CN115466912B - Surface enhancement processing method for titanium alloy leaf disc blade and application of method - Google Patents
Surface enhancement processing method for titanium alloy leaf disc blade and application of method Download PDFInfo
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
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- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
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- C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
- C22C32/001—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with only oxides
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- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F3/00—Changing the physical structure of non-ferrous metals or alloys by special physical methods, e.g. treatment with neutrons
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- 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
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- 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
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/12—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
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Abstract
The application relates to the technical field of machining, in particular to a surface enhancement machining method of a titanium Jin Shepan blade and application of the method; the method improves crack propagation generated in the earlier processing of the blade surface of the blade disc, reduces residual stress in the blade surface, and utilizes alloy powder and Gd 2 Zr 2 O 7 The synergistic effect of the powder and the hard ceramic powder enhances the performance of the blade of the impeller blade, and the processed titanium Jin Shepan blade has the characteristics of excellent corrosion resistance, high temperature resistance and abrasion resistance and stress resistance, so that the surface enhancement processing method can be used for processing and manufacturing the titanium Jin Shepan blade in an aeroengine.
Description
Technical Field
The application relates to the technical field of machining, in particular to a surface enhancement machining method of a titanium Jin Shepan blade and application of the method.
Background
The blade disc blades of the modern aviation turbine engine bear higher centrifugal load, aerodynamic load, high temperature and vibration alternating load when in work, meanwhile, a large number of blade disc blades in the middle service period can be scrapped due to the fact that the blade disc blades in the middle service period do not reach the designed service period due to the impact of foreign matters in an air inlet channel of the engine, and the high reliability and the high temperature resistance are the most basic requirements of the modern aviation engine on parts of the modern aviation engine. For the blade disc blades made of titanium alloy materials, the problems of large quantity, long size, weak rigidity, large bending and twisting, difficult material cutting, easy deformation, cutter withdrawal, crack and the like occur in the processing; in the key manufacturing technology of the advanced aeroengine, the surface modification plays a remarkable role in the aspects of wear resistance, high temperature, protection, heat insulation, sealing, flame retardance and the like of key parts of the aeroengine, and becomes one of the core technologies of the aeropower device. The multifunctional modification layer is prepared on the surface of the blade of the aeroengine titanium alloy by adopting a plasma spraying technology, so that the service life of the engine can be effectively prolonged, but the high temperature resistance, corrosion resistance, wear resistance and stress resistance of the existing surface modification layer are still insufficient, and a large improvement space exists.
CN101912990B discloses a milling vibration damping method for blisk blades, in which molten mixtures of crystalline paraffin, liquid wax, rosin resin and hindered phenol antioxidants are filled to eliminate chatter marks generated at blade tip positions during milling, and roughness of blade surfaces is reduced, but the wax filling process is complicated, so that the processing efficiency of blisk blades is low, and meanwhile, certain damage is easily generated to a machine tool after the removed wax enters the machine tool.
CN111250368A discloses a preparation process of a polyphenyl ester sealing modification layer for aeroengine casing parts, although the polyphenyl ester modification layer in the preparation process has high hardness and low pore content, the corrosion resistance and the high temperature resistance of the polyphenyl ester modification layer are still unknown.
Disclosure of Invention
In order to solve the technical problems, the application provides a surface enhancement processing method of a titanium Jin Shepan blade, which comprises the following steps:
s1, cutting and milling: rough milling, semi-finish milling and finish milling;
s2, laser strengthening;
s3, shot blasting;
s4, surface modification.
Further, the rough milling allowance in the step S1 is 1-4mm, the semi-finish milling allowance is 0.2-1mm, and the finish milling allowance is 0.1-0.2mm.
Further, the rough milling allowance in the step S1 is 1-2mm, the semi-finish milling allowance is 0.2-0.6mm, and the finish milling allowance is 0.1-0.2mm.
The laser strengthening technology is utilized to carry out surface treatment on the cut and milled blade of the blade disc, so that the deformation of the blade disc is reduced, possible cracks are made up, and the service life of the blade disc is prolonged.
Further, the absorption layer in the step S2 of laser strengthening is aluminum foil, the laser energy is 21-25J, the diameter of a light spot is 3-5mm, and the overlapping rate of the light spot is 10% -15%.
Further, the shot in the step S3 shot blasting is one of cast steel shot, white corundum sand, glass shot and ceramic shot.
Further, in the step S3 shot blasting, the shot is cast steel shot.
Further, in the step S3 shot blasting, the shot diameter is 0.2-0.4mm, the spraying pressure is 0.5-0.8MPa, and the coverage rate is 100-300%.
