CN114150256B - High-temperature-resistant hot corrosion coating for small-sized turbine working blade of aero-engine - Google Patents
High-temperature-resistant hot corrosion coating for small-sized turbine working blade of aero-engine Download PDFInfo
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- CN114150256B CN114150256B CN202111530168.XA CN202111530168A CN114150256B CN 114150256 B CN114150256 B CN 114150256B CN 202111530168 A CN202111530168 A CN 202111530168A CN 114150256 B CN114150256 B CN 114150256B
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- 238000000576 coating method Methods 0.000 title claims abstract description 100
- 239000011248 coating agent Substances 0.000 title claims abstract description 97
- 238000005260 corrosion Methods 0.000 title claims abstract description 24
- 230000007797 corrosion Effects 0.000 title claims abstract description 23
- 239000010410 layer Substances 0.000 claims abstract description 50
- 239000002344 surface layer Substances 0.000 claims abstract description 39
- 238000002360 preparation method Methods 0.000 claims abstract description 7
- 230000001681 protective effect Effects 0.000 claims description 46
- 239000000843 powder Substances 0.000 claims description 32
- 239000002390 adhesive tape Substances 0.000 claims description 24
- 238000009792 diffusion process Methods 0.000 claims description 22
- 239000007921 spray Substances 0.000 claims description 17
- 238000005507 spraying Methods 0.000 claims description 16
- 230000032683 aging Effects 0.000 claims description 14
- 238000000034 method Methods 0.000 claims description 13
- 238000007750 plasma spraying Methods 0.000 claims description 8
- 238000010290 vacuum plasma spraying Methods 0.000 claims description 7
- 238000004519 manufacturing process Methods 0.000 claims description 4
- 238000005498 polishing Methods 0.000 claims description 4
- 239000003292 glue Substances 0.000 claims 1
- 238000007790 scraping Methods 0.000 abstract description 11
- 239000011159 matrix material Substances 0.000 abstract description 9
- 238000000227 grinding Methods 0.000 abstract description 8
- 238000012423 maintenance Methods 0.000 abstract description 5
- 238000005524 ceramic coating Methods 0.000 abstract description 3
- 239000007789 gas Substances 0.000 description 8
- 230000000052 comparative effect Effects 0.000 description 7
- 230000008569 process Effects 0.000 description 6
- 238000012360 testing method Methods 0.000 description 6
- 230000003628 erosive effect Effects 0.000 description 5
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 4
- 239000002245 particle Substances 0.000 description 4
- 238000009826 distribution Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 2
- 229910052786 argon Inorganic materials 0.000 description 2
- 229910003460 diamond Inorganic materials 0.000 description 2
- 239000010432 diamond Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
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- 230000003647 oxidation Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- 238000005070 sampling Methods 0.000 description 2
- 239000000758 substrate Substances 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 239000002253 acid Substances 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000012159 carrier gas Substances 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000011247 coating layer Substances 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 238000007561 laser diffraction method Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 238000003921 particle size analysis Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000011253 protective coating Substances 0.000 description 1
- 230000003746 surface roughness Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
- C23C4/134—Plasma spraying
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
- C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/18—After-treatment
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/284—Selection of ceramic materials
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
The application discloses a high-temperature-resistant hot corrosion coating of a small-size turbine working blade of an aeroengine and a preparation method thereof, comprising the following steps: a NiCoCrAlYTA coating sprayed on the blade body and the blade edge plate flow surface, and a NiCrAlY bottom layer and a YSZ surface layer sprayed on the blade tip. According to the high-temperature-resistant hot corrosion coating for the small-size turbine working blade of the aeroengine, the NiCoCrAlYTA coating is sprayed on the blade body and the flange flow path surface, the NiCrAlY bottom layer and the YSZ surface layer are sprayed on the blade tip, the NiCrAlY bottom layer and the YSZ surface layer are adopted for the blade tip, high-temperature protection can be realized, scraping and scrapping of the blade caused by adhesion of the coating can be avoided, and after the YSZ surface layer is adopted for the blade tip, the ceramic coating is not adhered and agglomerated after scraping and grinding, and can be discharged along with airflow, so that scraping and grinding damage of a blade matrix is avoided, and the maintenance cost of the engine is reduced.
Description
Technical Field
The application relates to the field of aeroengines, in particular to a high-temperature-resistant hot corrosion coating for a small-size turbine working blade of an aeroengine. In addition, the application also relates to a preparation method of the high-temperature-resistant hot corrosion coating comprising the small-size turbine rotor blade of the aero-engine.
