Activating agent, prefabricated paste, prefabricated member and process for repairing thin-wall-penetrating defects

Abstract

The present invention relates to the field of the repairing of high-temperature blades of gas turbines. Disclosed are an activating agent, prefabricated paste, prefabricated member and process for repairing thin-wall-penetrating defects. The activating agent at least comprises the following elements in percentage by mass: 7.1-9.8% of Cr, 15.2-19.8% of Co, 2.5-4.3% of Al, 0.2-1.7% of W, 6.2-8.7% of Ti, 5.6-7.8% of Ta, 5.6-8.8% of Mo, 2.7-4.2% of Ru, 5.6-7.8% of Hf, 0.07-0.15% of Zr, 0.10-0.15% of C, and 0.01-0.05% of Sc. The prefabricated paste is prepared by blending the activating agent, a curing agent and a binding agent. The prefabricated member is made of the prefabricated paste. The process comprises the steps of polishing of a defect, forming of a prefabricated member, trimming of the prefabricated member, additive-manufacturing-based repairing of the defect, and post-treatment. In the present invention, a repair area has a structure close to that of a substrate and can adapt to the high-temperature working environment of a blade, and the mechanical strength of a joint is high; therefore, the cracking and deformation of the thin wall of the blade caused by a high heat input are effectively avoided, an air channel is prevented from being blocked, and the problem of a thin-wall-penetrating defect of a nickel-based high-temperature alloy blade being difficult to repair is solved.

Description

Activator, prefabricated paste, prefabricated part and process for repairing thin-wall penetrating defects Technical Field

[0001] The present invention relates to the field of gas turbine high-temperature blade repair, in particular to an activator, a prefabricated paste, a prefabricated part and a process for repairing thin-wall penetrating defects. Background Art

[0002] Nickel-based high-temperature alloy blades are the core components of heavy-duty gas turbines. They are known as the "aorta" of turbine components and are responsible for extracting energy from gas combustion. Their operating temperatures are extremely harsh. The first-stage turbine blades, in particular, must withstand the impact of high-temperature airflows approaching 1400°C, far exceeding the heat resistance limit of nickel-based high-temperature alloys themselves (about 1100°C). Therefore, effective cooling measures must be adopted to ensure the reliable operation of the blades in high-temperature environments. The use of a composite air film cooling hollow structure is an effective cooling method that enables the blades to meet high-temperature and high-pressure working conditions. When the blades are in service, cooling air circulates inside to remove heat, and at the same time escapes through the air film holes on the blades to form an air film, isolating the high temperature and reducing the surface temperature of the turbine blades during operation.

[0003] During long-term service, high-temperature blades are susceptible to deformation damage such as cracking, ablation, and material loss due to foreign object impact, airflow erosion, and thermal fatigue. If these damages occur in the thin-walled parts of hollow blades, they will often cause penetrating damage to the thin walls. Due to the poor weldability of nickel-based high-temperature alloys, the process window for fusion welding repair is particularly narrow, making it even more difficult to use them to repair thin-walled blades. High heat input can easily cause deformation of thin walls. Although large-gap brazing or powder metallurgy repair technologies can effectively avoid the occurrence of welding cracks, such repair technologies require the introduction of a large amount of low-melting-point brazing filler metal during the repair process. When using them to repair penetrating defects on the thin walls of blades, the brazing filler metal will liquefy and flow into the blade airway, causing airway blockage and damaging the structure of the hollow blade.

[0004] Summary of the Invention

[0005] The purpose of the present invention is to provide an activator, prefabricated paste, prefabricated part and process for repairing thin-wall penetrating defects in response to the above-mentioned problems, so that the tissue of the repair area is close to the substrate, can adapt to the high-temperature working environment of the blade and the mechanical properties of the joint are high, effectively avoiding cracking and deformation of the thin wall of the blade caused by high heat input, preventing airway blockage, and solving the problem of difficult repair of thin-wall penetrating defects in nickel-based high-temperature alloy blades.

[0006] The technical solution adopted by the present invention is as follows: an activator for repairing thin-wall through-hole defects, the preparation of which comprises at least the following elements in mass percentage:

[0007] Cr (7.1%-9.8%), Co (15.2%-19.8%), Al (2.5%-4.3%), W (0.2-1.7%), Ti (6.2%-8.7%), Ta (5.6%-7.8%), Mo (5.6%-8.8%), Ru (2.7%-4.2%), Hf (5.6%-7.8%), Zr (0.07%-0.15%), C (0.10%-0.15%), Sc (0.01%-0.05%), and the rest is Ni and / or unavoidable impurity elements.

