CN110819981A - Method for repairing nickel-based single crystal turbine blade shroud - Google Patents
Method for repairing nickel-based single crystal turbine blade shroud Download PDFInfo
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- CN110819981A CN110819981A CN201910999704.7A CN201910999704A CN110819981A CN 110819981 A CN110819981 A CN 110819981A CN 201910999704 A CN201910999704 A CN 201910999704A CN 110819981 A CN110819981 A CN 110819981A
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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
- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
- C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
- C23C24/103—Coating with metallic material, i.e. metals or metal alloys, optionally comprising hard particles, e.g. oxides, carbides or nitrides
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
- B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
- B23P6/007—Repairing turbine components, e.g. moving or stationary blades, rotors using only additive methods, e.g. build-up welding
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Abstract
The invention provides a method for repairing a blade shroud of a nickel-based single-crystal turbine blade, and relates to the field of structural repair. The repairing method comprises the following steps: removing the damaged part of the turbine blade shroud to form a part to be repaired, wherein the blade comprises a plurality of areas which are sequentially connected in the spanwise direction; carrying out gradient heating or heat preservation on each area in the repairing process so as to gradually decrease the heating or heat preservation temperature of each area from near to far away from the part to be repaired; forming a cladding layer on the surface of the part to be repaired by a laser cladding process; and removing the material of the preset area of the cladding layer to form a target repairing layer. The repair method of the nickel-based single crystal turbine blade shroud can reduce thermal stress and thermal deformation, enables the crystal orientation of the repaired part to be consistent with that of a base body, meets the use requirement of the blade after subsequent polishing and modification, prolongs the service life of the blade and reduces the cost.
Description
Technical Field
The disclosure relates to the field of structure repair, in particular to a repair method of a nickel-based single crystal turbine blade shroud.
Background
The nickel-based single crystal alloy has good high temperature resistance, creep resistance, oxidation resistance and thermal mechanical fatigue resistance, so that the nickel-based single crystal alloy is widely applied to turbine blades of aeroengines and gas turbines, and the turbine blade shroud is an important component of the turbine blade and is often influenced by extreme environments in the operation process of the blade, so that the turbine blade shroud has defects and damages such as chipping or cracking. The occurrence of these defects and damages changes the bearing structure and the vibration characteristics of the blades, with slight consequences of machine damage, blade rejection and heavy consequences of rotor blade breakage, jeopardizing the safety of the engines and airplanes.
When defects or damages occur to the existing turbine blades, the existing turbine blades are required to be replaced frequently, but the yield of the turbine blades in the manufacturing process is low, the materials are expensive, and the replacement cost is high.
It is to be noted that the information disclosed in the above background section is only for enhancement of understanding of the background of the present disclosure, and thus may include information that does not constitute prior art known to those of ordinary skill in the art.
Disclosure of Invention
The purpose of the present disclosure is to overcome the defects in the prior art, and provide a method for repairing a blade shroud of a nickel-based single crystal turbine blade, which can reduce thermal stress and thermal deformation, so that the crystal orientation of the repaired portion is consistent with that of a base body, meet the use requirements of the blade after subsequent polishing and modification, prolong the service life of the blade, avoid frequent blade replacement, and reduce cost.
According to one aspect of the present disclosure, there is provided a method for repairing a nickel-based single crystal turbine blade shroud, comprising:
removing a damaged part of a turbine blade shroud to form a part to be repaired, wherein the blade comprises a plurality of areas which are sequentially connected in the spanwise direction;
carrying out gradient heating or heat preservation on each region in the repairing process so as to gradually decrease the heating or heat preservation temperature of each region from near to far away from the part to be repaired;
forming a cladding layer on the surface of the part to be repaired by a laser cladding process;
and removing the material of the preset area of the cladding layer to form a target repairing layer.
In an exemplary embodiment of the present disclosure, the removing the damaged portion of the turbine blade shroud to form the portion to be repaired, the blade including a plurality of regions connected in sequence in a span-wise direction includes:
removing the damaged part of the blade shroud of the turbine blade by adopting mechanical processing to form a part to be repaired;
the blade comprises a blade root, a blade body, a blade tip and a blade shroud which are sequentially connected in the spanwise direction, and the part to be repaired is located on the blade shroud.