Background
The working vane of the gas turbine is an important component of a turbine part of an aeroengine, the working environment is a high-temperature, high-speed and high-pressure ultra-severe environment, the vane base material is mostly made of single crystal materials, and the high-temperature and hot corrosion resistant protective coating is mostly sprayed on the surface of the vane for protecting the part base, prolonging the service life of the vane and reducing the cost.
The vacuum plasma spraying NiCoCrAlYTA coating is an excellent high-temperature oxidation resistant coating which is commonly used for turbine parts of aeroengines, and the blade body and the blade tip of a gas turbine rotor blade are commonly sprayed with the coating. However, during use, the tip coating and the turbine outer ring of the object are found to have scraping and metal accumulation in the inner circle of the turbine outer ring during use, as shown in fig. 1, and the tip of the working blade of the gas turbine is worn out due to continued use, as shown in fig. 2.
Disclosure of Invention
The application provides a high-temperature-resistant hot corrosion coating for a small-size turbine working blade of an aeroengine and a preparation method thereof, and aims to solve the technical problem that the blade tip abrasion is easy to cause when the same coating is used for the existing integral blade.
The technical scheme adopted by the application is as follows:
a high temperature hot erosion resistant coating for a small turbine rotor blade of an aircraft engine comprising: a NiCoCrAlYTA coating sprayed on the blade body and the blade edge plate flow surface, and a NiCrAlY bottom layer and a YSZ surface layer sprayed on the blade tip.
Further, the thickness of the NiCoCrAlYTA coating is 0.04 mm-0.1 mm; the thickness of the NiCrAlY bottom layer is 0.02 mm-0.15 mm; the thickness of the YSZ surface layer is 0.1 mm-0.35 mm.
According to another aspect of the application, there is also provided a method for preparing the high temperature hot corrosion resistant coating of a small turbine rotor blade of an aeroengine, comprising the steps of:
s1, protecting a non-spraying part of a blade, and carrying out vacuum plasma spraying on NiCoCrAlYTA powder on the blade body and the runner surface of the edge plate to form a NiCoCrAlYTA coating;
s2, removing the protection, and performing diffusion treatment on the blade with the NiCoCrAlYTA coating;
s3, polishing the NiCoCrAlYTA coating of the blade body and the edge plate after the diffusion treatment, and removing the NiCoCrAlYTA coating remained on the surface of the blade tip;
s4, protecting the blade body, the tenon teeth and the edge plate, performing atmospheric plasma spraying on the surface of the blade tip by using NiCrAlY powder to form a NiCrAlY bottom layer, and performing atmospheric plasma spraying on the NiCrAlY bottom layer by using YSZ powder to form a YSZ surface layer;
s5, removing the protection, and performing aging treatment on the blade with the NiCrAlY bottom layer and the YSZ surface layer.
Further, in the step S2, the diffusion treatment temperature is 900-1100 ℃, and the diffusion treatment time is 4-7 hours.
Further, in the step S5, the aging treatment temperature is 600-900 ℃, and the aging treatment time is 18-32 h.
Further, the specific step of protecting the blade body and the tenon tooth in the step S4 includes: the tenon tooth is protected by a protective clamp; the blade body is protected by adopting a high-temperature-resistant protective adhesive tape.
Further, the protective jig comprises a mounting base, a bottom plate arranged on the mounting base, a groove structure for accommodating the blade edge plate is arranged on the bottom plate, a mounting plate arranged on the mounting base and stacked on the bottom plate is circumferentially provided with a mortise matched with the blade tenon, a cover plate arranged on the mounting base and covered on the mounting plate is arranged on the bottom plate, the bottom plate and the cover plate are matched to be used for protecting the edge plate, a first connecting piece for fixedly connecting the bottom plate and the mounting plate is used for fixedly connecting the mounting plate and a second connecting piece for fixedly connecting the mounting plate and the cover plate.
Further, a plurality of mortises are adopted, and the mortises are distributed at intervals along the circumferential direction of the mounting plate; the groove structures are multiple, and the groove structures are arranged in one-to-one correspondence with the mortises; the plug is used for plugging the mortise.
Further, after the blade body, the tenon teeth and the edge plates are protected, a protective clamp with blades is arranged on a rotary table, the rotary table rotates along the axial center line, the rotary table rotates at 80-150 rpm, a plasma spray gun moves up and down along the direction parallel to the center line to spray NiCrAlY powder until the tips of all the blades form a NiCrAlY bottom layer; the turntable rotates along the axial center line, the rotating speed of the turntable is 80 rpm-150 rpm, and the plasma spray gun moves up and down along the direction parallel to the center line to spray YSZ powder until YSZ surface layers are formed on all the NiCrAlY bottom layers.
Further, at least two layers of high-temperature protective adhesive tapes are adopted; the high-temperature protective adhesive is positioned at the junction of the blade body and the blade tip and presents an oblique angle of 40-60 degrees.