Preferably, the pellet diameter is 0.3mm, the injection pressure is 0.65MPa, and the coverage rate is 200%.
Further, after the shot blasting in the step S3, the surface roughness of the blade of the blisk is kept to be 0.8-1.2 mu m.
Further, after the shot blasting in the step S3, the surface roughness of the blade of the blisk is kept to be 0.8-1.0 mu m.
Preferably, after the shot blasting in the step S3, when the surface roughness of the blade of the blisk is 0.9 mu m, the processed blade of the blisk has the best gas heat corrosion resistance rate and the maximum bending strength which is 0.46 g/(m) respectively 2 H) and 182.0MPa; the speculation is: at the moment, in the step S4, the binding force between the modification layer and the leaf disc blade is strongest, and the compactness of the modification layer is good; if the surface roughness of the blade of the impeller is too small, the modification layer is not easy to adhere to the surface of the blade of the impeller; however, when the roughness is too large, relatively deep pits can appear locally, and the paint is influenced by the action of an electric field and is easily concentrated at the edge of the concave part with lower resistance during spraying, so that gaps are generated in the modification layer, the modification layer is uneven in distribution and insufficient in compactness, and the enhancement effect on the surface of the blade of the bladed disk is further reduced.
Further, the surface modification in the step S4 adopts a plasma spraying technology, and the modification material is prepared from alloy powder and Gd 2 Zr 2 O 7 Powder and hard ceramic powder.
Further, the finishing material in the step S4 is as follows, based on the total weight of the material: 18-25% of alloy powder, gd 2 Zr 2 O 7 25% -35% of powder, and the total amount of the hard ceramic powder is 100%. When the alloy powder is excessively added, the thermal expansion coefficient of the alloy powder is excessively different from that of other components in the modification material, so that the modification layer is easy to generate deformation phenomena such as expansion and the like at high temperature, and Gd 2 Zr 2 O 7 The addition of the powder and the hard ceramic powder to a certain extent can improve the hardness, corrosion resistance and high temperature resistance of the modification layer, but when the addition amount is too large, the fracture toughness of the modification layer is poorThe crack is easy to be unstable and expand when being impacted by external force, thereby reducing the reinforcing performance of the modification layer on the titanium alloy blade disc and shortening the service life of the titanium alloy blade disc.
Preferably, the finishing material is: alloy powder 22%, gd 2 Zr 2 O 7 30% of powder and 48% of hard ceramic powder.
Further, the alloy powder is: 15% -25% of Ni, 5% -10% of Nb, 18% -25% of Cr, 13% -17% of W, 8% -20% of Ti, 15% -22% of C and 0.5% -1.5% of Ta.
Inside the finishing layer and the contact surface with the titanium alloy blade, stable NbC or Nb is formed between the metals Nb and C 4 C 3 The high-temperature stability of the whole decorative layer and the titanium alloy leaf disc blade can be improved; the Ni-Cr alloy in the alloy material can improve the high-temperature oxidation corrosion resistance of the modification layer, the Ni-W alloy can increase the strong reducing medium resistance of the modification layer, and the Ni-Cr-W and Ti-Ta alloy can increase the acid corrosion resistance of the modification layer; through the synergistic effect of all metals in the alloy, the compactness of the prepared modification layer and the binding force of the modification layer and a metal matrix are enhanced, and the wear resistance, corrosion resistance and mechanical strength of the modification layer are further enhanced.
Preferably, the alloy powder is: 20% of Ni, 8% of Nb, 23% of Cr, 15% of W, 14% of Ti, 19% of C and 1% of Ta; the modified layer has higher hardness for metals Cr and Ni, and has larger plastic deformation and no stress resistance when the addition amount is too large, and is easy to promote precipitation of harmful phases when the content of refractory metal W is too large, so that the stability and mechanical strength of the modified layer are reduced.
Further, the spraying thickness of the modified material in the step S4 is 80-130 μm.
Preferably, the thickness of the coating of the finishing material in the step S4 is 110 μm.
Further, in the plasma spraying technology of step S4, the spraying parameters are as follows: argon flow is 40-55L/min, hydrogen flow is 10-20L/min, current is 500-650A, powder feeding rate is 35-45g/min, spraying distance is 130-140mm, and spraying angle is 45-90 degrees.