In an exemplary embodiment of the present disclosure, the heating or holding temperature of each of the regions ranges from 80 ℃ to 200 ℃.
In an exemplary embodiment of the present disclosure, performing gradient heating or heat preservation on each region in a repair process, so that each heating or heat preservation temperature of each region from near to far from the portion to be repaired gradually decreases includes:
in an inert gas environment, gradient heating or heat preservation is carried out on each area of the blade in an induction mode, the heating or heat preservation temperature of the area containing the part to be repaired in each area is higher than that of other areas, and the heating or heat preservation temperature of the area close to the part to be repaired in each area is higher than that of the area far away from the part to be repaired.
In an exemplary embodiment of the present disclosure, the forming a cladding layer on the surface of the portion to be repaired through a laser cladding process includes:
scanning the part to be repaired by adopting laser;
adding a cladding material to the part to be repaired;
and scanning the part to be repaired and the cladding material by adopting laser to form a cladding layer.
In an exemplary embodiment of the present disclosure, a spot diameter of the laser is 1.0 to 1.5mm, a scanning power of the laser is 300 to 800W, and a scanning speed of the laser is 5 to 8 mm/s.
In an exemplary embodiment of the present disclosure, the cladding material is a nickel-based single crystal superalloy powder.
In an exemplary embodiment of the present disclosure, the repair method further includes:
and detecting the temperature of each area by using a temperature sensor, and adjusting the temperature of each area to return to the corresponding preset range when the temperature of each area exceeds the corresponding preset range.
In an exemplary embodiment of the present disclosure, the cladding process is multilayer multi-pass cladding.
In an exemplary embodiment of the present disclosure, the repair method further includes:
and carrying out X-ray and fluorescent flaw detection on the target repairing layer.
According to the method for repairing the nickel-based single crystal turbine blade shroud, the damaged part of the turbine blade shroud can be repaired by adopting a laser cladding process, the service life of the turbine blade can be prolonged, resource waste caused by frequent replacement of the blade is avoided, and the cost is reduced. In the process, as the plurality of areas of the turbine blade are heated or insulated simultaneously, the temperature difference between the part to be repaired and other areas can be reduced, and the temperature of each area from near to far from the part to be repaired is gradually reduced, so that the temperature difference between the area close to the part to be repaired and the part to be repaired can be reduced, and the thermal stress of the part to be repaired and the adjacent parts can be reduced. The crystal growth rate, growth direction and grain size of the part to be repaired can be controlled by controlling the temperature of each area, so that the crystal orientations of the target repair layer and the original blade substrate are kept consistent, and the macroscopic mechanical property of the blade is ensured; meanwhile, in each area, the thermal stress in two adjacent areas is reduced, so that the thermal stress of the repaired blade can be reduced on the whole, and the thermal deformation of the repaired blade is reduced.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the disclosure.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present disclosure and together with the description, serve to explain the principles of the disclosure. It is to be understood that the drawings in the following description are merely exemplary of the disclosure, and that other drawings may be derived from those drawings by one of ordinary skill in the art without the exercise of inventive faculty.
FIG. 1 is a flow chart of a method of repairing a nickel-based single crystal turbine blade shroud according to an embodiment of the present disclosure.
FIG. 2 is a schematic structural view of a blade according to an embodiment of the present disclosure.
FIG. 3 is a schematic view of an induction coil wrap around a blade according to an embodiment of the present disclosure.
FIG. 4 is a schematic diagram of a repair system according to an embodiment of the present disclosure.
Fig. 5 is a flowchart of step S130 in fig. 1.
Fig. 6 is a schematic view of a repair system according to an embodiment of the disclosure.
In the figure: 101. a leaf shroud; 102. a blade tip; 103. a leaf body; 104. a blade root; 1. a coil; 2. a heating device; 3. a laser scanning device; 4. a temperature sensor; 5. a powder feeding device; 6. a control system; 7. a cooling system; 8. an operation platform.