[0008] Furthermore, the melting point of the activator is between 1130°C and 1160°C.

[0009] Furthermore, the activator is in powder form with a particle size of 30 μm to 53 μm and is prepared by an atomization method.

[0010] A prefabricated paste for repairing thin-walled penetrating defects, the prefabricated paste is in paste form and is prepared by mixing the activator, curing agent and adhesive for repairing thin-walled penetrating defects in the required proportions; wherein:

[0011] The curing agent is M-21 or Mar-M004 commercial alloy powder with a particle size ranging from 85 μm to 106 μm; the binder is commercial NICROBRAZ S-BINDR type; the mass of the activator accounts for 40%-50%, the mass of the binder accounts for 3%-5%, and the balance is the curing agent.

[0012] A prefabricated part for repairing thin-wall penetrating defects is prepared by using a mold to prepare a prefabricated paste for repairing thin-wall penetrating defects.

[0013] Specifically, the mold is a ceramic mold, the prefabricated paste is placed in the ceramic mold, and evenly flattened to a thickness of 5 mm to 9 mm; then the ceramic mold with the prefabricated paste is placed in a vacuum chamber with a degree of vacuum better than 1×10 -3 Pa vacuum furnace sintering, the vacuum furnace provides a vacuum environment, the sintering temperature is 1140 ℃ ~ 1170 ℃, the sintering time is 10min ~ 15min; after sintering, the temperature in the vacuum furnace is reduced to 1000 ℃ ~ 1050 ℃ for hot isostatic pressing treatment, during hot isostatic pressing treatment, the pressure in the vacuum furnace is 10MPa ~ 20MPa, the holding time of hot isostatic pressing treatment is 30min ~ 60min, after hot isostatic pressing treatment, the furnace is cooled to form a prefabricated part, the thickness of the prefabricated part is about 3mm ~ 7mm.

[0014] A process for repairing thin-wall penetration defects, which is used to repair thin-wall penetration defects on hollow thin-walled blades whose base material is a precipitation-strengthened nickel-based casting high-temperature alloy such as Mar-M247, MGA2400, or GTD444, comprises the following steps:

[0015] S1: defect polishing;

[0016] The penetrating defect area is mechanically polished to remove the oxide layer. At the same time, the area around the penetrating defect is polished into a groove. The slope of the groove should be less than 60°. The length and width of the groove after polishing should not exceed 20mm×10mm. The thickness of the thin wall at the penetrating defect should be within 2mm~5mm. After polishing, place it in alcohol or acetone solution for ultrasonic cleaning for 60 minutes, take it out and blow dry it for use.

[0017] S2: Preform molding; making the preform for repairing the thin-walled penetrating defect;

[0018] S3: Prefabricated parts modification;

[0019] According to the specific size of the groove formed after the defect is polished in step S1, the prefabricated part in step S2 is polished and reshaped. The thickness of the prefabricated part after reshaping is 0.5 mm to 1 mm thicker than the thickness of the thin wall at the penetrating defect. The lower surface of the prefabricated part should be flush with the end face of the small diameter end of the groove, that is, the upper surface of the prefabricated part after reshaping should be 0.5 mm to 1 mm higher than the end face of the large diameter end of the groove. The remaining positions of the prefabricated part match the shape and size of the groove. The polished and reshaped prefabricated part is placed in an alcohol or acetone solution for ultrasonic cleaning for 60 minutes, removed and blown dry for later use.

[0020] S4: defect additive;

[0021] The preformed part after the modification in step S3 is assembled to the groove of step S1, and then the preformed part is placed under a vacuum of better than 1×10 -3 Pa vacuum furnace is used for metallurgical insulation, and the vacuum furnace provides a vacuum environment; the insulation temperature of the metallurgical insulation is 1190℃~1210℃, the insulation time is 45min~60min, and the furnace is cooled after the insulation is completed.

[0022] S5: post-processing;

[0023] After the metallurgical insulation and cooling in step S4 are completed, the blade is subjected to performance recovery heat treatment, and the excess metal in the repair area is removed by reshaping, thereby completing the shape reshaping of the defects.