In a preferred embodiment, when the spraying parameters of step S4 are: argon flow 50L/min, hydrogen flow 15L/min, current 580A, powder feeding rate 40g/min, spraying distance 135mm, and spraying angle 45-90 degrees to uniformly modify the gaps of the blades of the impeller, wherein the modified blades have optimal gas hot corrosion resistance due to good compactness of the modification layer. The reasons may be: when the powder feeding speed is too high, part of powder cannot be melted sufficiently, particles possibly can be generated to enable spraying to be uneven, and when the powder feeding speed is too low, part of raw materials of the coating are oxidized seriously; in addition, when the spraying distance is too large, air holes are generated when the temperature of the coating is reduced, the binding force between the modification layer and the metal matrix is also reduced, part of the coating can be sputtered out to cause low spraying efficiency, and when the spraying distance is too small, the spraying is uneven.
The beneficial effects are that:
1. the method comprises the steps of cutting and milling, laser strengthening, shot blasting and surface modification, wherein crack growth generated on the surface of the blade disc in the cutting and milling process is improved through the laser strengthening and the shot blasting, residual stress is reduced, mechanical properties of the blade disc are further enhanced through the surface modification, and the processing method also reduces operation complexity of the front-stage cutting and milling of the blade disc.
2. The surface roughness of the blisk blade after shot blasting is limited to be 0.8-1.2 mu m, so that the modification layer has good compactness, the binding force between the modification layer and the blisk blade is enhanced, and the processing method has excellent performance enhancement effect on the blisk blade.
3. The finishing material of the application consists of alloy powder and Gd 2 Zr 2 O 7 Powder and hard ceramic powder composition, gd 2 Zr 2 O 7 The use of the alloy powder can improve the corrosion resistance of the modification layer to molten silicate, the addition of the hard ceramic powder further improves the bearing capacity and frictional wear performance of the modification layer, the metal particles in the alloy powder can reduce the difference of the thermal expansion coefficients of the contact surfaces of the modification layer containing ceramic material and the titanium alloy blade disc, and the heat between the substrate and the modification layer is effectively improvedMismatch between physical and mechanical properties; by utilizing the synergistic effect of the three, the processed titanium Jin Shepan blade has excellent performances of corrosion resistance, high temperature resistance and abrasion resistance and stress resistance, so that the surface enhancement processing method can be used for processing and manufacturing the titanium Jin Shepan blade in an aeroengine.
4. The composition of the alloy powder is limited in this application to: 15% -25% of Ni, 5% -10% of Nb, 18% -25% of Cr, 13% -17% of W, 8% -20% of Ti, 15% -22% of C and 0.5% -1.5% of Ta. The mechanical strength and the high-temperature corrosion resistance of the surface-modified blisk blade are further improved by utilizing the synergistic effect of the components.
Detailed Description
Examples
Example 1
A surface enhancement processing method of a titanium alloy leaf disc blade comprises the following steps:
s1, cutting and milling: rough milling, semi-finish milling and finish milling;
the five-axis linkage numerical control milling technology is adopted to cut and mill the titanium Jin Shepan blade, the milling cutter adopts a superhard conical neck ball end mill (purchased from MIUMI-VINA company, model KTBL-2), spiral cutting is carried out along a preset track, rough milling allowance is 2mm, semi-finish milling allowance is 0.5mm, and finish milling allowance is 0.15mm.
S2, laser strengthening;
the leaf disc blade is fixed on a machine tool for laser strengthening, wherein the absorption layer is aluminum foil, the laser energy is 23J, the diameter of a light spot is 4mm, and the overlapping rate of the light spot is 13%.
S3, shot blasting;
cast steel shots with the diameter of 0.3mm are adopted, the spraying pressure is 0.65MPa, the coverage rate is 200%, a roughness tester (Sanfeng SJ-410 high-precision tester in Japan) is used for testing the surface roughness of the blade of the impeller, and the surface roughness of the blade of the impeller after shot blasting is 0.9 mu m.
S4, surface modification;
the surface modification of the titanium alloy leaf disc blade is carried out by adopting a plasma spraying technology, and the spraying parameters are as follows: argon flow 50L/min, hydrogen flow 15L/min, current 580A, powder feeding rate 40g/min, spraying distance 135mm, and spraying angle within 45-90 degrees so that the gaps of the blades of the leaf disk are uniformly modified; after the spraying was completed, the parts were dried in an oven at 60 ℃ and then kept at 180 ℃ for 1.5 hours to cure. The thickness of the material modified on the surface of the titanium Jin Shepan blade is 110 mu m.
The finishing material comprises the following components in percentage by weight: alloy powder 22%, gd 2 Zr 2 O 7 30% of powder and 48% of hard ceramic powder.
The alloy powder comprises the following components in percentage by weight: 20% of Ni, 8% of Nb, 23% of Cr, 15% of W, 14% of Ti, 19% of C and 1% of Ta.