Detailed Description
Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar structures, and thus their detailed description will be omitted.
Although relative terms, such as "upper" and "lower," may be used in this specification to describe one element of an icon relative to another, these terms are used in this specification for convenience only, e.g., in accordance with the orientation of the examples described in the figures. It will be appreciated that if the device of the icon were turned upside down, the element described as "upper" would become the element "lower". When a structure is "on" another structure, it may mean that the structure is integrally formed with the other structure, or that the structure is "directly" disposed on the other structure, or that the structure is "indirectly" disposed on the other structure via another structure.
The terms "a," "an," "the," "said" are used to indicate the presence of one or more elements/components/etc.; the terms "comprising" and "having" are intended to be inclusive and mean that there may be additional elements/components/etc. other than the listed elements/components/etc.
The disclosed embodiment provides a repair method for a nickel-based single crystal turbine blade shroud, which can be completed with the assistance of a repair system, and as shown in fig. 1, the repair method can include:
step S110, removing a damaged part of a turbine blade shroud to form a part to be repaired, wherein the blade comprises a plurality of areas which are sequentially connected in the spanwise direction;
step S120, carrying out gradient heating or heat preservation on each region in the repairing process so as to gradually decrease the heating or heat preservation temperature of each region from near to far away from the part to be repaired;
step S130, forming a cladding layer on the surface of the part to be repaired through a laser cladding process;
and step S140, removing materials in a preset area of the cladding layer to form a target repairing layer.
According to the method for repairing the nickel-based single crystal turbine blade shroud, the damaged part of the turbine blade shroud can be repaired by adopting a laser cladding process, the service life of the turbine blade can be prolonged, resource waste caused by frequent replacement of the blade is avoided, and the cost is reduced. In the process, as a plurality of areas of the turbine blade are heated or insulated simultaneously, the temperature difference between the part to be repaired and other areas can be reduced, and the temperature of each area in each area from near to far away from the part to be repaired is gradually reduced, so that the temperature difference between the area close to the part to be repaired and the part to be repaired can be reduced, the thermal stress between the part to be repaired and the adjacent part can be reduced, the crystal growth rate, the growth direction and the grain size of the part to be repaired can be controlled by controlling the temperature of each area, the crystal orientation of the target repairing layer and the crystal orientation of the original blade matrix can be kept consistent, and the macroscopic mechanical property of the blade can be ensured; meanwhile, in each area, the thermal stress in two adjacent areas is reduced, so that the thermal stress of the repaired blade can be reduced on the whole, and the thermal deformation of the repaired blade is reduced.
The following describes in detail the steps of the method for repairing a nickel-based single crystal turbine blade shroud according to an embodiment of the present disclosure:
as shown in fig. 1, in step S110, a damaged portion of the blade shroud may be removed to form a portion to be repaired, and the blade may include a plurality of regions connected in sequence in the span-wise direction.
As shown in fig. 2-3, the shroud 101 is an important component of the turbine blade, and can be used to improve the reliability of the turbine blade and reduce blade vibration. In the working process of the blade, due to the influence of extreme environments such as high temperature, high pressure, corrosion, thermal fatigue and vibration, the friction generated between the blade shroud 101 and the working surface of the blade shroud 101, the collision friction between the top of the blade shroud 101 and a casing and the like, the defects such as fatigue damage, chipping or cracks and the like are caused on the local part of the blade shroud, and the part with the defects such as fatigue damage, chipping or cracks can be used as a damaged part to be repaired, so that the replacement frequency of the blade is reduced, and the cost is reduced. During repair, the damaged portion may be removed to form a portion to be repaired, and the blade may be divided into a plurality of sequentially connected regions along a blade span direction, for example, the span direction may be a direction in which the blade extends along the longitudinal direction, and of course, other directions may also be used, which are not particularly limited herein. The number of the regions may be 3, 4, 5, 6, 7 or 8, or may be other numbers, and is not limited herein.
In addition, the surface of the part to be repaired needs to be cleaned so as to remove impurities and oil stains on the surface of the part to be repaired. The surface of the part to be repaired can be cleaned by using an organic solvent, for example, the surface of the part to be repaired can be cleaned by using alcohol, acetone or isopropanol, and the like.