The application has the following beneficial effects:
according to the high-temperature-resistant hot corrosion coating for the small-size turbine working blade of the aeroengine, the NiCoCrAlYTA coating is sprayed on the blade body and the flange flow path surface, the NiCrAlY bottom layer and the YSZ surface layer are sprayed on the blade tip, the NiCrAlY bottom layer and the YSZ surface layer are adopted for the blade tip, high-temperature protection can be realized, scraping and scrapping of the blade caused by adhesion of the coating can be avoided, and after the YSZ surface layer is adopted for the blade tip, the ceramic coating is not adhered and agglomerated after scraping and grinding, and can be discharged along with airflow, so that scraping and grinding damage of a blade matrix is avoided, and the maintenance cost of the engine is reduced. And the YSZ surface layer can be sprayed again after being removed mechanically. However, the blade body and the blade tip of the existing blade are both coated with the same coating, and because the small-size turbine working blade is in a high-temperature, high-pressure and high-speed environment for a long time, when the coating is damaged, the new turbine working blade can only be replaced, and maintenance cannot be performed.
In addition to the objects, features and advantages described above, the present application has other objects, features and advantages. The application will be described in further detail with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application. In the drawings:
FIG. 1 is a schematic view of the inner circle of the outer ring of the turbine of the present application;
FIG. 2 is a schematic illustration of a gas turbine rotor blade tip of the present application;
FIG. 3 is a microstructure view of a polished blade body of preferred embodiment 1 of the present application;
FIG. 4 is a microstructure view of a tip polished state of a preferred embodiment 1 of the present application;
FIG. 5 is a microstructure view of a blade body polished state of preferred comparative example 1 of the present application;
FIG. 6 is a microstructure view of a tip polished state of a preferred comparative example 1 of the present application;
FIG. 7 is a microstructure view of a blade body in a corroded state according to a preferred embodiment 1 of the present application;
FIG. 8 is a microstructure view of a tip erosion state of a preferred embodiment 1 of the present application;
FIG. 9 is an external view of the trial rear blade body of the preferred embodiment 1 of the present application;
FIG. 10 is a view of the appearance of a post-test blade tip of the preferred embodiment 1 of the present application;
FIG. 11 is a microscopic view of the tip of a test post-run blade of the preferred embodiment 1 of the present application;
FIG. 12 is a schematic view of a protective jig according to a preferred embodiment 1 of the present application;
fig. 13 is a schematic view of the fixed connection base plate 2 and the mounting plate 3 of the preferred embodiment 1 of the present application.
Reference numerals illustrate:
1. a mounting base; 2. a bottom plate; 3. a mounting plate; 4. a cover plate; 5. a first connector; 6. a second connector; 7. and (5) plugging.
Detailed Description
It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other. The application will be described in detail below with reference to the drawings in connection with embodiments.
FIG. 1 is a schematic view of the inner circle of the outer ring of the turbine of the present application; FIG. 2 is a schematic illustration of a gas turbine rotor blade tip of the present application; FIG. 3 is a microstructure view of a polished blade body of preferred embodiment 1 of the present application; FIG. 4 is a microstructure view of a tip polished state of a preferred embodiment 1 of the present application; FIG. 5 is a microstructure view of a blade body polished state of preferred comparative example 1 of the present application; FIG. 6 is a microstructure view of a tip polished state of a preferred comparative example 1 of the present application; FIG. 7 is a microstructure view of a blade body in a corroded state according to a preferred embodiment 1 of the present application; FIG. 8 is a microstructure view of a tip erosion state of a preferred embodiment 1 of the present application; FIG. 9 is an external view of the trial rear blade body of the preferred embodiment 1 of the present application; FIG. 10 is a view of the appearance of a post-test blade tip of the preferred embodiment 1 of the present application; FIG. 11 is a microscopic view of the tip of a test post-run blade of the preferred embodiment 1 of the present application; FIG. 12 is a schematic view of a protective jig according to a preferred embodiment 1 of the present application; fig. 13 is a schematic view of the fixed connection base plate 2 and the mounting plate 3 of the preferred embodiment 1 of the present application.