Example 2
A surface enhancement processing method of a titanium alloy leaf disc blade comprises the following steps:
s1, cutting and milling: rough milling, semi-finish milling and finish milling;
the five-axis linkage numerical control milling technology is adopted to cut and mill the titanium Jin Shepan blade, the milling cutter adopts a superhard conical neck ball end mill (purchased from model KTBL-2 of MIUMI-VINA company) to carry out spiral cutting along a preset track, the rough milling allowance is 4mm, the semi-finish milling allowance is 1mm, and the finish milling allowance is 0.2mm.
S2, laser strengthening;
the leaf disc blade is fixed on a machine tool for laser strengthening, wherein the absorption layer is aluminum foil, the laser energy is 21J, the diameter of a light spot is 5mm, and the overlapping rate of the light spot is 15%.
S3, shot blasting;
cast steel shots with the diameter of 0.2mm are adopted, the spraying pressure is 0.5MPa, the coverage rate is 100%, a roughness tester (Sanfeng SJ-410 high-precision tester in Japan) is used for testing the surface roughness of the blade of the impeller, and the surface roughness of the blade of the impeller after shot blasting is 0.8 mu m.
S4, surface modification;
the surface modification of the titanium alloy leaf disc blade is carried out by adopting a plasma spraying technology, and the spraying parameters are as follows: argon flow 40L/min, hydrogen flow 10L/min, current 650A, powder feeding rate 35g/min, spraying distance 130mm, and spraying angle within 45-90 degrees so that the gaps of the blades of the leaf disk are uniformly modified; after the spraying, the parts were dried in an oven at 60 ℃ and then kept at 180 ℃ for 2 hours to cure. The thickness of the material modified on the surface of the titanium Jin Shepan blade is 80 mu m.
The finishing material comprises the following components in percentage by weight: alloy powder 25%, gd 2 Zr 2 O 7 35% of powder and 40% of hard ceramic powder.
The alloy powder comprises the following components in percentage by weight: 15% of Ni, 10% of Nb, 25% of Cr, 13% of W, 20% of Ti, 16.5% of C and 0.5% of Ta.
Example 3
A surface enhancement processing method of a titanium alloy leaf disc blade comprises the following steps:
s1, cutting and milling: rough milling, semi-finish milling and finish milling;
the five-axis linkage numerical control milling technology is adopted to cut and mill the titanium Jin Shepan blade, the milling cutter adopts a superhard conical neck ball end mill (purchased from model KTBL-2 of MIUMI-VINA company) to carry out spiral cutting along a preset track, the rough milling allowance is 1mm, the semi-finish milling allowance is 0.2mm, and the finish milling allowance is 0.1mm.
S2, laser strengthening;
the leaf disc blade is fixed on a machine tool for laser strengthening, wherein the absorption layer is aluminum foil, the laser energy is 25J, the diameter of a light spot is 3mm, and the overlapping rate of the light spot is 10%.
S3, shot blasting;
cast steel shots with the diameter of 0.4mm are adopted, the spraying pressure is 0.8MPa, the coverage rate is 300%, a roughness tester (Sanfeng SJ-410 high-precision tester in Japan) is used for testing the surface roughness of the blade of the impeller, and the surface roughness of the blade of the impeller after shot blasting is 1.2 mu m.
S4, surface modification;
the surface modification of the titanium alloy leaf disc blade is carried out by adopting a plasma spraying technology, and the spraying parameters are as follows: argon flow 55L/min, hydrogen flow 20L/min, current 500A, powder feeding rate 45g/min, spraying distance 140mm, and spraying angle within 45-90 degrees so that the gaps of the blades of the leaf disk are uniformly modified; after the spraying, the parts were dried in an oven at 60 ℃ and then kept at 200 ℃ for 1 hour to cure. The thickness of the material modified on the surface of the titanium Jin Shepan blade is 130 mu m.
The finishing material comprises the following components in percentage by weight: alloy powder 18%, gd 2 Zr 2 O 7 25% of powder and 57% of hard ceramic powder.
The alloy powder comprises the following components in percentage by weight: 25% of Ni, 6.5% of Nb, 19% of Cr, 17% of W, 11% of Ti, 20% of C and 1.5% of Ta.
Comparative example 1
Consistent with example 1, the difference is that: the finishing material comprises the following components in percentage by weight: alloy powder 40%, gd 2 Zr 2 O 7 30% of powder and 30% of hard ceramic powder.
Comparative example 2
Consistent with example 1, the difference is that: the alloy powder comprises the following components in percentage by weight: 43% of Ni, 8% of Nb, 21% of Cr, 13% of Ti and 15% of C.