In an embodiment, the damaged portion of the tip shroud 101 may be mechanically ground to remove the nickel-based single crystal material of the damaged portion, so that the damaged portion is recessed inward to form a portion to be repaired, and a surface of the portion to be repaired may be a smooth plane or a curved surface, which is not particularly limited herein. The nickel-based single crystal material can be polished by a mechanical processing instrument or manually, and is not particularly limited as long as the nickel-based single crystal material at the damaged part can be removed.
As shown in fig. 2, the blade may include a shroud 101, a tip 102, a body 103 and a root 104 connected in sequence along the span direction, and the blade may be further divided into a plurality of regions along the span direction, and each region may be connected in sequence along the span direction, in one embodiment, one region may be from the root 104 to the center of the blade, two regions may be from the center of the blade to three quarters of the body 103 of the blade, three regions may be from the remaining body 103 and the undamaged shroud 101, and four regions may be to-be-repaired regions.
It should be noted that the blade may also comprise other areas, such as: five, six, seven or even more regions may also be included, not to mention here.
As shown in fig. 1, in step S120, gradient heating or temperature preservation is performed on each region in the repairing process, so that the heating or temperature preservation temperature of each region from near to far from the to-be-repaired portion gradually decreases.
In the repairing process, gradient heating or heat preservation can be carried out on each area, wherein the gradient heating or heat preservation refers to that the blade is heated or heat preserved according to the corresponding preset temperature of each area, and the heating or heat preservation temperatures of two adjacent areas in the blade are different. Specifically, each region of the blade may be inductively preheated in an inert gas atmosphere, and the inert gas may be argon, neon, nitrogen, argon, or the like, or may be other gas having relatively stable chemical properties.
As shown in fig. 3, the induction coil 1 may be used for induction preheating, or the coil may be used for heating or heat preservation. For example, there may be a plurality of coils 1, for example, there may be 3, 4, 5, 6, 7 or 8 coils, and of course, there may be other numbers, which are not limited herein. It should be noted that the overall preheating temperature of each region may be 80 ℃, the number of the coils 1 may be equal to the number of the divided regions in the blade, and each coil 1 may have a region corresponding to one thereof, and the coil 1 may be wound around the outer circumference of the region corresponding thereto so as to inductively preheat each region of the blade by the heating coil 1. As shown in fig. 4, the temperature of each induction coil 1 can be controlled by the control system 6, so as to heat or preserve heat of each region, further reduce the temperature difference between the region close to the part to be repaired and the part to be repaired, thereby reducing the thermal stress between the part to be repaired and the adjacent part, and the crystal growth rate, growth direction and grain size of the part to be repaired can be controlled by controlling the heating or preserving temperature of each region, so that the crystal orientations of the target repair layer and the original blade repair matrix are kept consistent, thereby ensuring the macro mechanical property of the blade.
For example, the control system 6 may control the heating device 2 to heat each coil 1 according to each preset temperature corresponding to each region, so that the induction temperature of each coil 1 is within the corresponding preset temperature range. The coil 1 may be a copper alloy tube, but of course, may be other devices that can be used for heating, and is not limited herein.
It should be noted that, the regions of the blade may be heated or insulated in other manners, and are not limited herein.
Each area has a preset temperature corresponding to one of the areas, the preset temperatures of two adjacent areas in the plurality of areas can be different from each other, when the part to be repaired is located in the middle area, the preset temperatures of the two adjacent areas can be the same, and meanwhile, the preset temperatures of the two areas with the same distance can also be the same. In addition, the preset temperature of the region including the portion to be repaired in each region may be higher than the preset temperature of any other region, for example, the heating or heat preservation temperature of the portion to be repaired may range from 80 ℃ to 200 ℃, for example, the preset temperature of the region where the portion to be repaired is located may be 80 ℃, 120 ℃, 140 ℃, 160 ℃, or 200 ℃, of course, other temperatures may also be used, and are not listed here. It should be noted that, in order to ensure the repairing effect, the temperature of the part to be repaired can be kept constant.