[0024] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are:

[0025] 1. Compared with traditional repair materials, the activator disclosed in the present invention does not add high concentrations of B, Si, and Zr as melting point depressants. Instead, it achieves high entropy of the alloy by adjusting the mass ratio of the strengthening elements in the high-temperature alloy, thereby suppressing the melting point of the activator to within the range allowed by the process. Therefore, the repair area obtained by using the preform of the present invention does not contain low-melting-point B-, Si-, and Zr-rich compounds and / or eutectic phases. The repair area has a structure similar to that of the substrate, can withstand the high-temperature operating environment of the blade, and the mechanical properties and strength of the joint are high.

[0026] 2. Compared with the existing fusion welding technology, the process disclosed in the present invention has the beneficial effect of avoiding cracking and deformation of thin-wall blades caused by high heat input; compared with the existing large-gap brazing or powder metallurgy repair technology, the beneficial effect is that it avoids a large amount of liquid phase flowing into the blade airway during the metallurgical process, causing airway blockage; and effectively solves the problem of difficult repair of thin-wall penetrating defects in nickel-based high-temperature alloy blades. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] The present invention will now be described by way of example with reference to the accompanying drawings, in which:

[0028] FIG1 is a microstructure of a DFX-M preform provided by the present invention;

[0029] FIG2 is a schematic diagram of a thin-wall penetration defect of an N1 guide blade provided by the present invention;

[0030] FIG3 is a schematic diagram of step S1 in the process provided by the present invention;

[0031] FIG4 is a schematic diagram of step S2 or S3 in the process provided by the present invention;

[0032] FIG5 is a schematic diagram of step S4 in the process provided by the present invention;

[0033] FIG6 is a schematic diagram of step S5 in the process provided by the present invention;

[0034] FIG7 is a microstructure of the repaired area obtained by repairing the thin-wall penetrating defect of the N1 guide blade according to the present invention.

[0035] Markings in the figure: 1-thin wall; 2-air channel; 3-matrix; 4-penetrating defect; 5-groove; 6-prefabricated part. DETAILED DESCRIPTION

[0036] All features disclosed in this specification, or all steps in the disclosed methods or processes, except mutually exclusive features and / or steps, can be combined in any manner.

[0037] Any feature disclosed in this specification, unless otherwise stated, may be replaced by other equivalent or similar features. That is, unless otherwise stated, each feature is only an example of a series of equivalent or similar features.

[0038] Example 1

[0039] An activator for repairing thin-wall through-hole defects, the preparation of the activator comprises at least the following elements in mass percentage:

[0040] Cr (7.1% - 9.8%), Co (15.2% - 19.8%), Al (2.5% - 4.3%), W (0.2 - 1.7%), Ti (6.2% - 8.7%), Ta (5.6% - 7.8%), Mo (5.6% - 8.8%), Ru (2.7% - 4.2%), Hf (5.6% - 7.8%), Zr (0.07% - 0.15%), C (0.10% - 0.15%), Sc (0.01% - 0.05%), and the rest is Ni and / or unavoidable impurity elements.

[0041] In this embodiment, the activator is in powder form with a particle size of 30 μm to 53 μm, and can be prepared by an atomization method; the melting temperature range is 1130° C. to 1160° C.

[0042] It should be noted that the atomization method is a conventional method in this field and will not be further explained here.

[0043] In order to further clearly illustrate and describe the technical solution of the present invention, the following non-limiting embodiments of the activator are provided, as shown in Table 1. The following element content data are all mass percentage data.

[0044] Table 1 Implementation Methods of Activators

[0045] Based on the aforementioned activator implementation, it can be seen that, compared to conventional repair materials, the activator of this embodiment does not add high concentrations of B, Si, and Zr as melting point depressants. Instead, it achieves high entropy of the alloy by adjusting the mass ratio of the strengthening elements in the high-temperature alloy, thereby suppressing the activator's melting point to within the process-permitted range. Therefore, when the activator of the present invention is used to repair defects, the resulting repaired area does not contain low-melting-point B-, Si-, and Zr-rich compounds and / or eutectic phases. The repaired area's structure is similar to that of the substrate, capable of withstanding the high-temperature operating environment of the blade, and the joint has high mechanical strength.

[0046] Example 2

[0047] A prefabricated paste for repairing thin-walled penetrating defects. In order to further clearly illustrate and describe the technical solution of the present invention, the following non-limiting implementation methods of the activator are provided.

