with the accessory inside stator blade 44
Related operation, can repair at short notice compared with reference example to TBC44e.
Also, in external coating sandblasting stripping process S1, the undercoating stripping process S2 of present embodiment
And in coating operation S4, sand-blast material, the solvent of pickling and filmogen will not enter in meditation
Inside leaf 44.Related operation is pulled down therefore, it is possible to omit to the accessory inside stator blade 44, with
Reference example is compared can be repaired at short notice to TBC44e.
In masking pin insertion operation S41, before masking pin 50 is inserted into Cooling Holes 44d,
Coating adhesive 60 on the side of masking pin 50.By coating adhesive 60, can be by masking pin
50 are fixed on Cooling Holes 44d in adeciduate mode, can further improve the 50 pairs of coolings of masking pin
The sealing of hole 44d.
(Figure 10) is projected in the bottom 50b of masking pin 50 from the surface 44s of blade body 44h
In the case of, as shown in figure 11, using the cut-out such as scissors, pocket knife part 50c is not inserted into.Now,
The surface 44s for making the bottom surface 50d and blade body 44h of the masking pin 50 occurred due to cut-out is total to
Face.Figure 11 illustrates that the surface 44s of the bottom surface 50d and blade body 44h that make masking pin 50 is coplanar
State.
In masking pin insertion operation S41, cut-out masking pin 50 be not inserted into part 50c after,
The surface 44s of the blade body 44h of the bottom surface 50d comprising masking pin 50 is carried out at sandblasting
Reason.Compared with the surface 44s of blade body 44h, the bottom surface 50d for covering pin 50 is easier because of spray
Sand is processed and is ground, therefore as shown in figure 12, the masking pin 50 occurred due to blasting treatment
Surface 44ss of the bottom surface 50d than blade body 44h it is low.
By making surface 44ss of the bottom surface 50d of masking pin 50 than blade body 44h low, in thermal boundary
In coating formation process S42, the film forming for being prevented from Cooling Holes 44d peripheries is uneven such that it is able to
Form uniform TBC44e.
Compared with the surface 44s of blade body 44h, the surface more light of the bottom surface 50d of pin 50 is covered
It is sliding, therefore, it is difficult to attachment TBC44e.Accordingly, it is difficult to TBC44e is formed on the 50d of bottom surface, because
This can suppress the blocking of the Cooling Holes 44d that the film forming of TBC44e causes.
Here, in the case of being formed with a small amount of TBC44e on the 50d of bottom surface and forming film, with
The thickness of the surface 44s of blade body 44h is compared, in the masking pin 50 for having carried out blasting treatment
The thickness of the film formed on the 50d of bottom surface is very thin, forms the low film of rigidity.By in diffusion heat treatments
Masking pin 50 is removed in operation S5, so as to simultaneously the low film of the rigidity is removed with masking pin 50.
Therefore, in diffusion heat treatments operation S5, the film formed on the 50d of bottom surface is removed, therefore
The opening of Cooling Holes 44d is able to maintain that, the blocking of the Cooling Holes 44d that film forming causes can be suppressed.
In addition, it is low that bottom surface 50d is processed as into surface 44s than blade body 44h, and suppress to hide
The film forming of the bottom surface 50d of pin 50 to surface is covered, so as to after thermal barrier coating formation process S42,
Can make masking pin 50 bottom surface 50d film formation surface relative to blade body 44h surface 44s
Film formation surface depression.By make masking pin 50 bottom surface 50d film formation surface relative to blade master
The film formation surface depression of the surface 44s of body 44h, is able to confirm that the trace of the bottom surface 50d of masking pin 50
Mark.Therefore, after thermal barrier coating formation process S42, even if TBC44e is thickening, it is also possible to bright
Really determine position, size, the shape of Cooling Holes 44d corresponding with the bottom surface 50d of masking pin 50,
Therefore it is easy to ensure that Cooling Holes 44d.
After masking pin 50 is removed in diffusion heat treatments operation S5, in the inwall of Cooling Holes 44d
On be attached with undercoating 44f, the filmogen of external coating 44g, but the filmogen adhered on inwall
Amount it is few, therefore after diffusion heat treatments operation S5, can easily implement Cooling Holes 44d's
Guarantee.Therefore, only it is capable of achieving Cooling Holes 44d really by removing the filmogen adhered on inwall
Protect, it is not necessary to enter eleven punch 11, therefore, it is possible to the expansion of the Cooling Holes 44d for causing that prevents from boring a hole.
