Repairing method for aero-engine single crystal turbine blade thermal barrier coating ceramic layer and application of repairing method

Abstract

The invention discloses a repairing method for a ceramic layer of a thermal barrier coating of a single-crystal turbine blade of an aero-engine and application of the repairing method, and belongs to the technical field of aero-engine hot end component thermal barrier coating repairing. The repairing method comprises the following steps that the turbine blade is pretreated; the blade back is subjected to rapid sand blasting according to an S shape under 0.07-0.13 MPa to remove a ceramic layer; the blade basin is subjected to rapid sand blasting at the pressure of 0.17 MP-0. 2 MPa according to an S shape to remove a ceramic layer at a time; the ceramic layer is removed through rapid sand blasting under the pressure of 0.07 MPa to 0.13 MPa of the margin plate; the blade basin is subjected to rapid sand blasting again at the pressure of 0.07 MPa-0. 13 MPa according to an S shape to remove a ceramic layer for the second time; the turbine blade is subjected to nondestructive testing after being cleaned and dried; and carrying out ceramic layer re-preparation on the turbine blade which is qualified through nondestructive testing. According to the repairing method, the ceramic layer can be accurately controlled to be removed, the aluminide diffusion coating cannot be excessively thinned, the repairing method can be continuously used, and the blade repairing period is remarkably shortened.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of thermal barrier coating repair of hot end components of an aero-engine, and particularly relates to a repair method for a ceramic layer of a thermal barrier coating of a single-crystal turbine blade of an aero-engine and application thereof. BACKGROUND

[0002] The application of a thermal barrier coating to a hot end component such as a turbine blade of an aero-engine can improve the temperature resistance of the turbine blade, and the thermal barrier coating is composed of a metal bonding layer and a ceramic top layer. After the turbine blade is used for a period of time, the peeled ceramic top layer needs to be repaired, that is, the ceramic top layer is removed and then recoated.

[0003] During the operation of the turbine blade, a thermal growth oxide layer is formed at the interface between the metal bonding layer and the ceramic top layer, which hinders the further diffusion of oxygen and provides oxidation protection for the hot end component. During the operation of the engine, high-temperature combustion gas acts on the blade basin of the turbine blade and is discharged from the exhaust edge to flow to the next stage of blade, and therefore, the blade basin and the blade back of the turbine blade are in different heating states. Although the blade basin is cooled by a gas film, the ambient temperature thereof during use is also much higher than that of the blade back. The growth of the thermal growth oxide layer is affected by temperature, so that the growth states of the thermal growth oxide layers at the blade basin and the blade back are different. For the same used blade, the oxide layer can be clearly seen after the ceramic top layer is removed at the blade basin, and the oxidation at the blade back is relatively light. The in-situ formation of the thermal growth oxide layer at the interface between the metal bonding layer and the ceramic top layer can improve the bonding between the bonding layer and the ceramic top layer to a certain extent, but also brings difficulties to the accurate removal of the ceramic layer during repair. It is difficult to remove the ceramic top layer by using a conventional mechanical method (such as a physical method of sandblasting), and if the ceramic layer at different positions of the turbine blade is removed by using the same process parameters, the thickness of the remaining metal bonding layer will be inevitably affected. In addition, for a single-crystal superalloy blade, recrystallization of the substrate will occur, which is not conducive to the continued use of the blade. Therefore, there is an urgent need to develop a ceramic layer repair method which can effectively reduce the influence on the metal bonding layer to ensure that the thermal barrier coating can be normally used after repair. SUMMARY

[0004] In view of the problems in the prior art, the present application aims to provide a repair method for a ceramic layer of a thermal barrier coating of a single-crystal turbine blade of an aero-engine, which removes the ceramic layer by using different processes according to the heating characteristics of the turbine blade during use, slows down the influence of the coating removal process on the metal bonding layer and the single-crystal superalloy, retains as much metal bonding layer as possible, plays the protection performance of the aluminide diffusion coating bonding layer, and ensures that the blade can continue to be used after the ceramic layer is recoated, thereby saving maintenance costs and saving repair cycles.

[0005] The purpose of the present application is achieved by the following technical solutions:

[0006] In a first aspect, the application provides a method for repairing a ceramic layer of a thermal barrier coating of a single crystal turbine blade of an aero-engine, wherein a metallic bonding layer of the thermal barrier coating is an aluminide diffusion coating, and the ceramic layer of the thermal barrier coating is coated on the surface of the aluminide diffusion coating by an electron beam physical vapor deposition method, and the method comprises the following steps:

[0007] Turbine blade pretreatment: cleaning the turbine blade to remove impurities, and then drying;

[0008] Ceramic layer removal from the back of the blade: protecting the tenon, rim plate and blade basin of the single crystal turbine blade with the metallic bonding layer being an aluminide diffusion coating, and then removing the ceramic layer from the back of the blade by rapid sandblasting under S type 0.07 MPa-0.13 MPa;

[0009] First ceramic layer removal from the blade basin: protecting the back of the blade, and then removing the ceramic layer from the blade basin by rapid sandblasting under S type 0.17 MP-0.2 MPa;

[0010] Ceramic layer removal from the rim plate: protecting the blade body, and then removing the ceramic layer from the rim plate by rapid sandblasting under 0.07 MPa-0.13 MPa;

[0011] Second ceramic layer removal from the blade basin: protecting the back of the blade and the rim plate from which the ceramic layer has been removed, and then removing the ceramic layer from the blade basin by rapid sandblasting under S type 0.07 MPa-0.13 MPa again;

[0012] Turbine blade cleaning: cleaning the turbine blade with the aluminide diffusion coating after the ceramic layer is removed;

[0013] Turbine blade drying;

[0014] Turbine blade non-destructive testing;

[0015] Ceramic layer re-preparation: preheating the blade from which the ceramic layer is removed and which passes the non-destructive testing in an electron beam physical vapor deposition device, and after the blade is uniformly heated, oxygen is introduced to form a pure oxide film on the surface of the aluminide diffusion coating, and then a ceramic surface layer is deposited to form a new thermal barrier coating of the turbine blade.

[0016] Further, the aluminide diffusion coating is one of an aluminized coating, a platinum electroplated aluminized coating, an aluminized silicon coating or an aluminized chromium coating, and the aluminide diffusion coating is vacuum diffused after the elements are infiltrated, and the thickness of the aluminide diffusion coating is 20-50 μm.