Comparative example 3
Consistent with example 1, the difference is that: the surface roughness of the blade disc after shot blasting is 1.8 mu m, and in the plasma spraying technology in the step S4, the powder feeding speed is 60g/min, and the spraying distance is 135mm.
Gd in the above examples 2 Zr 2 O 7 The powder was purchased from Wangdakang New Material Co., shenzhen City; the hard ceramic powder is purchased from silver arrow industry products manufacturing company, model number Ni30AA; the alloy powder is self-made, and the self-making method comprises the following steps: the alloy powder is prepared by mixing the components according to the weight ratio, melting at 1300 ℃, then introducing into an atomizer for atomization, cooling and solidifying in a natural state, and drying the alloy powder in a baking oven at 280 ℃ for 2 hours.
The performance test method comprises the following steps:
1. resistance to hot gas corrosion: the test is carried out according to the aeronautical industry standard HB 7740-2017 gas hot corrosion test method, and the surface corrosion condition is observed visually.
2. Bending performance test: flexural strength was measured as specified in HB 5434.6-2004. Performance test results:
TABLE 1
Claims (5)
1. The surface enhancement processing method of the titanium alloy leaf disc blade is characterized by comprising the following steps of:
s1, cutting and milling: rough milling, semi-finish milling and finish milling;
s2, laser strengthening;
s3, shot blasting;
s4, surface modification;
in the step S3, the pellet diameter is 0.2-0.4mm, the spraying pressure is 0.5-0.8MPa, and the coverage rate is 100% -300%;
after the shot blasting in the step S3, keeping the surface roughness of the blade disc to be 0.8-1.2 mu m;
the surface modification in the step S4 adopts a plasma spraying technology, and the modification material is prepared from alloy powder and Gd 2 Zr 2 O 7 Powder and hard ceramic powder;
the modified materials in the step S4 are as follows, based on the total weight of the materials: 18-25% of alloy powder, gd 2 Zr 2 O 7 25% -35% of powder, wherein the total amount of the hard ceramic powder is 100%;
the alloy powder comprises the following components in percentage by weight: 15% -25% of Ni, 5% -10% of Nb, 18% -25% of Cr, 13% -17% of W, 8% -20% of Ti, 15% -22% of C and 0.5% -1.5% of Ta.
2. The surface enhancement processing method of a titanium alloy leaf disc blade according to claim 1, wherein in the step S2, the laser energy is 21-25J, the spot diameter is 3-5mm, and the spot overlap ratio is 10% -15%.
3. The method for surface strengthening treatment of a titanium alloy blisk blade according to claim 1, wherein the coating thickness of the finishing material is 80-130 μm.
4. The surface strengthening processing method of the titanium alloy leaf disc blade according to claim 3, wherein in the plasma spraying technology of the step S4, the powder feeding speed is 35-45g/min, and the spraying distance is 130-140mm.
5. The surface enhancing method for a titanium alloy blisk blade according to any one of claims 1 to 4, wherein the surface enhancing method is applicable to the manufacture of titanium Jin Shepan blades in aeroengines.
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| EP1783248A1 (en) * | 2005-11-04 | 2007-05-09 | Siemens Aktiengesellschaft | Two-layer thermal barrier coating system containing a pyrochlore phase |
| US10041361B2 (en) * | 2014-10-15 | 2018-08-07 | General Electric Company | Turbine blade coating composition |
| CN106757007B (en) * | 2016-12-30 | 2019-07-05 | 无锡透平叶片有限公司 | A kind of fan blade and preparation method thereof |
| CN107866743A (en) * | 2017-11-29 | 2018-04-03 | 无锡透平叶片有限公司 | A kind of titanium alloy blade and its processing method |
| CN110643930A (en) * | 2019-11-15 | 2020-01-03 | 河北工业大学 | Preparation method of composite thermal barrier coating resistant to high temperature CMAS and rainwater corrosion |
| CN111304578B (en) * | 2020-02-28 | 2022-07-01 | 中国人民解放军国防科技大学 | Heat insulation/radar wave absorption integrated composite coating, titanium alloy material with composite coating coated on surface and preparation method of titanium alloy material |
| CN112404913B (en) * | 2020-10-13 | 2022-11-15 | 中国航发沈阳黎明航空发动机有限责任公司 | Titanium alloy blisk blade processing method |
| CN112760637A (en) * | 2020-12-24 | 2021-05-07 | 天津市机械涂层研究所有限责任公司 | Remanufacturing and repairing method for failed gas turbine blade |
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