Figure 13 illustrates the bottom 50b in cut-out masking pin 50 and after carrying out blasting treatment, in heat
In barrier coating formation process S42, interior painting is sequentially formed on the surface 44s of blade body 44h again
Pattern after layer 44f and external coating 44g.Blade body during TBC44e is formed by spraying
The temperature of the surface 44s of 44h is about 200 DEG C.The elastomer being made up of the material of silicon class is led in this way
Key is made up of siloxanes key, the wire condensate on side switch with organic substituents such as methyl, phenyl
The silicon rubber of composition.The heat resisting temperature of the elastomer being made up of the material of silicon class is more than 200 DEG C, because
This masking pin 50 will not be ashed in the formation of TBC44e, not fall off and maintain sealing.
In diffusion heat treatments operation S5, by heat treatment masking pin 50 is ashed.Using by
In the case of the present embodiment of the elastomer that the material of silicon class is constituted, can by 850 DEG C, 11.5
Hour heat treatment condition realizing good ashing, but as long as being more than 300 DEG C of heat treatment condition
Just can be ashed, as long as the condition that can be ashed, then can use arbitrary heat treatment condition.Figure
14 are illustrated and are heat-treated by diffusion heat treatments operation S5, the sample after being ashed masking pin 50
State.Although the masking pin 50 after being ashed by heat treatment is able to maintain that shape, it is unable to maintain that just
Property, so as to defeated and dispersed into powder.
When thermal barrier coating formation process S42 is implemented, not only the surface 44s of blade body 44h, hides
At least a portion for covering the bottom surface 50d of pin 50 is also covered by TBC44e.If the bottom surface of masking pin 50
50d is covered by TBC44e, then at least a portion for covering the bottom surface 50d of pin 50 is blocked, from
And masking pin 50 cannot be extracted.However, by covering the implement heat treatment of pin 50, so as to cover pin
50 ashing, therefore, it is possible to more simply remove masking pin 50.
It should be noted that in the local external coating stripping process S11 of external coating sandblasting stripping process S1
In, in the case where external coating 44g is peeled off by grinder 70, as shown in figure 15, using grinding
Planar portions 71a in the grinding part 71 of grinding machine 70 are being ground external coating 44g.As shown in figure 16,
The end 71b in the grinding part 71 of grinder 70 is not used to be ground external coating 44g.By not making
External coating 44g is ground using planar portions 71a with end 71b, excessively grinding is prevented from and is caused
Blade body 44h surface 44s damage.In addition, being ground by using planar portions 71a outer
Coating 44g, can carry out the stripping of uniform external coating 44g.
In undercoating stripping process S2, include around Cooling Holes 44d at 70 Duis by grinder
In the case where overall undercoating 44f of the surface 44s of interior blade body 44h is peeled off,
Similarly it is ground undercoating 44f using planar portions 71a.In being ground by using planar portions 71a
Coating 44f, it is the damage of the surface 44s for being prevented from excessively being ground the blade body 44h for causing, cold
But the deformation of the shape of hole 48a.
The surface 44s of blade body 44h has a concaveconvex shape, thus with the concaveconvex shape of surface 44s
Radius of curvature matchingly select grinding part 71 planar portions 71a size.
Specifically, using the little grinding part 71 of the size of planar portions 71a to surface 44s in it is recessed
The external coating 44g of the little part of the radius of curvature of convex form, undercoating 44f are ground.Conversely,
Using curvature half of the big grinding part 71 of the size of planar portions 71a to the concaveconvex shape in the 44s of surface
The external coating 44g of the big part in footpath, undercoating 44f are efficiently ground.
In this case, selected and table by changing the grinding part 71 of grinder 70
The size of planar portions 71a that the radius of curvature of the concaveconvex shape of face 44s matches.
Therefore, by matchingly selecting grinding part with the radius of curvature of the concaveconvex shape of surface 44s
The size of 71 planar portions 71a, so as to will not be to the table of the blade body 44h with concaveconvex shape
Face 44s is excessively ground, and external coating 44g, undercoating 44f efficiently can be peeled off.