According to the high-temperature-resistant hot corrosion coating for the small-size turbine working blade of the aeroengine, the NiCoCrAlYTA coating is sprayed on the blade body and the flange flow path surface, the NiCrAlY bottom layer and the YSZ surface layer are sprayed on the blade tip, the NiCrAlY bottom layer and the YSZ surface layer are adopted for the blade tip, high-temperature protection can be realized, scraping and scrapping of the blade caused by adhesion of the coating can be avoided, and after the YSZ surface layer is adopted for the blade tip, the ceramic coating is not adhered and agglomerated after scraping and grinding, and can be discharged along with airflow, so that scraping and grinding damage of a blade matrix is avoided, and the maintenance cost of the engine is reduced. And the YSZ surface layer can be sprayed again after being removed mechanically. However, the blade body and the blade tip of the existing blade are both coated with the same coating, and because the small-size turbine working blade is in a high-temperature, high-pressure and high-speed environment for a long time, when the coating is damaged, the new turbine working blade can only be replaced, and maintenance cannot be performed.
The turbine rotor blade belongs to a small-size blade, the edge plate of the blade is (15-20) cm multiplied by 8cm, and the blade body height is 20-25 cm.
The NiCoCrAlYTA powder comprises the following components in percentage by mass: 18-28%, cr: 16-25%, al: 4-13%, Y:0.3 to 0.9 percent, ta: 2-5%, the balance being Ni, niCoCrAlYTA powder particle size distribution (wt%): is more than 38 mu m and less than or equal to 15 percent; 5-38 mu m, more than or equal to 80 percent; less than 5 mu m and less than or equal to 5 percent. The test was performed according to GB/T19077 particle size analysis laser diffraction method.
The MCrAlY powder comprises the following components in percentage by mass: 20-25%, al: 8-12%, Y:0.7 to 1.3 percent, and the balance of Ni and unavoidable impurities; the MCrAlY powder particle size distribution is: more than 140 meshes and less than or equal to 1 percent; 140-325 meshes, more than or equal to 90 percent; less than 325 meshes and less than or equal to 9 percent.
The YSZ powder comprises the following components in percentage by mass: zrO (ZrO) 2 +Y 2 O 3 ≥98％，Y 2 O 3 : 6-8%; the YSZ powder particle size distribution is: less than 140 meshes and more than or equal to 99 percent.
In this example, the thickness of the NiCoCrAlYTA coating is 0.04mm to 0.1mm. The thickness of the NiCrAlY bottom layer is 0.02 mm-0.15 mm. The thickness of the YSZ surface layer is 0.1 mm-0.35 mm. The coating needs to meet the requirements of the specified range values, and the protective effect of the coating is reduced when the thickness of the coating is too thin. The NiCrAlY bottom layer also serves as a bonding layer of the YSZ surface layer, and the YSZ surface layer can be peeled off in the use process due to the excessive thinness. If the thickness of the coating is over, the quality of the blade exceeds standard, and the service performance of the engine is affected.
According to another aspect of the application, there is also provided a method for preparing the high temperature hot corrosion resistant coating of a small turbine rotor blade of an aeroengine, comprising the steps of:
s1, protecting a non-spraying part of a blade, and carrying out vacuum plasma spraying on NiCoCrAlYTA powder on the blade body and the flow passage surface of the edge plate to form a NiCoCrAlYTA coating;
s2, removing the protection, and performing diffusion treatment on the blade with the NiCoCrAlYTA coating;
s3, polishing the NiCoCrAlYTA coating of the blade body and the edge plate after the diffusion treatment, and removing the NiCoCrAlYTA coating remained on the surface of the blade tip;
s4, protecting the blade body, the tenon teeth and the edge plate, performing atmospheric plasma spraying on the surface of the blade tip by using NiCrAlY powder to form a NiCrAlY bottom layer, and performing atmospheric plasma spraying on the NiCrAlY bottom layer by using YSZ powder to form a YSZ surface layer;
s5, removing the protection, and performing aging treatment on the blade with the NiCrAlY bottom layer and the YSZ surface layer.
According to the preparation method of the high-temperature-resistant hot corrosion coating of the small-size turbine working blade of the aeroengine, the NiCoCrAlYTA powder is sprayed on the runner surfaces of the blade body and the flange plate to form the NiCoCrAlYTA coating, and then the NiCrAlY powder and the YSZ powder are sprayed on the blade tip to form the NiCrAlY bottom layer and the YSZ surface layer, so that different high-temperature-resistant coatings are sprayed on different parts of the blade, and different spraying technologies are adopted, so that the production cost is reduced, and meanwhile, the service life and reliability of each coating are remarkably improved. As the roughness of the blade body surface coating can influence the air flow in the using process of the engine, the NiCoCrAlYTA coating on the blade body surface needs to be polished. And then removing the NiCoCrAlYTA coating formed on the surface of the blade tip in a grinding mode to ensure that the surface of the blade tip is free of the NiCoCrAlYTA coating. The three coatings are high temperature resistant coatings, the blade body is protected from damage or reduced damage in a high temperature environment, the NiCoCrAlYTA coating is formed by vacuum plasma spraying, the NiCoCrAlYTA coating is compact and free of oxide, the high temperature oxidation resistant effect is good, the blade tip is formed into a NiCrAlY bottom layer and a YSZ surface layer by atmospheric plasma spraying, the high temperature resistance is realized, and the YSZ surface layer after scraping can be removed along with air flow.