[0017] Further, in the ceramic layer removal from the back of the blade, the rapid sandblasting time is 2-3 s.

[0018] Further, in the ceramic layer removal from the rim plate, the rapid sandblasting time is 2-3 s.

[0019] Further, the fast sandblasting time for removing the ceramic layer from the leaf basin for the first time is 3s-5s.

[0020] The fast sandblasting time for removing the ceramic layer from the leaf basin for the second time is 2s-3s.

[0021] Further, in the process of removing the ceramic layer from the leaf back, the leaf basin and the edge plate by fast sandblasting, the abrasive is white corundum sand, the sandblasting distance is 80mm-150mm, and the sandblasting angle is 85°-95°; the particle size of the abrasive used for removing the ceramic layer from the leaf basin for the first time is 80 mesh-150 mesh, and the particle size of the abrasive used for removing the ceramic layer from the leaf back, the leaf basin for the second time and the edge plate is 150 mesh-220 mesh.

[0022] Further, the turbine blade cleaning adopts large water flow flushing and ultrasonic cleaning, and the leaf body and the inner cavity of the ceramic layer removed blade are flushed; then the ceramic layer removed blade tenon is placed downward and the blade tip is placed upward in clean water for ultrasonic cleaning.

[0023] Further, the turbine blade drying is to blow dry the water stains on the outer surface and the inner cavity of the ceramic layer removed blade by compressed air, and then the ceramic layer removed blade is placed in a 120℃-200℃ oven for drying for 60min-120min.

[0024] Further, in the ceramic layer re-preparation, the preheating temperature is 900℃-1000℃, and the preheating time is 50min-60min; an electron beam physical vapor deposition process is used to deposit a ceramic surface layer on the surface of the aluminide diffusion coating, the ceramic surface layer presents a columnar crystal structure, and the thickness is 110μm-150μm.

[0025] In the second aspect, the application provides an application of a repair method for the ceramic layer of the thermal barrier coating of the single-crystal turbine blade of the aero-engine, which is used for repairing the thermal barrier coating of the used aero-engine turbine blade or repairing the new product of the thermal barrier coating of the unused aero-engine turbine blade.

[0026] The advantages and effects of the application are as follows:

[0027] 1. Compared with the prior art mechanical method for removing the thermal barrier coating of the blade, the repair method can accurately control the removal of the ceramic layer, will not cause the excessive thinning of the aluminide diffusion coating, and can continue to be used. Moreover, the single-crystal alloy blade substrate is not mechanically treated, the risk of recrystallization is avoided, the blade that passes the nondestructive testing is directly deposited with a ceramic surface layer and then put into use again, and the blade repair period can be significantly shortened.

[0028] 2. Compared with the prior art, the ceramic layer is removed by chemical methods such as alkali boiling, and the ceramic layer is removed only on the surface of the aluminide diffusion coating, and there is no loose corrosion layer formed by the reaction of alkali and the aluminide diffusion coating on the surface of the blade and the aluminide infiltration layer in the cavity, so that the service life of the blade is prolonged and the cost is saved.

[0029] 3. Compared with the prior art, the ceramic layer is removed by sandblasting to avoid the corrosion of the infiltration layer in the cavity of the turbine blade, and different parameters are formulated according to the different characteristics of the oxide growth on the surface of the aluminide diffusion coating after the blade is used, so that the damage of the sandblasting method to the metal bonding layer of the aluminide diffusion coating is controlled, the metal bonding layer is retained as much as possible, the metal bonding layer can still be used after the ceramic layer is removed, and the recrystallization of the single crystal alloy blade is avoided, thereby reducing the influence on the performance of the blade. BRIEF DESCRIPTION OF DRAWINGS

[0030] Figure 1 The scanning electron microscope (SEM) image of the metal bonding layer after the ceramic layer of Example 1 is removed;

[0031] Figure 2 The scanning electron microscope (SEM) image of the thermal barrier coating of the repaired turbine blade of Example 1;

[0032] Figure 3 The scanning electron microscope (SEM) image of the metal bonding layer after the ceramic layer of Comparative Example 1 is removed;

[0033] Figure 4 The scanning electron microscope (SEM) image of the metal bonding layer after the ceramic layer of Comparative Example 2 is removed. DETAILED DESCRIPTION

[0034] The specific embodiments of the present application will be further described in detail below in combination with the drawings and examples.

[0035] A repairing method for the ceramic layer of the thermal barrier coating of an aero-engine single crystal turbine blade, the metal bonding layer of the thermal barrier coating is an aluminide diffusion coating, the aluminide diffusion coating includes but is not limited to one of an aluminizing coating, an electroplated platinum aluminizing coating, an aluminizing silicon coating and an aluminizing chromium coating, and the aluminide diffusion coating is vacuum-diffused after the elements are infiltrated, and the thickness is 20-50 μm; the ceramic layer of the thermal barrier coating is deposited on the surface of the aluminide diffusion coating by electron beam physical vapor deposition, and includes the following steps:

[0036] The turbine blade is cleaned and pretreated, the used turbine blade is cleaned by a hydrocarbon cleaning agent to remove the organic matter on the surface, the new turbine blade is degreased, and then is blown dry;

[0037] Ceramic layer removal on the back of the blade: the edge plate and the blade basin of the turbine blade with aluminide diffusion coating on the metal bonding layer are protected, and then the back of the blade is quickly sandblasted in S shape at a pressure of 0.1 MPa and a time of 2 s-3 s, the abrasive is white corundum sand, the abrasive particle size is 150-220 mesh, the sandblasting distance is 80-150 mm, the sandblasting angle is 85°-95°, and the ceramic layer is removed;

[0038] First ceramic layer removal on the blade basin: the back of the blade is protected, and then the blade basin is quickly sandblasted in S shape at a pressure of 0.2 MPa and a time of 3 s-5 s, the abrasive is white corundum sand, the abrasive particle size is 80-150 mesh, the sandblasting distance is 80-150 mm, the sandblasting angle is 85°-95°, and the ceramic layer is removed;

[0039] Ceramic layer removal on the edge plate: the blade body is protected, and then the edge plate is quickly sandblasted at a pressure of 0.1 MPa and a time of 2 s-3 s, the abrasive is white corundum sand, the abrasive particle size is 150-220 mesh, the sandblasting distance is 80-150 mm, the sandblasting angle is 85°-95°, and the ceramic layer is removed;