In the case where abrasive machining is fixed, it is also possible to which on one side pair dust for adding man-hour is blown on one side
It is fixed abrasive machining.By blowing while be fixed abrasive machining, dust is prevented from
Invade from Cooling Holes 44d to the inside of blade body 44h.
In addition, after abrasive machining is fixed, if being blown, being prevented from blade body
The dust on the surface of 44h, the attachment of the dust of Cooling Holes 44d inwalls.By preventing blade body 44h
Surface dust attachment, can well carry out the masking based on masking tape M.In addition, logical
The attachment of the dust for preventing Cooling Holes 44d inwalls is crossed, can be carried out well based on masking pin 50
Masking.
In addition, in undercoating stripping process S2, it is also possible to after undercoating 44f is peeled off, lead to
Cross 700 DEG C, the heat treatment of 1 hour carry out temper color (heat tint) and process (discoloration heat),
The undercoating discoloration of remaining is made, undercoating 44f is peeled off again.Changed colour simultaneously by making the undercoating of remaining
Peeled off, undercoating 44f of remaining can be peeled off.
Also, the lift-off processing of temper color process and undercoating 44f can also be repeated.It is logical
The lift-off processing that temper color process and undercoating 44f is repeated is crossed, can be reduced as far as
The undercoating of remaining.
More than, embodiments of the present invention have been described in detail referring to the drawings, but specific structure
Above-mentioned embodiment is not limited to, the design alteration being also contained in the range of the purport without departing from the present invention
Deng.
It should be noted that in the present embodiment, the thermal barrier coating stripping means of stator blade 44 is set to,
But not limited to this, as long as the gas turbine component being an exposure in the burning gases of high temperature, then can answer
For the thermal barrier coating stripping means of arbitrary gas turbine component.For example, it is also possible to be applied to
Cooling Holes, the movable vane 47 of TBC, the thermal barrier coating stripping means of segmentation ring 49.
In addition, in the present embodiment, do not pull down accessory and carry out the stripping of thermal barrier coating, but not
Need to omit and when pulling down relevant operation of accessory, it is also possible to as the repair procedure of reference example,
Pulling down carries out again the stripping of thermal barrier coating after accessory, then the accessory of removal and installation again.
In addition, in the present embodiment, in the external coating stripping process S11 of local by grinding at
Manage to peel off the external coating 44g around Cooling Holes 44d, but as long as being bonded-abrasive processing, can make
With arbitrary process.As long as and removing material does not enter Cooling Holes 44d, it is possible to use arbitrary machine
Tool working process is peeled off.
Equally, in the present embodiment, in undercoating stripping process S2 also by milled processed this
The bonded-abrasive of sample is processed to peel off undercoating 44f, but as long as removing material does not enter Cooling Holes, can
With using arbitrary machining processes.
Also, Cooling Holes 44d in the present embodiment, is peeled off in external coating sandblasting stripping process S1
The external coating 44g of surrounding, but it is also possible in the lump peel off undercoating 44f around Cooling Holes 44d.
In this case, masking tape M is not peeled in undercoating stripping process S2, masking can be being kept
Undercoating 44f is peeled off in the state of Cooling Holes 44d.Therefore, grind in undercoating stripping process S2
Cutting material, sand-blast material will not enter Cooling Holes 44d, therefore can also use removing material, sandblasting
Material is likely to enter the lift-off processing of Cooling Holes 44d.
In addition, in the present embodiment using the masking pin 50 with cone shape, but as long as being energy
It is enough to make masking pin 50 to be embedded in by way of not coming off from Cooling Holes 44d being pressed into Cooling Holes 44d
Shape, then can have any shape.If such as Cooling Holes are circle, as long as at least the one of masking pin
Part is the shape of the part with truncated cone-shaped, then can make masking pin 50 with not from cold by pressing
But the mode that hole 44d comes off is embedded in.
In addition, in the present embodiment masking pin is removed by heat treatment, but as long as heat can formed
After barrier coating remove, it is also possible to formed thermal barrier coating after pull up masking pin and remove etc., do not carry out heat
Process and remove after heat coating.