[0048] The first embodiment is to prepare a DFX-M prefabricated paste.

[0049] Materials:

[0050] Activator: the activator with the brand name DFB-P in Example 1; Curing agent: M-21 commercial alloy powder; Binder: NICROBRAZ S-BINDR commercial type;

[0051] Among them: M-21 commercial alloy powder, particle size between 85μm and 106μm, nominal chemical composition:

[0052] C (0.13wt%), B (0.02wt%), Cr (5.7wt%), Mo (2.0wt%), Al (6.0wt%), W (11.0wt%), Nb (1.5wt%), Zr (0.12wt%), and the rest are Ni and / or inevitable impurity elements.

[0053] Material dosage: Activator powder accounts for 40% by weight, adhesive accounts for 4% by weight, and the balance is curing agent.

[0054] The paste prepared by uniformly mixing the above amounts of activator, curing agent and binder is used as a prefabricated paste for making corresponding DFX-M prefabricated parts.

[0055] The second implementation method is to prepare a DFX-Y prefabricated paste.

[0056] Material selection:

[0057] Activator: the activator with the brand DFB-A in Example 1; Curing agent: Mar-M004 commercial alloy powder; Binder: NICROBRAZ S-BINDR commercial type;

[0058] Among them: Mar-M004 commercial alloy powder, particle size between 85μm and 106μm, composition:

[0059] C (0.05wt%), Cr (12.0wt%), Mo (4.5wt%), Nb (2.0wt%), Al (5.9wt%), Ti (0.6wt%), Hf (1.3wt%), Zr (0.05wt%), B (0.015wt%).

[0060] Material usage: Activator powder accounts for 40% by weight, adhesive accounts for 3.5% by weight, and the balance is curing agent.

[0061] The paste prepared by uniformly mixing the above amounts of activator, curing agent and binder is used as a prefabricated paste for making corresponding DFX-Y prefabricated parts.

[0062] Example 3

[0063] A prefabricated part for repairing thin-walled through-hole defects. In order to further clearly illustrate and describe the technical solution of the present invention, the following non-limiting implementation methods of an activator are provided.

[0064] The first embodiment is to prepare a DFX-M preform.

[0065] The DFX-M prefabricated paste in Example 2 was placed in a ceramic mold and spread evenly to a thickness of about 5 mm. -3 The preform was sintered in a vacuum furnace at 1150°C for 10 minutes. After sintering, the temperature in the vacuum furnace was lowered to 1050°C for hot isostatic pressing (HIP) at a pressure of 15 MPa for 30 minutes before cooling in the furnace. This resulted in a preform 6 with a thickness of approximately 3 mm. The microstructure of the DFX-M preform is shown in Figure 1.

[0066] The second implementation method is to prepare a DFX-Y preform.

[0067] The DFX-Y prefabricated paste in Example 2 was placed in a ceramic mold and evenly spread to a thickness of about 5 mm. -3 The preform 6 is sintered in a vacuum furnace with a sintering temperature of 1170°C and a sintering time of 10 minutes. After sintering, the temperature in the vacuum furnace is lowered to 1000°C for hot isostatic pressing. The pressure in the vacuum furnace is 20 MPa. The heat preservation time is 30 minutes and then the preform is cooled in the furnace to obtain a preform 6 with a thickness of about 3 mm.

[0068] Example 4

[0069] A process for repairing thin-wall penetrating defects is described in detail below, taking the first-stage turbine guide blade N1 for a 50MW heavy-duty gas turbine as an example, in order to further clearly illustrate and describe the technical solution of the present invention.

[0070] The N1 guide vane is a hollow vane having a base 3 and a thin wall 1. An air channel 2 is formed between the thin wall 1 and the base 3. A defect penetrates the thin wall 1 to form a penetrating defect 4. The base material of the thin wall 1 is Mar-M247 precipitation-strengthened nickel-based cast high-temperature alloy with the nominal chemical composition:

[0071] Ni-8wt%Cr-10wt%Co-10wt%W-5.5wt%Al-1wt%Ti-3wt%Ta-1.5wt%Hf-0.6wt%Mo-0.15wt%C-0.015wt%B-0.03wt%Zr.

[0072] As shown in FIG2-FIG7, the repair process is completed through the following steps, see steps S1-S5 for details.