[0040] Second ceramic layer removal on the blade basin: the back of the blade and the edge plate with the removed ceramic layer are protected, and then the blade basin is quickly sandblasted in S shape at a pressure of 0.07-0.13 MPa and a time of 2 s-3 s, the abrasive is white corundum sand, the abrasive particle size is 150-220 mesh, the sandblasting distance is 80-150 mm, the sandblasting angle is 85°-95°, and the ceramic layer is removed;

[0041] Turbine blade cleaning: the turbine blade with aluminide diffusion coating after the ceramic layer is removed is subjected to high flow flushing and ultrasonic cleaning, the blade body and the inner cavity of the blade with the removed ceramic layer are flushed for 2-3 min to flush out the residual sand in the inner cavity, and then the floating dust on the surface of the blade body is flushed away; then the blade tenon of the blade with the removed ceramic layer is placed downward and the blade tip is placed upward in clean water, and ultrasonic cleaning is performed at room temperature for 15-30 min;

[0042] Turbine blade drying: the water stains on the outer surface and the inner cavity of the blade with the removed ceramic layer are blown dry by compressed air, and then the blade with the removed ceramic layer is placed in an oven at 120-200°C and dried for 60-120 min;

[0043] Non-destructive testing of the turbine blade is performed;

[0044] Preparation of the ceramic layer: the blade with the removed ceramic layer that passes the non-destructive testing is placed in the sample chamber of the electron beam physical vapor deposition equipment, the vacuum degree of the vacuum chamber reaches 1×10 -3The blade is sent into a vacuum chamber, the blade is heated to 900-1000℃, and the blade is kept for 50-60 min to make the blade evenly heated, oxygen is introduced to make a pure oxide film grow on the surface of the aluminide diffusion coating, and then a ceramic top layer is deposited, the ceramic top layer has a columnar crystal structure and a thickness of 110-150μm, and the turbine blade forms a new thermal barrier coating.

[0045] The application of a repair method for a ceramic layer of a thermal barrier coating of a single crystal turbine blade of an aero-engine, the repair method being used for repairing a used aero-engine turbine blade with a thermal barrier coating or repairing a new unused aero-engine turbine blade with a thermal barrier coating.

[0046] Embodiment 1

[0047] A repair method for a ceramic layer of a thermal barrier coating of a single crystal turbine blade of an aero-engine, a metal bonding layer of the thermal barrier coating being a CrAl permeation coating, vacuum diffusion being performed after element permeation, and the thickness of the metal bonding layer being 40μm; the ceramic layer of the thermal barrier coating being deposited on the surface of the aluminide diffusion coating by electron beam physical vapor deposition, and the method comprising the following steps:

[0048] The turbine blade is cleaned and pretreated, the used turbine blade is cleaned by using a hydrocarbon cleaning agent to remove surface organic matter, and the new unused turbine blade is degreased and then dried;

[0049] Ceramic layer is removed from the blade back: the rim and the blade basin of the turbine blade with the metal bonding layer being the aluminide diffusion coating are protected, then the blade back is quickly sandblasted in an S shape at a pressure of 0.11MPa and a time of 2s, the abrasive is white corundum sand, the abrasive particle size is 180 mesh, the sandblasting distance is 100mm, the sandblasting angle is 90°, and the ceramic layer is removed;

[0050] The blade basin is once removed from the ceramic layer: the blade back is protected, then the blade basin is quickly sandblasted in an S shape at a pressure of 0.18MPa and a time of 4s, the abrasive is white corundum sand, the abrasive particle size is 100 mesh, the sandblasting distance is 100mm, the sandblasting angle is 90°, and the ceramic layer is removed;

[0051] The rim is removed from the ceramic layer: the blade body is protected, then the rim is quickly sandblasted at a pressure of 0.11MPa and a time of 2s, the abrasive is white corundum sand, the abrasive particle size is 180 mesh, the sandblasting distance is 100mm, the sandblasting angle is 90°, and the ceramic layer is removed;

[0052] The blade basin is twice removed from the ceramic layer: the blade back and the rim which have been removed from the ceramic layer are protected, then the blade basin is quickly sandblasted in an S shape at a pressure of 0.11MPa and a time of 2s, the abrasive is white corundum sand, the abrasive particle size is 180 mesh, the sandblasting distance is 100mm, the sandblasting angle is 90°, and the ceramic layer is removed;

[0053] Turbine blade cleaning: the turbine blade with aluminide diffusion coating after removing ceramic layer is washed by large water flow and ultrasonic cleaning, the blade body and inner cavity of the blade with removing ceramic layer are washed for 2 min to flush out the residual sand in the inner cavity and then flush off the floating dust on the surface of the blade body; then the blade with removing ceramic layer is placed in clean water with tenon downward and blade tip upward, and ultrasonic cleaning is performed for 15 min at room temperature;

[0054] Turbine blade drying: the water stains on the outer surface and inner cavity of the blade with removing ceramic layer are blown dry by compressed air, and then the blade with removing ceramic layer is placed in an oven at 200℃ for 60 min;

[0055] Non-destructive testing is performed on the turbine blade;

[0056] Ceramic layer re-preparation: the blade with removing ceramic layer that passes the non-destructive testing is placed in the sample chamber of the electron beam physical vapor deposition equipment, the vacuum degree of the vacuum chamber reaches 1×10 -3 The blade is sent into the vacuum chamber, heated to 1000℃ and kept for 60 min to make the blade evenly heated, oxygen is introduced to make a pure oxide film grow on the surface of the aluminide diffusion coating, and then the ceramic surface layer is deposited, which presents columnar crystal structure and has a thickness of 110μm, and the turbine blade forms a new thermal barrier coating.