In this embodiment, the temperature of the diffusion treatment in step S2 is 900 to 1100 ℃, and the time of the diffusion treatment is 4 to 7 hours. And carrying out diffusion treatment on the blade with the NiCoCrAlYTA coating so as to improve the binding force between the NiCoCrAlYTA coating and the blade body substrate. Based on the DD407 monocrystal material as the blade matrix material, the diffusion treatment temperature is 900-1100 ℃, so that a diffusion layer is formed between the NiCoCrAlYTA coating and the blade matrix, and the coating combination property is provided. However, too high a temperature can result in a change in the texture of the blade matrix material, while affecting the performance of the NiCoCrAlYTa coating.
In this embodiment, the temperature of the aging treatment in step S5 is 600-900 ℃, and the time of the aging treatment is 18-32 hours. And carrying out aging treatment on the blade with the NiCrAlY bottom layer and the YSZ surface layer so as to improve the binding force between the NiCrAlY bottom layer and the blade tip substrate as well as between the NiCrAlY bottom layer and the YSZ surface layer. And (3) carrying out aging treatment on the premise of ensuring that the blade matrix material is not affected, so that the NiCrAlY bottom layer and the blade tip matrix form a diffusion layer, and the bonding property of the blade tip coating and the matrix is provided.
In this embodiment, the specific steps for protecting the blade body and the tenon tooth in step S4 include: the tenon tooth is protected by a protective clamp; the blade body is protected by adopting a high-temperature-resistant protective adhesive tape.
As shown in fig. 12 and 13, in this embodiment, the protection fixture includes a mounting base 1, a bottom plate 2 disposed on the mounting base 1, a groove structure for accommodating a blade edge plate is disposed on the bottom plate 2, a mounting plate 3 disposed on the mounting base 1 and stacked on the bottom plate 2, a mortise for matching with the blade tenon is circumferentially disposed on the mounting plate 3, a cover plate 4 disposed on the mounting base 1 and covered on the mounting plate 3, the bottom plate 2 and the cover plate 4 are matched for the protection edge plate, a first connecting member 5 for fixedly connecting the bottom plate 2 and the mounting plate 3, and a second connecting member 6 for fixedly connecting the mounting plate 3 and the cover plate 4. The first connecting member 5 is a hexagon socket screw. The second connecting member 6 is a hexagon socket screw.
Preferably, a plurality of mortises are adopted, and the mortises are distributed at intervals along the circumferential direction of the mounting plate 3; the groove structures are multiple, and the groove structures are arranged in one-to-one correspondence with the mortises; a plug 7 for plugging the mortise is also included. In actual production, the mortises and the groove structures are provided with 30-60, so that spraying of at least 30-60 blade tips can be realized on the protective clamp at one time, but when the number of the blade tips to be sprayed is smaller than that of the mortises, the protective clamp is rotated circumferentially to prevent the sprayed NiCrAlY powder and YSZ powder from entering the groove structures or the mortises to form a coating so as to pollute the protective clamp, and therefore, the plug 7 is designed to plug the part of the protective clamp where the blade is not installed. The plug 7 comprises a tenon tooth structure matched with the tenon groove and a boss matched with the groove structure, so that the tenon groove on the mounting plate 3 and the groove structure on the bottom plate 2 are plugged.
In the embodiment, after a blade body, a tenon tooth and a flange plate are protected, a protection clamp with blades is arranged on a rotary table, the rotary table rotates along an axial center line, the rotary table rotates at 80-150 rpm, a plasma spray gun moves up and down along a direction parallel to the center line to spray NiCrAlY powder until the tips of all the blades form a NiCrAlY bottom layer; the turntable rotates along the axial center line, the rotating speed of the turntable is 80 rpm-150 rpm, and the plasma spray gun moves up and down along the direction parallel to the center line to spray YSZ powder until YSZ surface layers are formed on all the NiCrAlY bottom layers. The special high protective clamp is adopted for carrying out atmospheric plasma spraying, so that the position of the plasma spray gun relative to the blade tip of each blade is unchanged when the blade tip of the blade is sprayed, the consistency of the blade tip spraying of each blade is ensured, and the protection and clamping of the tenon tooth and the flange plate are also considered.