Masking pin removing step can also be set outside diffusion heat treatments operation S5.In this case,
For example can arrange after thermal barrier coating formation process S42 and before diffusion heat treatments operation S5
The operation for removing masking pin by heat treatment is used as masking pin removing step.But, if as this enforcement
Mode like that by as masking pin removing step in the way of implement diffusion heat treatments operation S5, then with point
Open up and put diffusion heat treatments operation and compare with the situation of masking pin removing step, can apply short-term is interior
Plus thermal barrier coating.
Industrial applicibility
A mode of the invention, can be in the interior stripping for realizing thermal barrier coating of short-term.
Claims (9)
1. a kind of thermal barrier coating stripping means, it is Cooling Holes to be formed with member body and in institute
State and the combustion gas wheel with external coating and internally coated thermal barrier coating is formed with the surface of member body
The thermal barrier coating stripping means of mechanism member, wherein, the thermal barrier coating stripping means performs following operation：
Local external coating stripping process, is peeled off around at least described Cooling Holes by machining processes
The external coating；
Masking operation, the position to having peeled off the external coating in the local external coating stripping process
Implement masking；
Main external coating stripping process, after the masking operation, is peeled off described by blasting treatment
External coating；And
Undercoating stripping process, after the main external coating stripping process, by machining processes
To peel off the undercoating.
2. thermal barrier coating stripping means according to claim 1, wherein,
The machining processes of the local external coating stripping process are bonded-abrasive working process.
3. thermal barrier coating stripping means according to claim 2, wherein,
The bonded-abrasive working process be using the process of grinder, and the bonded-abrasive processing
The grinding part of the grinder is matchingly changed in process with the radius of curvature on the surface.
4. thermal barrier coating stripping means according to claim 1, wherein,
After the main external coating stripping process and before the undercoating stripping process, removal is performed
The masking removing step of the masking.
5. thermal barrier coating stripping means according to claim 1, wherein,
Temper color process is carried out, so as to peel off the undercoating of the remaining, at the temper color
The undercoating discoloration of the remaining in the undercoating stripping process is made in reason by heat treatment.
6. thermal barrier coating stripping means according to any one of claim 1 to 5, wherein,
The gas turbine component is stator blade.
7. a kind of thermal barrier coating method for repairing and mending, it is Cooling Holes to be formed with member body and in institute
State and the combustion gas wheel with external coating and internally coated thermal barrier coating is formed with the surface of member body
The thermal barrier coating method for repairing and mending of mechanism member, wherein, the thermal barrier coating method for repairing and mending performs following operation：
Thermal barrier coating stripping means any one of claim 1 to 6；
Masking pin insertion operation, after the thermal barrier coating stripping means is implemented, by masking pin insertion
The Cooling Holes；
Thermal barrier coating formation process, after the masking pin insertion operation, in the member body
Thermal barrier coating is formed on surface；And
Masking pin removing step, after the thermal barrier coating formation process, removes the masking pin.
8. thermal barrier coating method for repairing and mending according to claim 7, wherein,
In the masking pin removing step, the masking pin ashing is made by heat treatment.
9. thermal barrier coating method for repairing and mending according to claim 7, wherein,
The masking pin is the elastomer of silicon class.
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| CN201510713943.3A CN106637030A (en) | 2015-10-28 | 2015-10-28 | Thermal barrier coating stripping method and thermal barrier coating repair method |
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| CN201510713943.3A CN106637030A (en) | 2015-10-28 | 2015-10-28 | Thermal barrier coating stripping method and thermal barrier coating repair method |
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| CB02 | Change of applicant information |
Address after: Kanagawa Prefecture, Japan Applicant after: Mitsubishi Power Co., Ltd Applicant after: MITSUBISHI HEAVY INDUSTRIES DONGFANG GAS TURBINE (GUANGZHOU) Co.,Ltd. Address before: Kanagawa Prefecture, Japan Applicant before: MITSUBISHI HITACHI POWER SYSTEMS, Ltd. Applicant before: MITSUBISHI HEAVY INDUSTRIES DONGFANG GAS TURBINE (GUANGZHOU) Co.,Ltd. |
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Application publication date: 20170510 |
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