[0057] Example 2

[0058] A repairing method for the ceramic layer of the thermal barrier coating of a single crystal turbine blade of an aero-engine, the metal bonding layer of the thermal barrier coating is an Al-infiltrated coating, which is vacuum-diffused after element infiltration and has a thickness of 50μm; the ceramic layer of the thermal barrier coating is deposited on the surface of the aluminide diffusion coating by electron beam physical vapor deposition, and the method comprises the following steps:

[0059] Turbine blade cleaning pretreatment: the used turbine blade is cleaned by a hydrocarbon cleaning agent to remove the surface organic matter, and the new turbine blade is degreased and then blown dry;

[0060] Ceramic layer removal on the blade back: the rim and the bucket of the turbine blade with the metal bonding layer being the aluminide diffusion coating are protected, then the blade back is quickly sandblasted in S shape at a pressure of 0.07MPa and a time of 3s, the abrasive is white corundum sand, the abrasive particle size is 150 mesh, the sandblasting distance is 150mm, and the sandblasting angle is 95° to remove the ceramic layer;

[0061] First ceramic layer removal on the bucket: the blade back is protected, then the bucket is quickly sandblasted in S shape at a pressure of 0.17MPa and a time of 5s, the abrasive is white corundum sand, the abrasive particle size is 150 mesh, the sandblasting distance is 150mm, and the sandblasting angle is 95° to remove the ceramic layer;

[0062] Edge plate ceramic layer removal: the edge plate is protected, then the edge plate is quickly sandblasted at a pressure of 0.07 MPa for 3 s, the abrasive is white corundum sand, the abrasive particle size is 150 mesh, the sandblasting distance is 150 mm, and the sandblasting angle is 95°, and the ceramic layer is removed;

[0063] Secondly, the ceramic layer of the turbine blade is removed: the turbine blade is protected, then the turbine blade is quickly sandblasted at a pressure of 0.07 MPa for 3 s, the abrasive is white corundum sand, the abrasive particle size is 150 mesh, the sandblasting distance is 150 mm, and the sandblasting angle is 95°, and the ceramic layer is removed;

[0064] Turbine blade cleaning: the turbine blade with the aluminide diffusion coating after the ceramic layer is removed is subjected to water flow flushing and ultrasonic cleaning; the blade body and the inner cavity of the turbine blade after the ceramic layer is removed are flushed for 3 min, residual sand in the inner cavity is flushed out, and then floating dust on the surface of the blade body is flushed out; then the turbine blade after the ceramic layer is removed is placed in clean water with the tenon downward and the blade tip upward, and ultrasonic cleaning is performed at room temperature for 30 min;

[0065] Turbine blade drying: the water stains on the outer surface and the inner cavity of the turbine blade after the ceramic layer is removed are blown dry by compressed air, and then the turbine blade after the ceramic layer is removed is placed in an oven at 120℃ and dried for 150 min;

[0066] The turbine blade is subjected to nondestructive testing;

[0067] Preparation of the ceramic layer: the turbine blade after the ceramic layer is removed and the nondestructive testing is qualified is placed in a sample chamber of an electron beam physical vapor deposition device, the vacuum degree of the vacuum chamber reaches 1×10 -3 The turbine blade is heated to 950℃ and kept for 55 min to make the turbine blade evenly heated, oxygen is introduced to make a pure oxide film grow on the surface of the aluminide diffusion coating, and then the ceramic surface layer is deposited, the ceramic surface layer has a columnar crystal structure and a thickness of 120 μm, and the turbine blade forms a new thermal barrier coating.

[0068] Example 3

[0069] A repairing method for a ceramic layer of a thermal barrier coating of a single-crystal turbine blade of an aero-engine, a metal bonding layer of the thermal barrier coating is an electroplated Pt-Al coating, vacuum diffusion is performed after element penetration, and the thickness is 40 μm; the ceramic layer of the thermal barrier coating is deposited on the surface of the aluminide diffusion coating by electron beam physical vapor deposition, and the method comprises the following steps:

[0070] The turbine blade is subjected to cleaning pretreatment, the used turbine blade is cleaned by using a hydrocarbon cleaning agent to remove surface organic matter, the new turbine blade is degreased, and then dried;

[0071] Leaf back ceramic layer removal: the edge plate and the leaf basin of the turbine blade with the metal bonding layer of aluminide diffusion coating are protected, then the leaf back is quickly sandblasted in S shape at a pressure of 0.09 MPa and a time of 2.5 s, the abrasive is white corundum sand, the abrasive particle size is 180 mesh, the sandblasting distance is 100 mm, the sandblasting angle is 90°, and the ceramic layer is removed;

[0072] Leaf basin first ceramic layer removal: the leaf back is protected, then the leaf basin is quickly sandblasted in S shape at a pressure of 0.18 MPa and a time of 4 s, the abrasive is white corundum sand, the abrasive particle size is 100 mesh, the sandblasting distance is 100 mm, the sandblasting angle is 90°, and the ceramic layer is removed;

[0073] Edge plate ceramic layer removal: the blade body is protected, then the edge plate is quickly sandblasted at a pressure of 0.09 MPa and a time of 2.5 s, the abrasive is white corundum sand, the abrasive particle size is 180 mesh, the sandblasting distance is 100 mm, the sandblasting angle is 90°, and the ceramic layer is removed;

[0074] Leaf basin second ceramic layer removal: the leaf back and the edge plate with the removed ceramic layer are protected, then the leaf basin is quickly sandblasted in S shape at a pressure of 0.09 MPa and a time of 2.5 s, the abrasive is white corundum sand, the abrasive particle size is 180 mesh, the sandblasting distance is 100 mm, the sandblasting angle is 90°, and the ceramic layer is removed;

[0075] Turbine blade cleaning: the turbine blade with the removed ceramic layer and the aluminide diffusion coating is subjected to high-flow flushing and ultrasonic cleaning, the blade body and the inner cavity of the turbine blade with the removed ceramic layer are flushed for 2 min to flush out the residual sand in the inner cavity, and then the floating dust on the surface of the blade body is flushed away; then the turbine blade with the removed ceramic layer is placed in clean water with the tenon downward and the blade tip upward, and is subjected to ultrasonic cleaning at room temperature for 20 min;

[0076] Turbine blade drying: the water stains on the outer surface and the inner cavity of the turbine blade with the removed ceramic layer are blown dry by compressed air, and then the turbine blade with the removed ceramic layer is placed in an oven at 150 ℃ and is dried for 60 min;

[0077] Turbine blade non-destructive testing;

[0078] Ceramic layer re-preparation: the turbine blade with the removed ceramic layer and passing the non-destructive testing is placed in a sample chamber of an electron beam physical vapor deposition device, the vacuum degree of the vacuum chamber reaches 1×10 -3 The turbine blade is heated to 1000 ℃ and is kept for 60 min to make the turbine blade evenly heated, oxygen is introduced to make a pure oxide film grow on the surface of the aluminide diffusion coating, and then a ceramic surface layer is deposited, the ceramic surface layer has a columnar crystal structure and a thickness of 110 μm, and the turbine blade forms a new thermal barrier coating.