[0073] S1: defect polishing;

[0074] The penetrating defect 4 on the thin wall 1 of the N1 guide blade was mechanically polished to remove the oxide layer. At the same time, the thin wall 1 around the penetrating defect 4 was polished to a groove 5 with a slope of 45°. The large diameter end of the groove 5 was located on the outer surface of the N1 guide blade, and the small diameter end of the groove 5 was located on the inner wall of the cavity of the N1 guide blade. The length × width of the groove 5 after polishing was 10 mm × 2 mm, and the thickness of the thin wall 1 at the groove 5 was 2.2 mm. After polishing, it was placed in alcohol for ultrasonic cleaning for 60 minutes, taken out and blown dry for later use.

[0075] S2: Preform molding: Using the description in Example 3, a DFX-M preform was produced.

[0076] S3: Prefabricated part shaping;

[0077] According to the geometric dimensions of the groove 5 in step S1, the DFX-M preform 6 in Example 3 was polished. The thickness of the preform 6 after shaping was 2.7 mm, and the lower surface of the preform 6 was kept flush with the inner wall of the cavity at the blade defect. The polished and trimmed preform 6 was then placed in an alcohol solution for ultrasonic cleaning for 60 minutes, taken out and blown dry for later use.

[0078] S4: defect additive;

[0079] The preform 6 after the trimming in step S2 is assembled to the groove 5 in step S1, and the large diameter end of the groove 5 is 0.5 mm higher than the outer surface of the N1 guide blade; then metallurgical insulation is carried out in a vacuum furnace with a vacuum degree better than 1×10-3Pa, the insulation temperature is 1210℃, the insulation time is 50 minutes, and the furnace is cooled after the insulation is completed.

[0080] S5: post-processing;

[0081] After metallurgical insulation and cooling are completed, the blade is subjected to performance recovery heat treatment, and the excess metal in the repair area is removed by shaping to complete the reshaping of the penetrating defect 4 on the thin wall 1 of the N1 guide blade.

[0082] test:

[0083] After the repair was completed, the joints in the repaired area were made into tensile parts, and the room temperature tensile strength was measured to be 795 MPa, reaching 80.3% of the base material strength; the high temperature tensile strength at 900°C reached 473 MPa, reaching 70.1% of the base material strength.

[0084] In summary, compared with the existing fusion welding technology, the process disclosed in this embodiment does not adopt welding, thereby avoiding cracking and deformation of the thin wall 1 of the blade caused by high heat input; compared with the existing large-gap brazing or powder metallurgy repair technology, the prefabricated parts 6 used for prefabrication and the constraint of the groove 5 are used to avoid a large amount of liquid phase flowing into the air channel 2 during the metallurgical process, causing blockage of the air channel 2; that is, it effectively solves the problem of difficult repair of the penetrating defects 4 of the thin wall 1 of the nickel-based high-temperature alloy blade.

[0085] The present invention is not limited to the aforementioned specific embodiments, but extends to any new features or any new combination disclosed in this specification, as well as any new method or process steps or any new combination disclosed.

Claims

1. An activator for repairing thin-wall penetration defects, characterized in that: The preparation of the activator includes at least the following elements in mass percentage: Cr (7.1% - 9.8%), Co (15.2% - 19.8%), Al (2.5% - 4.3%), W (0.2-1.7%), Ti (6.2% - 8.7%), Ta (5.6% - 7.8%), Mo (5.6% - 8.8%), Ru (2.7% - 4.2%), Hf (5.6% - 7.8%), Zr (0.07% - 0.15%), C (0.10% - 0.15%), Sc (0.01% - 0.05%), and the rest is Ni and / or unavoidable impurity elements.

2. The activator according to claim 1, characterized in that: The preparation of the activator includes at least the following elements in mass percentage: Cr (9.8%), Co (15.7%), Al (4.3%), W (1.7%), Ti (7.2%), Ta (7.8%), Mo (7.6%), Ru (3.0%), Hf (6.4%), Zr (0.10%), C (0.15%), Sc (0.01%), and the rest is Ni and / or unavoidable impurity elements.

3. The activator according to claim 1, characterized in that: The preparation of the activator includes at least the following elements in mass percentage: Cr (7.2%), Co (18.1%), Al (3.8%), W (0.2%), Ti (8.7%), Ta (5.9%), Mo (5.6%), Ru (2.7%), Hf (5.6%), Zr (0.07%), C (0.10%), Sc (0.01%), and the rest is Ni and / or unavoidable impurity elements.