In this embodiment, at least two layers of the high-temperature protective tape are used. The high-temperature protective adhesive tape is positioned at the junction of the blade body and the blade tip and presents an oblique angle of 40-60 degrees. In order to prevent the high-temperature-resistant protective adhesive tape from being burnt in the spraying process, at least two layers of high-temperature-resistant protective adhesive tapes are required to be adhered to the blade body, and the high-temperature protective adhesive tape at the junction of the blade body and the blade tip coating is required to be in an oblique angle of 40-60 degrees so as to prevent the blade tip coating from forming a bridge with the high-temperature protective adhesive tape, thereby avoiding the peeling of the coating when the high-temperature protective adhesive tape is taken down. After the rotary table rotates for a circle, after finishing YSZ surface layer spraying, firstly taking out the blade from the protective clamp, then removing the high-temperature protective adhesive tape on the surface of the blade body, adopting the diamond file to lightly press the high-temperature protective adhesive tape to coat, separating the adhesive tape from the coat, then tearing off the high-temperature protective adhesive tape along the blade body to tenon tooth direction, and lightly rubbing the junction of the blade tip and the blade body along the blade body to tenon tooth direction by using oilstone after the high-temperature protective adhesive tape is completely removed, thereby ensuring smooth transition of the coat.
Examples
Example 1
A high temperature hot erosion resistant coating for a small turbine rotor blade of an aircraft engine comprising: a NiCoCrAlYTA coating with the thickness of 0.08mm is sprayed on the blade body and the blade edge plate flow surface, a NiCrAlY bottom layer with the thickness of 0.08mm and a YSZ surface layer with the thickness of 0.2mm are sprayed on the blade tip.
The preparation method of the high-temperature-resistant hot corrosion coating of the small-size turbine working blade of the aero-engine comprises the following steps:
s1, protecting non-spraying parts of the blade by adopting a high-temperature protective adhesive tape, and carrying out vacuum plasma spraying on NiCoCrAlYTA powder on the blade body and the edge plate flow passage surface, wherein the spraying process comprises the following steps of: the vacuum degree is below 85mbar, the spraying distance is 200-300, the current is 650-750A, and a NiCoCrAlYTA coating with the thickness of 0.08mm is formed;
s2, removing the high-temperature protective tape, and performing diffusion treatment on the blade with the NiCoCrAlYTA coating, wherein the diffusion treatment temperature is 1100 ℃, and the diffusion treatment time is 5 hours;
s3, polishing the NiCoCrAlYTA coating on the surface of the blade body after the diffusion treatment, and removing the NiCoCrAlYTA coating remained on the surface of the blade tip by adopting a grinding processing mode;
s4, the blade body is protected by adopting at least two layers of high-temperature-resistant protective adhesive tapes, all 30 blades are arranged in the mortises of the installation plate 3 of the protective clamp through the tenons, the mortises of the installation plate 3 are 50, the mortises of the non-installed blades are plugged by adopting plugs 7, the cover plate 4 is covered, the cover plate 4 is fixed by the inner hexagonal cylindrical screw, the protective clamp with the blades is arranged on the turntable,
after the blade body, the tenon teeth and the flange plate are protected, a protective clamp with blades is arranged on a rotary table, the rotary table rotates along an axial center line, the rotary table rotates at 80 rpm-150 rpm, a plasma spray gun moves up and down along a direction parallel to the center line to spray NiCrAlY powder, and the spraying process comprises the following steps: the flow rate (SCFH) of argon gas is 150+/-10, the flow rate (SCFH) of hydrogen gas is 10+/-1, the gas carrying capacity (SCFH) is 10-15, the current (A) is 500+/-50, the powder feeding amount (g/min) is 40+/-5, the spraying distance (mm) is 150+/-10, and the NiCrAlY bottom layer is formed on the tips of all blades; the rotary table rotates along the axial center line, the rotating speed of the rotary table is 80 rpm-150 rpm, the plasma spray gun moves up and down along the direction parallel to the center line to spray YSZ powder, and the spraying process comprises the following steps: the flow rate of argon gas (SCFH) is 150+/-10, the flow rate of hydrogen gas (SCFH) is 10.5+/-1, the carrier gas quantity (SCFH) is 10-15, the current (A) is 500+/-50, the powder feeding quantity (g/min) is 28+/-5, the spraying distance (mm) is 100+/-10, and a YSZ surface layer is formed on all NiCrAlY bottom layers;
s5, firstly taking the blade out of a protective clamp, then removing the high-temperature protective adhesive tape on the surface of the blade body, adopting a diamond file to light the pressure and high-temperature protective adhesive tape to coat the blade body, separating the adhesive tape from the coat, then tearing off the high-temperature protective adhesive tape along the direction from the blade body to the tenon tooth, after the high-temperature protective adhesive tape is removed completely, lightly rubbing the junction between the blade tip and the blade body along the direction from the blade body to the tenon tooth by using oilstone, and then carrying out aging treatment on the blade with the NiCrAlY bottom layer and the YSZ surface layer, wherein the temperature of the aging treatment is 800 ℃, and the time of the aging treatment is 24 hours.