[0079] Example 4

[0080] A repairing method for a ceramic layer of a thermal barrier coating of a single crystal turbine blade of an aero-engine, a metal bonding layer of the thermal barrier coating is an electroplated Pt-Al coating, vacuum diffusion is carried out after element penetration, and the thickness is 40 μm; the ceramic layer of the thermal barrier coating is deposited on the surface of the aluminide diffusion coating by electron beam physical vapor deposition, and comprises the following steps:

[0081] The turbine blade is cleaned and pretreated, the used turbine blade is cleaned by using a hydrocarbon cleaning agent to remove surface organic matter, and the unused turbine blade is degreased, and then dried;

[0082] The ceramic layer is removed from the back of the blade: the rim and the blade basin of the turbine blade with the metal bonding layer of the aluminide diffusion coating are protected, then the back of the blade is quickly sandblasted in an S shape at a pressure of 0.11 MPa and a time of 2 s, the abrasive is white corundum sand, the abrasive particle size is 220 mesh, the sandblasting distance is 100 mm, the sandblasting angle is 90°, and the ceramic layer is removed;

[0083] The ceramic layer is removed from the blade basin once: the back of the blade is protected, then the blade basin is quickly sandblasted in an S shape at a pressure of 0.2 MPa and a time of 3 s, the abrasive is white corundum sand, the abrasive particle size is 100 mesh, the sandblasting distance is 100 mm, the sandblasting angle is 90°, and the ceramic layer is removed;

[0084] The ceramic layer is removed from the rim: the blade body is protected, then the rim is quickly sandblasted at a pressure of 0.11 MPa and a time of 2 s, the abrasive is white corundum sand, the abrasive particle size is 220 mesh, the sandblasting distance is 100 mm, the sandblasting angle is 90°, and the ceramic layer is removed;

[0085] The ceramic layer is removed from the blade basin twice: the back of the blade and the rim with the removed ceramic layer are protected, then the blade basin is quickly sandblasted in an S shape at a pressure of 0.11 MPa and a time of 2 s, the abrasive is white corundum sand, the abrasive particle size is 220 mesh, the sandblasting distance is 100 mm, the sandblasting angle is 90°, and the ceramic layer is removed;

[0086] The turbine blade is cleaned: the turbine blade with the aluminide diffusion coating after the ceramic layer is removed is washed by a large water flow and ultrasonic cleaning, the blade body and the inner cavity of the turbine blade with the removed ceramic layer are washed for 2 min to wash out the residual sand in the inner cavity, and then the floating dust on the surface of the blade body is washed away; then the blade tenon of the turbine blade with the removed ceramic layer is placed downward, and the blade tip is placed upward in clean water, and ultrasonic cleaning is carried out for 15 min at room temperature;

[0087] The turbine blade is dried: the water stains on the outer surface and the inner cavity of the turbine blade with the removed ceramic layer are blown dry by compressed air, and then the turbine blade with the removed ceramic layer is placed in a 200℃ oven and dried for 60 min;

[0088] The turbine blade is subjected to nondestructive testing;

[0089] Ceramic layer re-preparation: the turbine blade with removed ceramic layer and passed nondestructive testing is placed in the sample chamber of the electron beam physical vapor deposition device, the vacuum chamber is vacuumed to 1x10 -3 The turbine blade is sent into the vacuum chamber, the blade is heated to 1000℃ and kept for 60 min to make the blade evenly heated, oxygen is introduced to make a pure oxide film grow on the surface of the aluminide diffusion coating, then the ceramic surface layer is deposited, the ceramic surface layer has columnar crystal structure and the thickness is 150 μm, and the turbine blade forms a new thermal barrier coating.

[0090] Example 5

[0091] A repairing method for the ceramic layer of the thermal barrier coating of a single crystal turbine blade of an aero-engine, the metal bonding layer of the thermal barrier coating is an Al-infiltrated coating, vacuum diffusion is performed after element infiltration, and the thickness is 20 μm; the ceramic layer of the thermal barrier coating is deposited on the surface of the aluminide diffusion coating by electron beam physical vapor deposition, and the method comprises the following steps:

[0092] The turbine blade is cleaned and pretreated, the used turbine blade is cleaned by using a hydrocarbon cleaning agent to remove surface organic matter, the unused turbine blade is degreased, and then dried;

[0093] Ceramic layer removal of the blade back: the rim and the blade basin of the turbine blade with the metal bonding layer being the aluminide diffusion coating are protected, then the blade back is quickly sandblasted in an S shape at a pressure of 0.13 MPa and a time of 2 s, the abrasive is white corundum sand, the abrasive particle size is 220 mesh, the sandblasting distance is 80 mm, the sandblasting angle is 85°, and the ceramic layer is removed;

[0094] First ceramic layer removal of the blade basin: the blade back is protected, then the blade basin is quickly sandblasted in an S shape at a pressure of 0.2 MPa and a time of 3 s, the abrasive is white corundum sand, the abrasive particle size is 80 mesh, the sandblasting distance is 80 mm, the sandblasting angle is 85°, and the ceramic layer is removed;

[0095] Ceramic layer removal of the rim: the blade body is protected, then the rim is quickly sandblasted at a pressure of 0.13 MPa and a time of 2 s, the abrasive is white corundum sand, the abrasive particle size is 220 mesh, the sandblasting distance is 80 mm, the sandblasting angle is 85°, and the ceramic layer is removed;

[0096] Second ceramic layer removal of the blade basin: the blade back and the rim with the removed ceramic layer are protected, then the blade basin is quickly sandblasted in an S shape at a pressure of 0.13 MPa and a time of 2 s, the abrasive is white corundum sand, the abrasive particle size is 220 mesh, the sandblasting distance is 80 mm, the sandblasting angle is 85°, and the ceramic layer is removed;

[0097] Turbine blade cleaning: the turbine blade with aluminide diffusion coating after removing the ceramic layer is rinsed with a large water flow and ultrasonic cleaning, the blade body and inner cavity of the blade removing the ceramic layer are rinsed for 2 min, the residual sand in the inner cavity is flushed out, and then the floating dust on the surface of the blade body is flushed away; then the blade removing the ceramic layer is placed in clean water with the tenon downward and the blade tip upward, and ultrasonic cleaning is performed at room temperature for 15 min;