In one embodiment, the heating or holding temperature of the region closer to the site to be repaired may be greater than the heating or holding temperature of the region farther from the site to be repaired. For example, when the portion to be repaired is located in the fourth region, the distance between the third region and the portion to be repaired is smaller than the distance between the second region and the portion to be repaired, and the distance between the second region and the portion to be repaired is smaller than the distance between the first region and the portion to be repaired. For example, the preset temperature of the fourth region may range from 80 ℃ to 700 ℃, and the preset temperature of the third region may range from 60 ℃ to 80 ℃, which may be 60 ℃, 65 ℃, 70 ℃, 75 ℃ or 80 ℃; the preset temperature of the second region can be 40-60 deg.C, which can be 40 deg.C, 45 deg.C, 50 deg.C, 55 deg.C or 60 deg.C; the preset temperature of the first region may range from 20 ℃ to 40 ℃, which may be 20 ℃, 25 ℃, 30 ℃, 35 ℃ or 40 ℃, and of course, the first region, the second region, the third region and the fourth region may be other temperatures, which are not listed herein.
As shown in fig. 1, in step S130, a cladding layer may be formed on the surface of the portion to be repaired through a laser cladding process.
The part to be repaired can be scanned by laser, and the cladding material is added to the surface of the part to be repaired while the laser is scanned, so that the material of the part to be repaired and the cladding material are melted and fused into a whole at the same time, and a cladding layer is formed. In the process, in order to ensure the repairing effect, a multi-layer and multi-channel cladding process can be adopted. The cladding material may be the same as the material of the tip shroud 101, for example, it may be nickel-based single crystal superalloy powder, and when the material of the tip shroud 101 is other materials, the cladding material may also be other materials, which is not limited herein. The thickness of the cladding layer may be determined according to the thickness of the portion to be repaired, and is not particularly limited herein.
In one embodiment, as shown in fig. 5, step 130 may include:
and step S1301, scanning the part to be repaired by adopting laser.
As shown in fig. 6, the tip shroud 101 may be placed on the cladding operation table 8, the portion to be repaired faces one side of the laser light source, and the laser scanning device 3 is used to scan the portion to be repaired, so as to melt the surface of the portion to be repaired. For example, the spot diameter may range from 1.0mm to 1.5mm, for example, the spot diameter may be 1.0mm, 1.1mm, 1.2mm, 1.3mm, 1.4mm, or 1.5 mm; the value range of the scanning power can be 300-800W, for example, the scanning power can be 300W, 400W, 500W, 600W, 700W or 800W; the scanning speed can be 5-8 mm/s, for example, 5mm/s, 6mm/s, 7mm/s or 8 mm/s. Of course, the spot diameter, the scanning power and the scanning speed may also be in other value ranges, and are not particularly limited herein.
Step S1302, adding a cladding material to the portion to be repaired.
The cladding material can be powder particles, the granularity of the powder particles can be-100 to +300 meshes, and the cladding material can also be massive solid, so that the existence state of the cladding material is not specially limited. Taking the cladding material as powder as an example, the cladding material can be added to the surface of the part to be repaired by a powder feeding device 5 in a synchronous powder feeding manner, and the value range of the powder feeding rate can be 8.5-12.5 g/min, for example, the powder feeding rate can be 8.5g/min, 9.5g/min, 10.5g/min, 11.5g/min and 12.5 g/min; of course, the powder feeding rate may be other rates, and is not particularly limited. Of course, the cladding material may also be added to the surface of the portion to be repaired in other manners, and the manner of adding the cladding material is not particularly limited herein.
And step S1303, scanning the part to be repaired and the cladding material by laser to form a cladding layer.
The laser is adopted to simultaneously scan the part to be repaired and the cladding material arranged on the surface of the part to be repaired, so that the surface to be repaired and the cladding material can be simultaneously melted and fused into a whole and can be rapidly solidified, and a cladding layer is formed. The cladding process can be multilayer and multi-pass cladding, the thickness of each layer can be 0.3 mm-0.5 mm, and of course, other thicknesses can be adopted, which is not illustrated.