Comparative example 1
A high temperature hot erosion resistant coating for a small turbine rotor blade of an aircraft engine comprising: and a NiCoCrAlYTA coating with the thickness of 0.1mm is sprayed on the blade body, the blade edge flow surface and the blade tip.
The preparation method of the high-temperature-resistant hot corrosion coating of the small-size turbine working blade of the aero-engine comprises the following steps:
the non-spraying part of the blade is protected by adopting a high-temperature protective adhesive tape, and NiCoCrAlYTA powder is subjected to vacuum plasma spraying on the blade body, the edge plate runner surface and the blade tip to form a NiCoCrAlYTA coating with the thickness of 0.1mm.
The resulting leaves of example 1 and comparative example 1 were subjected to metallographic sampling, the microstructure in a polished state was observed, and the leaves after metallographic sampling of example 1 were subjected to corrosion with weak acid, and the microstructure in a corroded state was observed.
As shown in FIG. 3, the polished microstructure of example 1 shows that the NiCoCrAlYTA coating of the blade body has a thickness of 0.08mm, a porosity of less than 2%, unmelted particles of less than 2%, phi of less than 10 μm, and the blade body coating is mechanically polished to form a flat surface with less airflow resistance during engine use. As shown in FIG. 4, the thickness of the coating of the tip NiCrAlY bottom layer and the YSZ surface layer is 0.05-0.08 mm, the porosity is less than 6-8%, the unmelted grain is less than 3-5%, the phi is less than 0.045 mu m, the thickness of the coating of the YSZ surface layer is 0.05-0.08 mm, and the porosity is less than 6-8%.
As shown in FIGS. 7 and 8, the example 1 is a microstructure of the etched state, wherein the blade body NiCoCrAlYTA coating and the base member have a 0.01mm diffusion layer, and the blade tip NiCrAlY base layer and the base member have a 0.005mm diffusion layer.
As shown in fig. 5 and 6, which are the microstructure diagrams of the polished state of comparative example 1, the surface roughness of the coating layer was large, and the resistance to the flow of air during the use of the engine was large.
The aeroengine small-size turbine rotor blade prepared in the above example 1 is equivalently tested for 1000 hours, the appearance of the blade body coating and the appearance of the blade tip coating after test are shown in fig. 9 and 10, and the microstructure of the blade tip coating is shown in fig. 11.
As shown in fig. 9, 10 and 11, the coating of the blade body and the blade tip is not dropped after trial run, and the coating is complete and accords with the service performance of the engine.
The above description is only of the preferred embodiments of the present application and is not intended to limit the present application, but various modifications and variations can be made to the present application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.
Claims (8)
1. The preparation method of the high-temperature-resistant hot corrosion coating of the small-size turbine rotor blade of the aeroengine is characterized by comprising the following steps of:
s1, protecting a non-spraying part of a blade, and carrying out vacuum plasma spraying on NiCoCrAlYTA powder on the blade body and the runner surface of the edge plate to form a NiCoCrAlYTA coating;
s2, removing the protection, and performing diffusion treatment on the blade with the NiCoCrAlYTA coating, wherein the temperature of the diffusion treatment is 900-1100 ℃, and the time of the diffusion treatment is 4-7 hours;
s3, polishing the NiCoCrAlYTA coating of the blade body and the edge plate after the diffusion treatment, and removing the NiCoCrAlYTA coating remained on the surface of the blade tip;
s4, protecting the blade body, the tenon teeth and the edge plate, performing atmospheric plasma spraying on the surface of the blade tip by using NiCrAlY powder to form a NiCrAlY bottom layer, and performing atmospheric plasma spraying on the NiCrAlY bottom layer by using YSZ powder to form a YSZ surface layer;
s5, removing the protection, and performing aging treatment on the blade with the NiCrAlY bottom layer and the YSZ surface layer, wherein the temperature of the aging treatment is 600-900 ℃, and the aging treatment time is 18-32 h.
2. The method for preparing the high-temperature-resistant hot corrosion coating of the small-size turbine rotor blade of the aeroengine according to claim 1, wherein the method comprises the steps of,
the specific steps for protecting the blade body and the tenon tooth in the step S4 comprise the following steps:
the tenon tooth is protected by a protective clamp;
the blade body is protected by adopting a high-temperature-resistant protective adhesive tape.