[0098] Turbine blade drying: the water stains on the outer surface and inner cavity of the blade removing the ceramic layer are blown dry with compressed air, and then the blade removing the ceramic layer is placed in a 120℃ oven and dried for 120 min; after removing the ceramic layer in this embodiment 1, the morphology of the metal bonding layer is analyzed by SEM, as shown in FIG. 4, it can be seen that the thickness of the metal bonding layer is not obviously thinned, the bonding layer is uniform and continuous, the surface is smooth, and after use, a typical two-phase structure is presented, and the coating surface is slightly contaminated. Figure 1

[0099] Non-destructive testing of turbine blade;

[0100] Ceramic layer re-preparation: the blade removing the ceramic layer that passes the non-destructive testing is placed in the sample chamber of the electron beam physical vapor deposition equipment, the vacuum degree of the vacuum chamber reaches 1×10 -3 The blade is sent into the vacuum chamber, heated to 900℃, preheated for 50 min to make the blade evenly heated, oxygen is introduced to make a pure oxide film on the surface of the aluminide diffusion coating, and then the ceramic surface layer is deposited, the ceramic surface layer presents a columnar crystal structure with a thickness of 110μm, and a new thermal barrier coating is formed on the turbine blade; the structure of the repaired thermal barrier coating is characterized by SEM, as shown in FIG. 6, it can be seen that the thermal barrier coating presents a columnar crystal structure, is continuous and uniform, and the ceramic layer is well combined with the metal bonding layer. Figure 2

[0101] Embodiment 6

[0102] A repair method for the ceramic layer of the thermal barrier coating of a single-crystal turbine blade of an aero-engine, the metal bonding layer of the thermal barrier coating is a CrAl infiltration coating, vacuum diffusion is performed after element infiltration, and the thickness is 40μm; the ceramic layer of the thermal barrier coating is deposited on the surface of the aluminide diffusion coating by electron beam physical vapor deposition, including the following steps:

[0103] Turbine blade cleaning pretreatment: the used turbine blade is cleaned with a hydrocarbon cleaning agent to remove the surface organic matter, and the unused turbine blade is degreased, and then dried;

[0104] Ceramic layer removal on the back of the blade: the edge plate and the blade basin of the turbine blade with the metal bonding layer being an aluminide diffusion coating are protected, then the back of the blade is quickly sandblasted at a pressure of 0.09MPa and a time of 2.5s in an S shape, the abrasive is white corundum sand, the abrasive particle size is 150 mesh, the sandblasting distance is 100mm, and the sandblasting angle is 90°, and the ceramic layer is removed.​​

[0105] The ceramic layer of the blade basin is removed once: the blade back is protected, and then the blade basin is quickly sandblasted in S shape at a pressure of 0.2 MPa and a time of 3 s, the abrasive is white corundum sand, the abrasive particle size is 100 mesh, the sandblasting distance is 100 mm, and the sandblasting angle is 90°, so as to remove the ceramic layer;

[0106] The ceramic layer of the edge plate is removed: the blade body is protected, and then the edge plate is quickly sandblasted at a pressure of 0.09 MPa and a time of 2.5 s, the abrasive is white corundum sand, the abrasive particle size is 150 mesh, the sandblasting distance is 100 mm, and the sandblasting angle is 90°, so as to remove the ceramic layer;

[0107] The ceramic layer of the blade basin is removed twice: the blade back and the edge plate whose ceramic layer has been removed are protected, and then the blade basin is quickly sandblasted in S shape at a pressure of 0.09 MPa and a time of 2.5 s, the abrasive is white corundum sand, the abrasive particle size is 150 mesh, the sandblasting distance is 100 mm, and the sandblasting angle is 90°, so as to remove the ceramic layer;

[0108] The turbine blade is cleaned: the turbine blade with the aluminide diffusion coating after the ceramic layer is removed is subjected to high-flow flushing and ultrasonic cleaning, the blade body and the inner cavity of the blade whose ceramic layer is removed are flushed for 3 min, the residual sand in the inner cavity is flushed out, and then the floating dust on the surface of the blade body is flushed away; then the blade whose ceramic layer is removed is placed in clean water with the tenon downward and the blade tip upward, and is ultrasonically cleaned at room temperature for 20 min;

[0109] The turbine blade is dried: the water stains on the outer surface and the inner cavity of the blade whose ceramic layer is removed are blown dry by compressed air, and then the blade whose ceramic layer is removed is placed in an oven at 150℃ and is dried for 60 min;

[0110] The turbine blade is subjected to non-destructive testing;

[0111] The ceramic layer is prepared again: the blade whose ceramic layer is removed and which passes the non-destructive testing is placed in a sample chamber of an electron beam physical vapor deposition device, the vacuum degree of the vacuum chamber reaches 1×10 -3 The blade is heated to 1000℃ in the vacuum chamber and is kept for 60 min to make the blade evenly heated, oxygen is introduced to make a pure oxide film grow on the surface of the aluminide diffusion coating, and then the ceramic surface layer is deposited, the ceramic surface layer has a columnar crystal structure and a thickness of 150 μm, and the turbine blade forms a new thermal barrier coating.

[0112] Example 7

[0113] A repairing method for a ceramic layer of a thermal barrier coating of a single-crystal turbine blade of an aero-engine, a metal bonding layer of the thermal barrier coating is an Al-Si infiltrated coating, vacuum diffusion is performed after element infiltration, and the thickness is 20 μm; the ceramic layer of the thermal barrier coating is deposited on the surface of the aluminide diffusion coating by electron beam physical vapor deposition, and comprises the following steps:

[0114] Turbine blade cleaning pretreatment, the used turbine blade is cleaned with hydrocarbon cleaning agent, and the surface organic matter is removed. The unused turbine blade is degreased, and then dried;

[0115] S-type ceramic layer removal on the back of the blade: the edge plate and the blade basin of the turbine blade with an aluminide diffusion coating as the metal bonding layer are protected, and then the back of the blade is quickly sandblasted at a pressure of 0.07 MPa and a time of 3 s, the abrasive is white corundum sand, the abrasive particle size is 150 mesh, the sandblasting distance is 150 mm, the sandblasting angle is 95°, and the ceramic layer is removed;

[0116] S-type ceramic layer removal on the back of the blade: the edge plate and the blade basin of the turbine blade with an aluminide diffusion coating as the metal bonding layer are protected, and then the back of the blade is quickly sandblasted at a pressure of 0.07 MPa and a time of 3 s, the abrasive is white corundum sand, the abrasive particle size is 150 mesh, the sandblasting distance is 150 mm, the sandblasting angle is 95°, and the ceramic layer is removed;