4. The activator according to claim 1, characterized in that: The preparation of the activator includes at least the following elements in mass percentage: Cr (9.6%), Co (19.8%), Al (2.5%), W (1.0%), Ti (6.2%), Ta (6.5%), Mo (8.8%), Ru (4.2%), Hf (7.5%), Zr (0.15%), C (0.12%), Sc (0.05%), and the rest is Ni and / or unavoidable impurity elements.

5. The activator according to claim 1, characterized in that: The preparation of the activator includes at least the following elements in mass percentage: Cr (8.7%), Co (17.1%), Al (3.0%), W (0.8%), Ti (6.9%), Ta (5.6%), Mo (6.9%), Ru (2.8%), Hf (7.8%), Zr (0.11%), C (0.11%), Sc (0.01%), and the rest is Ni and / or unavoidable impurity elements.

6. The activator according to claim 1, characterized in that: The melting point of the activator is between 1130°C and 1160°C.

7. The activator according to claim 1, characterized in that: The activator is in powder form with a particle size of 30 μm to 53 μm and is prepared by an atomization method.

8. A prefabricated paste for repairing thin-wall penetrating defects, characterized in that: The prefabricated paste is in paste form and is prepared by mixing the activator, curing agent and adhesive for repairing thin-wall penetrating defects described in any one of claims 1 to 7 in a required proportion.

9. The prefabricated paste according to claim 8, characterized in that: The curing agent is M-21 or Mar-M004 commercial alloy powder with a particle size ranging from 85 μm to 106 μm; the binder is NICROBRAZ S-BINDR commercial type; wherein: The mass of the activator accounts for 40%-50%, the mass of the binder accounts for 3%-5%, and the balance is the curing agent.

10. A prefabricated part for repairing thin-walled through-defects, characterized in that: The prefabricated paste for repairing thin-walled penetrating defects as claimed in claim 8 or 9 is made into a prefabricated part (6) by using a mold.

11. The preform according to claim 10, characterized in that: The mold containing the prefabricated paste is placed in a vacuum environment for sintering, the sintering temperature is 1140°C to 1170°C, and the sintering time is 10min to 15min; after sintering, the ambient temperature is lowered to 1000°C to 1050°C for hot isostatic pressing, the ambient pressure for hot isostatic pressing is 10MPa to 20MPa, the holding time for hot isostatic pressing is 30min to 60min, and after hot isostatic pressing, the prefabricated part (6) is formed by cooling with the furnace.

12. The preform according to claim 11, characterized in that: The vacuum environment is provided by a vacuum furnace, and the vacuum degree of the vacuum environment is better than 1×10 -3 Pa.

13. A process for repairing thin-wall through-defects, characterized in that: The following steps are involved: S1: Defect polishing; The through-hole defect (4) area is polished to form a groove (5) in the through-hole defect (4), and then cleaned and dried for later use; S2: preform molding; manufacturing the preform for repairing the thin-walled through-defect according to claim 11 or 12; S3: Prefabricated parts modification; According to the specific size of the groove (5) formed after grinding the through-hole defect (4) in step S1, the preform (6) is ground and reshaped to match the shape and size of the groove (5), and the upper surface of the preform (6) is 0.5 mm-1 mm higher than the surface of the groove (5), and then cleaned and blown dry for later use; S4: defect additive; The prefabricated part (6) after the trimming in step S3 is assembled to the groove (5) in step S1, and then metallurgical insulation is carried out in a vacuum environment, and after the insulation is completed, the prefabricated part is cooled with the furnace; S5: post-processing; After cooling in step S4 is completed, a performance recovery heat treatment is performed to remove excess metal from the repair area to complete the shape reshaping.

14. The process according to claim 13, characterized in that: In step S1, the slope of the groove (5) is less than 60°.

15. The process according to any one of claims 13-14, characterized in that: This process is used to repair thin-wall penetration defects on hollow thin-walled blades whose substrate is a precipitation-strengthened nickel-based cast high-temperature alloy.

16. The process according to claim 15, characterized in that: The vacuum degree of the vacuum environment is better than 1×10 -3 Pa.

17. The process according to claim 15, characterized in that: The metallurgical insulation temperature is 1190°C ~ 1210°C, and the insulation time is 45min ~ 60min.

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