3. The method for preparing the high-temperature-resistant hot corrosion coating of the small-size turbine rotor blade of the aeroengine according to claim 2, wherein,
the protective clamp comprises a mounting base (1), a bottom plate (2) arranged on the mounting base (1), a groove structure for accommodating a blade edge plate is arranged on the bottom plate (2), a mounting plate (3) arranged on the mounting base (1) and stacked on the bottom plate (2), a mortice groove matched with a blade tenon tooth is circumferentially arranged on the mounting plate (3), a cover plate (4) arranged on the mounting base (1) and covered on the mounting plate (3) is arranged, the bottom plate (2) is matched with the cover plate (4) to be used for protecting the edge plate, and the first connecting piece (5) of the bottom plate (2) and the mounting plate (3) is used for being fixedly connected with the second connecting piece (6) of the mounting plate (3) and the cover plate (4).
4. A method for producing a high-temperature hot-corrosion-resistant coating for small-sized turbine rotor blades of an aircraft engine according to claim 3,
the mortises are arranged at intervals along the circumferential direction of the mounting plate (3);
the groove structures are arranged in a plurality of ways, and the groove structures are arranged in one-to-one correspondence with the mortises;
the device also comprises a plug (7) for plugging the mortise.
5. The method for preparing the high-temperature-resistant hot corrosion coating of the small-size turbine rotor blade of the aeroengine according to claim 4, wherein,
after the blade body, the tenon teeth and the edge plates are protected, a protective clamp with blades is arranged on a rotary table, the rotary table rotates along an axial center line, the rotary table rotates at 80-150 rpm, a plasma spray gun moves up and down along a direction parallel to the center line to spray NiCrAlY powder until the tips of all the blades form a NiCrAlY bottom layer;
the turntable rotates along the axial center line, the rotating speed of the turntable is 80 rpm-150 rpm, and the plasma spray gun moves up and down along the direction parallel to the center line to spray YSZ powder until YSZ surface layers are formed on all the NiCrAlY bottom layers.
6. The method for preparing the high-temperature-resistant hot corrosion coating of the small-size turbine rotor blade of the aeroengine according to claim 2, wherein,
the high-temperature protective adhesive tape adopts at least two layers;
the high-temperature protective glue is positioned at the junction of the blade body and the blade tip and presents an oblique angle of 40-60 degrees.
7. A high-temperature hot corrosion resistant coating for a small-sized turbine rotor blade of an aeroengine manufactured by the manufacturing method according to any one of claims 1 to 6 is characterized in that,
comprising the following steps: a NiCoCrAlYTA coating sprayed on the blade body and the blade edge plate flow surface, and a NiCrAlY bottom layer and a YSZ surface layer sprayed on the blade tip.
8. A high temperature hot corrosion resistant coating for small turbine rotor blades of an aircraft engine as set forth in claim 7,
the thickness of the NiCoCrAlYTA coating is 0.04-0.1 mm;
the thickness of the NiCrAlY bottom layer is 0.02 mm-0.15 mm;
the thickness of the YSZ surface layer is 0.1 mm-0.35 mm.
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| CN202111530168.XA CN114150256B (en) | 2021-12-14 | 2021-12-14 | High-temperature-resistant hot corrosion coating for small-sized turbine working blade of aero-engine |
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| WO2005068784A1 (en) * | 2004-01-13 | 2005-07-28 | Mtu Aero Engines Gmbh | Turbo machine blade and method for producing armour plating on the tips of turbo machine blades |
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| CN109440046A (en) * | 2018-11-30 | 2019-03-08 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine and gas turbine blades thermal barrier coating and preparation method thereof |
| CN111957464A (en) * | 2020-06-30 | 2020-11-20 | 中国航发南方工业有限公司 | Blade shroud spraying protection clamp and method for turbine blade |
| WO2021233496A1 (en) * | 2020-05-18 | 2021-11-25 | MTU Aero Engines AG | Blade for a turbomachine, having blade-tip armor plating and anti-erosion layer, and method for producing said blade |
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2021
- 2021-12-14 CN CN202111530168.XA patent/CN114150256B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2005068784A1 (en) * | 2004-01-13 | 2005-07-28 | Mtu Aero Engines Gmbh | Turbo machine blade and method for producing armour plating on the tips of turbo machine blades |
| CN105289881A (en) * | 2015-12-03 | 2016-02-03 | 中国南方航空工业(集团)有限公司 | Spraying protection clamp for turbine blades |
| CN109440046A (en) * | 2018-11-30 | 2019-03-08 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of aero-engine and gas turbine blades thermal barrier coating and preparation method thereof |
| WO2021233496A1 (en) * | 2020-05-18 | 2021-11-25 | MTU Aero Engines AG | Blade for a turbomachine, having blade-tip armor plating and anti-erosion layer, and method for producing said blade |
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