As shown in fig. 1, in step S140, a material of a predetermined region of the cladding layer is removed, and a target repair layer is formed.
Mechanical methods may be used to remove material from a predetermined area of the cladding layer, which may be an area outside the original size of the tip shroud 101, so that the size of the tip shroud 101 after repair is consistent with the size of the tip shroud 101 before repair. The excess material in the area can be removed by machining, and the material in the preset area can be removed by manual grinding, which is not limited herein.
The repair method of the embodiment of the present disclosure may further include:
step S150, detecting the temperature of each of the regions by using a temperature sensor, and adjusting the temperature of each of the regions to return to the corresponding predetermined range when the temperature of each of the regions exceeds the corresponding predetermined range.
For example, the temperature of each region can be detected by the temperature sensor 4, and the number of the temperature sensors 4 can be plural, which can be 3, 4, 5, 6, 7 or 8, and of course, other numbers can be also used, which are not listed here. It should be noted that the number of temperature sensors 4 may be matched to the number of regions in the blade, namely: each zone may be provided with one temperature sensor 4 in a one-to-one correspondence, and each temperature sensor 4 may be configured to detect the temperature of the zone corresponding thereto. When the detected temperature exceeds the preset temperature range of each area, the temperature of each area can be adjusted to return to the corresponding preset range.
For example, when the temperature detected by the temperature sensor 4 is greater than the maximum value of the preset temperature range of the area, the cooling system 7 may be used to cool the coil 1 by introducing cooling water into the coil 1, the cooling water may circulate inside the coil 1 through the cooling channel, so as to take away part of the heat and reduce the temperature inside the coil 1, and when the temperature is reduced to the preset range corresponding to the area, the supply of the cooling water is stopped. In addition, when the repair is completed, the temperature of each element of the induction coil 1 and the heating device 2 can be lowered by cooling water. When the temperature detected by the temperature sensor 4 is smaller than the minimum value of the preset temperature range of the area, the internal temperature of the coil 1 can be increased in a heating mode for the coil 1, and the heating can be stopped when the temperature is increased to the preset range corresponding to the area. In one embodiment, the temperature sensor 4 may be a thermocouple.
The repair method of the embodiment of the present disclosure may further include:
and step S160, carrying out X-ray and fluorescent flaw detection on the target repairing layer.
The X-ray detection system can be used for carrying out X-ray detection on the repaired tip shroud 101, and a penetrant dissolved with fluorescent dye can also be permeated into the surface of the repaired tip shroud 101 for carrying out fluorescent flaw detection so as to determine whether the repaired tip shroud 101 has defects or damages and evaluate the repairing effect of laser repair.
Other embodiments of the disclosure will be apparent to those skilled in the art from consideration of the specification and practice of the disclosure disclosed herein. This application is intended to cover any variations, uses, or adaptations of the disclosure following, in general, the principles of the disclosure and including such departures from the present disclosure as come within known or customary practice within the art to which the disclosure pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the disclosure being indicated by the following claims.
Claims (10)
1. A method for repairing a nickel-based single crystal turbine blade shroud is characterized by comprising the following steps:
removing a damaged part of a turbine blade shroud to form a part to be repaired, wherein the blade comprises a plurality of areas which are sequentially connected in the spanwise direction;
carrying out gradient heating or heat preservation on each region in the repairing process so as to gradually decrease the heating or heat preservation temperature of each region from near to far away from the part to be repaired;
forming a cladding layer on the surface of the part to be repaired by a laser cladding process;
and removing the material of the preset area of the cladding layer to form a target repairing layer.
2. The repair method of claim 1, wherein the removing the damaged portion of the turbine blade shroud to form the portion to be repaired, the blade including a plurality of regions connected in series in a span-wise direction comprises:
removing the damaged part of the blade shroud of the turbine blade by adopting mechanical processing to form a part to be repaired;
the blade comprises a blade root, a blade body, a blade tip and a blade shroud which are sequentially connected in the spanwise direction, and the part to be repaired is located on the blade shroud.
3. The repair method according to claim 1, wherein the heating or holding temperature of the portion to be repaired is in a range of 80 ℃ to 200 ℃.