[0117] S-type ceramic layer removal on the back of the blade: the edge plate and the blade basin of the turbine blade with an aluminide diffusion coating as the metal bonding layer are protected, and then the back of the blade is quickly sandblasted at a pressure of 0.07 MPa and a time of 3 s, the abrasive is white corundum sand, the abrasive particle size is 150 mesh, the sandblasting distance is 150 mm, the sandblasting angle is 95°, and the ceramic layer is removed;

[0118] S-type ceramic layer removal on the back of the blade: the edge plate and the blade basin of the turbine blade with an aluminide diffusion coating as the metal bonding layer are protected, and then the back of the blade is quickly sandblasted at a pressure of 0.07 MPa and a time of 3 s, the abrasive is white corundum sand, the abrasive particle size is 150 mesh, the sandblasting distance is 150 mm, the sandblasting angle is 95°, and the ceramic layer is removed;

[0119] Turbine blade cleaning: the turbine blade with an aluminide diffusion coating after removing the ceramic layer is subjected to a large water flow flushing and ultrasonic cleaning. The blade body and the inner cavity of the turbine blade after removing the ceramic layer are flushed for 3 min to flush out the residual sand in the inner cavity, and then the floating dust on the surface of the blade body is flushed away. Then the blade tenon of the turbine blade after removing the ceramic layer is placed downward, and the blade tip is placed upward in clean water, and ultrasonic cleaning is performed for 30 min at room temperature;

[0120] Turbine blade drying: the water stains on the outer surface and the inner cavity of the turbine blade after removing the ceramic layer are blown dry by compressed air, and then the turbine blade after removing the ceramic layer is placed in an oven at 120°C and dried for 120 min;

[0121] Turbine blade non-destructive testing;

[0122] Ceramic layer re-preparation: the turbine blade after removing the ceramic layer and passing the non-destructive testing is placed in the sample chamber of the electron beam physical vapor deposition equipment, the vacuum degree of the vacuum chamber reaches 1×10 -3The blade is sent into a vacuum chamber, the blade is heated to 900℃, and the blade is kept for 50 min to make the blade evenly heated. Oxygen is introduced to make a pure oxide film grow on the surface of the aluminide diffusion coating. Then, a ceramic top layer is deposited. The ceramic top layer has a columnar crystal structure and a thickness of 110 μm. The turbine blade forms a new thermal barrier coating.

[0123] Example 8

[0124] A repairing method for a ceramic layer of a thermal barrier coating of a single-crystal turbine blade of an aero-engine, wherein a metal bonding layer of the thermal barrier coating is an AlSi diffusion coating, and the AlSi diffusion coating is vacuum-diffused after element penetration and has a thickness of 50 μm; and the ceramic layer of the thermal barrier coating is deposited on the surface of the aluminide diffusion coating by electron beam physical vapor deposition, and the method comprises the following steps:

[0125] The turbine blade is cleaned and pretreated. The used turbine blade is cleaned by using a hydrocarbon cleaning agent to remove the organic matters on the surface. The unused turbine blade is degreased, and then is blown dry.

[0126] The ceramic layer is removed from the blade back. The rim and the blade basin of the turbine blade with the metal bonding layer being the aluminide diffusion coating are protected, and then the blade back is quickly sandblasted in an S shape at a pressure of 0.13 MPa and a time of 2 s. The abrasive is white corundum sand, the abrasive particle size is 220 mesh, the sandblasting distance is 80 mm, and the sandblasting angle is 85°. The ceramic layer is removed.

[0127] The ceramic layer is removed from the blade basin in one time. The blade back is protected, and then the blade basin is quickly sandblasted in an S shape at a pressure of 0.2 MPa and a time of 3 s. The abrasive is white corundum sand, the abrasive particle size is 80 mesh, the sandblasting distance is 80 mm, and the sandblasting angle is 85°. The ceramic layer is removed.

[0128] The ceramic layer is removed from the rim. The blade body is protected, and then the rim is quickly sandblasted at a pressure of 0.13 MPa and a time of 2 s. The abrasive is white corundum sand, the abrasive particle size is 220 mesh, the sandblasting distance is 80 mm, and the sandblasting angle is 85°. The ceramic layer is removed.

[0129] The ceramic layer is removed from the blade basin in two times. The blade back and the rim with the ceramic layer removed are protected, and then the blade basin is quickly sandblasted in an S shape at a pressure of 0.13 MPa and a time of 2 s. The abrasive is white corundum sand, the abrasive particle size is 220 mesh, the sandblasting distance is 80 mm, and the sandblasting angle is 85°. The ceramic layer is removed.

[0130] The turbine blade with the aluminide diffusion coating after the ceramic layer is removed is cleaned by using a large water flow and ultrasonic cleaning. The blade body and the inner cavity of the turbine blade with the ceramic layer removed are flushed for 2 min to flush out the residual sand in the inner cavity, and then the floating dust on the surface of the blade body is flushed away. Then, the blade tenon of the turbine blade with the ceramic layer removed is placed downward, and the blade tip is placed upward in clean water. The ultrasonic cleaning is performed for 15 min at room temperature.

[0131] Turbine blade drying: The water stains on the outer surface and inner cavity of the blades with the ceramic layer removed are dried by compressed air, and then the blades with the ceramic layer removed are placed in an oven at 120℃ and dried for 150 minutes.

[0132] Turbine blades undergo non-destructive testing;

[0133] Ceramic layer re-preparation: The blade with the ceramic layer removed, which passed non-destructive testing, was placed in the sample chamber of an electron beam physical vapor deposition (EBV) system, where the vacuum level reached 1×10⁻⁶. -3 The blades are then sent into a vacuum chamber and heated to 950°C. The temperature is maintained for 55 minutes to ensure uniform heating. Oxygen is introduced to allow a pure oxide film to grow on the surface of the aluminide diffusion coating. Then, a ceramic surface layer is deposited. The ceramic surface layer exhibits a columnar crystal structure with a thickness of 120 μm, thus forming a new thermal barrier coating on the turbine blades.

[0134] Comparative Example 1

[0135] The ceramic layer of the thermal barrier coating on a single-crystal turbine blade of an aero-engine was removed using an existing chemical method (alkali boiling). The surface of the metal bond layer after ceramic layer removal was characterized by SEM. Figure 3 As shown, corrosion products are generated on the surface of the aluminide diffusion coating of the metal bonding layer. Furthermore, for the aluminide diffusion layer in the inner cavity, the loose products after corrosion are difficult to remove, affecting the continued use of the blade.

[0136] Comparative Example 2

[0137] The ceramic layer of the thermal barrier coating on a single-crystal turbine blade of an aero-engine was removed using existing sandblasting technology. The surface of the metal bond layer after ceramic layer removal was characterized by SEM. Figure 4 As shown, the aluminide diffusion coating of the metal bonding layer is clearly damaged, the two-phase structure of the coating has disappeared, leaving only the interdiffusion layer, and in some areas the substrate has been exposed. This is due to the lack of precise control over the process, resulting in severe thinning of the bonding layer.

[0138] As can be seen from the embodiments and comparative examples of the present invention, the repair method of the ceramic layer of the thermal barrier coating for single crystal turbine blades of aero-engines of the present invention can control the damage to the aluminide diffusion coating bonding layer by the sandblasting method after removing the ceramic layer, retain the metal bonding layer to the maximum extent, and does not generate a corrosion layer; the blades that pass the inspection can be re-prepared after the ceramic layer is removed, and the repaired thermal barrier coating exhibits a columnar crystal structure, which is uniform and continuous, and the ceramic layer and the metal bonding layer are well bonded and can continue to be used.

Claims

1. A method for repairing a ceramic layer of a thermal barrier coating of a single crystal turbine blade of an aeroengine, characterized in that, The metal bonding layer of the thermal barrier coating is an aluminide diffusion coating, and the ceramic layer of the thermal barrier coating is coated on the surface of the aluminide diffusion coating by an electron beam physical vapor deposition method, and comprises the following steps: Turbine blade pretreatment: the turbine blade is cleaned to remove impurities, and then dried; Back of the blade removes the ceramic layer: the tenon, rim and blade basin of the single crystal turbine blade with the metal bonding layer being an aluminide diffusion coating are protected, and then the back of the blade is quickly sandblasted at 0.07-0.13 MPa in an S type to remove the ceramic layer; Blade basin removes the ceramic layer for the first time: the back of the blade is protected, and then the blade basin is quickly sandblasted at 0.17-0.2 MPa in an S type to remove the ceramic layer; Rim removes the ceramic layer: the blade body is protected, and then the rim is quickly sandblasted at 0.07-0.13 MPa to remove the ceramic layer; Blade basin removes the ceramic layer for the second time: the back of the blade and the rim that have removed the ceramic layer are protected, and then the blade basin is quickly sandblasted at 0.07-0.13 MPa in an S type to remove the ceramic layer again; Turbine blade cleaning: the turbine blade with the aluminide diffusion coating after removing the ceramic layer is cleaned; Turbine blade drying; Turbine blade non-destructive testing; Ceramic layer re-preparation: the turbine blade that has passed the non-destructive testing and removed the ceramic layer is preheated in an electron beam physical vapor deposition device, a pure oxide film is first grown on the surface of the aluminide diffusion coating after the blade is uniformly heated, and then a ceramic surface layer is deposited, so that the turbine blade forms a new thermal barrier coating.

2. A method of repairing a ceramic layer of a thermal barrier coating of a single crystal turbine blade of an aeroengine according to claim 1, characterized in that, The aluminide diffusion coating is one of an aluminized coating, a platinum electroplated aluminized coating, an aluminized silicon coating and an aluminized chromium coating, the aluminide diffusion coating is vacuum-diffused after the elements are infiltrated, and the thickness of the aluminide diffusion coating is 20-50 μm.

3. A method of repairing a ceramic layer of a thermal barrier coating of a single crystal turbine blade of an aeroengine according to claim 1, characterized in that, In the back of the blade removes the ceramic layer, the quick sandblasting time is 2-3 s.

4. A method of repairing a ceramic layer of a thermal barrier coating of a single crystal turbine blade of an aeroengine according to claim 1, characterized in that, In the rim removes the ceramic layer, the quick sandblasting time is 2-3 s.

5. A method of repairing a ceramic layer of a thermal barrier coating of a single crystal turbine blade of an aircraft engine as recited in claim 1, wherein, In the blade basin removes the ceramic layer for the first time, the quick sandblasting time is 3-5 s. In the blade basin removes the ceramic layer for the second time, the quick sandblasting time is 2-3 s.

6. A method of repairing a ceramic layer of a thermal barrier coating of a single crystal turbine blade of an aeroengine according to claim 1, characterized in that, In the process of removing the ceramic layer of the back of the blade, the blade basin and the rim by quick sandblasting, white corundum sand is used as the abrasive, the sandblasting distance is 80-150 mm, and the sandblasting angle is 85-95°; the particle size of the abrasive used for the blade basin removes the ceramic layer for the first time is 80-150 mesh, and the particle size of the abrasive used for the back of the blade, the blade basin removes the ceramic layer for the second time and the rim is 150-220 mesh.

7. A method of repairing a ceramic layer of a thermal barrier coating of a single crystal turbine blade of an aircraft engine as recited in claim 1, wherein, The turbine blade cleaning adopts a large water flow washing and ultrasonic cleaning, the blade body and the inner cavity of the blade that has removed the ceramic layer are washed; then the tenon of the blade that has removed the ceramic layer is placed downward and the blade tip is placed upward in clean water for ultrasonic cleaning.

8. A method of repairing a ceramic layer of a thermal barrier coating of a single crystal turbine blade of an aeroengine according to claim 1, characterized in that, The turbine blade drying is that the water spots on the outer surface and the inner cavity of the blade that has removed the ceramic layer are blown dry by compressed air, and then the blade that has removed the ceramic layer is placed in an oven at 120-200 °C and dried for 60-120 min.

9. A method of repairing a ceramic layer of a thermal barrier coating of a single crystal turbine blade of an aircraft engine as recited in claim 1, wherein, In the preparation of the ceramic layer, the preheating temperature is 900-1000 DEG C, and the preheating time is 50-60 min; the ceramic surface layer is deposited on the surface of the aluminide diffusion coating by electron beam physical vapor deposition process, and the ceramic surface layer presents columnar crystal structure with a thickness of 110-150 microns.

10. Use of the method for repairing a thermal barrier coating ceramic layer of a single crystal turbine blade of an aeroengine according to any one of claims 1 to 9, characterized in that, A method for repairing a thermal barrier coated aeroengine turbine blade after use or a new repair of a thermal barrier coated aeroengine turbine blade before use.

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