4. The repair method according to claim 1, wherein performing gradient heating or heat preservation on each region in the repair process so that the heating or heat preservation temperature of each region from near to far from the part to be repaired gradually decreases comprises:
in an inert gas environment, gradient heating or heat preservation is carried out on each area of the blade in an induction mode, the heating or heat preservation temperature of the area containing the part to be repaired in each area is higher than that of other areas, and the heating or heat preservation temperature of the area close to the part to be repaired in each area is higher than that of the area far away from the part to be repaired.
5. The repair method of claim 1, wherein the forming of the cladding layer on the surface of the portion to be repaired by the laser cladding process includes:
scanning the part to be repaired by adopting laser;
adding a cladding material to the part to be repaired;
and scanning the part to be repaired and the cladding material by adopting laser to form a cladding layer.
6. The repairing method according to claim 5, wherein the spot diameter of the laser is 1.0 to 1.5mm, the scanning power of the laser is 300 to 800W, and the scanning speed of the laser is 5 to 8 mm/s.
7. The repair method of claim 5 wherein the cladding material is a nickel-based single crystal superalloy powder.
8. The repair method of claim 1, further comprising:
and detecting the temperature of each area by using a temperature sensor, and adjusting the temperature of each area to return to the corresponding preset range when the temperature of each area exceeds the corresponding preset range.
9. The repair method of claim 1, wherein the cladding process is multi-layer multi-pass cladding.
10. The repair method of claim 1, further comprising:
and carrying out X-ray and fluorescent flaw detection on the target repairing layer.
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| CN201910999704.7A CN110819981A (en) | 2019-10-21 | 2019-10-21 | Method for repairing nickel-based single crystal turbine blade shroud |
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| CN201910999704.7A CN110819981A (en) | 2019-10-21 | 2019-10-21 | Method for repairing nickel-based single crystal turbine blade shroud |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112045363A (en) * | 2020-08-07 | 2020-12-08 | 中国人民解放军第五七一九工厂 | Integrated repairing method for turbine blade damage |
| CN112267110A (en) * | 2020-09-27 | 2021-01-26 | 西安交通大学 | Blade tip cutting coating preparation system with residual stress relieving effect and use method |
| CN113478167A (en) * | 2021-07-21 | 2021-10-08 | 中国航发航空科技股份有限公司 | Method for repairing blade shroud of working blade of high-pressure turbine of aircraft engine |
| CN113878119A (en) * | 2021-09-18 | 2022-01-04 | 航发优材(镇江)增材制造有限公司 | Laser direct deposition repair method for abrasion of tight-lock coupler for high-speed rail |
| CN116219434A (en) * | 2023-05-04 | 2023-06-06 | 成都裕鸢航空智能制造股份有限公司 | Repair device and repair method for turbine guide vane of aero-engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112045363A (en) * | 2020-08-07 | 2020-12-08 | 中国人民解放军第五七一九工厂 | Integrated repairing method for turbine blade damage |
| CN112267110A (en) * | 2020-09-27 | 2021-01-26 | 西安交通大学 | Blade tip cutting coating preparation system with residual stress relieving effect and use method |
| CN112267110B (en) * | 2020-09-27 | 2022-04-22 | 西安交通大学 | Blade tip cutting coating preparation system with residual stress relieving effect and use method |
| CN113478167A (en) * | 2021-07-21 | 2021-10-08 | 中国航发航空科技股份有限公司 | Method for repairing blade shroud of working blade of high-pressure turbine of aircraft engine |
| CN113878119A (en) * | 2021-09-18 | 2022-01-04 | 航发优材(镇江)增材制造有限公司 | Laser direct deposition repair method for abrasion of tight-lock coupler for high-speed rail |
| CN116219434A (en) * | 2023-05-04 | 2023-06-06 | 成都裕鸢航空智能制造股份有限公司 | Repair device and repair method for turbine guide vane of aero-engine |
| CN116219434B (en) * | 2023-05-04 | 2023-07-07 | 成都裕鸢航空智能制造股份有限公司 | Repair device and repair method for turbine guide vane of aero-engine |
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