CN113478167A - Method for repairing blade shroud of working blade of high-pressure turbine of aircraft engine - Google Patents
Method for repairing blade shroud of working blade of high-pressure turbine of aircraft engine Download PDFInfo
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- CN113478167A CN113478167A CN202110822365.2A CN202110822365A CN113478167A CN 113478167 A CN113478167 A CN 113478167A CN 202110822365 A CN202110822365 A CN 202110822365A CN 113478167 A CN113478167 A CN 113478167A
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- 238000000034 method Methods 0.000 title claims abstract description 29
- 238000000227 grinding Methods 0.000 claims abstract description 58
- 238000005219 brazing Methods 0.000 claims abstract description 56
- 238000007689 inspection Methods 0.000 claims abstract description 16
- 239000012720 thermal barrier coating Substances 0.000 claims abstract description 10
- 238000005507 spraying Methods 0.000 claims abstract description 4
- 238000001917 fluorescence detection Methods 0.000 claims abstract description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 24
- 239000000945 filler Substances 0.000 claims description 20
- 229910052751 metal Inorganic materials 0.000 claims description 20
- 239000002184 metal Substances 0.000 claims description 20
- 238000012545 processing Methods 0.000 claims description 14
- 238000010438 heat treatment Methods 0.000 claims description 12
- 229910052759 nickel Inorganic materials 0.000 claims description 12
- 238000003466 welding Methods 0.000 claims description 11
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 6
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 6
- 229910052782 aluminium Inorganic materials 0.000 claims description 6
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 6
- 238000001816 cooling Methods 0.000 claims description 6
- 239000010935 stainless steel Substances 0.000 claims description 6
- 229910001220 stainless steel Inorganic materials 0.000 claims description 6
- 239000010936 titanium Substances 0.000 claims description 6
- 229910052719 titanium Inorganic materials 0.000 claims description 6
- 229910052786 argon Inorganic materials 0.000 claims description 3
- 238000007599 discharging Methods 0.000 claims description 3
- 230000002452 interceptive effect Effects 0.000 claims 1
- 229910045601 alloy Inorganic materials 0.000 abstract description 11
- 239000000956 alloy Substances 0.000 abstract description 11
- 230000002035 prolonged effect Effects 0.000 abstract description 2
- 238000001514 detection method Methods 0.000 description 18
- 230000007547 defect Effects 0.000 description 13
- 239000000523 sample Substances 0.000 description 8
- 239000011248 coating agent Substances 0.000 description 6
- 238000000576 coating method Methods 0.000 description 6
- 238000012360 testing method Methods 0.000 description 4
- 238000009736 wetting Methods 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 2
- 238000007796 conventional method Methods 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000004146 energy storage Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
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- 230000035945 sensitivity Effects 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000011230 binding agent Substances 0.000 description 1
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- 238000004140 cleaning Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
- B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a method for repairing a blade shroud of a working blade of a high-pressure turbine of an aircraft engine. The method comprises the following steps: s1, roughly grinding a to-be-welded part of a contact surface of a leaf back; s2, roughly grinding the to-be-welded part of the contact surface of the leaf basin; s3, assembling the wear-resistant blocks; s4, vacuum brazing; s5, fine grinding; and S6, after ultrasonic and fluorescence detection, removing the original thermal barrier coating on the blade, recovering the original size, spraying the thermal barrier coating, and finally, detecting whether the blade is qualified through fluorescence inspection. The invention adopts a method of vacuum brazing the wear-resistant alloy block, the whole part is heated in a furnace, the deformation of the brazed part is small, the wear-resistant alloy block is processed by fine grinding to recover the size of the radial surface of the blade shroud, the use requirement of the repaired part can be met, the wear resistance of the part is enhanced, the wear of the high-pressure turbine blade in the subsequent use process is reduced, and the service life of the part is prolonged.
Description
Technical Field
The invention belongs to the technical field of machining, and particularly relates to a method for repairing a blade shroud of a high-pressure turbine working blade of an aircraft engine.
Background
The radial surface of the blade shroud of the high-pressure turbine working blade is matched with the radial surface of the blade shroud, and when the aircraft engine works, the high-pressure turbine blades can be extruded, abraded and collided with each other due to vibration, so that the radial surface of the blade shroud has the phenomenon of block falling, and the use requirement is not met. After the service life of the aircraft engine in the overhaul period is over, the working blade of the high-pressure turbine is damaged and needs to be repaired to meet the follow-up use requirement, so that the blade replacement is reduced, and the cost is reduced. Because the parts are repair parts and no machining allowance is left for other sizes of the blade, how to repair the blade to the original size is very important.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a method for repairing a blade shroud of a high-pressure turbine working blade of an aeroengine, which is used for recovering the radial surface dimension (see the dimension A +/-0.05 blade shroud chord width A and half chord width L in the figure 1) of the blade shroud of the high-pressure turbine working blade of the aeroengine, enhancing the wear resistance of the blade shroud, and reducing the rejection rate of the high-pressure turbine working blade after the engine is used.
In order to achieve the purpose, the technical scheme adopted by the invention for solving the technical problems is as follows:
a method for repairing a blade shroud of a working blade of a high-pressure turbine of an aircraft engine comprises the following steps:
s1, roughly grinding to-be-welded positions of contact surfaces of blade backs
Measuring the size of the root position of the step surface of the blade back and the switching of the contact surface, positioning and processing by using the tenon teeth, and then determining the position of the grinding wheel according to different sizes;
s2, roughly grinding the to-be-welded part of the contact surface of the leaf basin
Positioning and processing the tenon tooth, the radial rough grinding notch of the blade shroud back and the step high surface, measuring and grouping each blade to ensure the specified step size, and then determining the position of the grinding wheel according to different sizes;
s3, assembling wear-resistant blocks
Welding the wear-resistant block with the nickel-plated thickness of 0.01-0.03 mm with a stainless steel strip, then welding the stainless steel strip to the leaf crown, fixing the wear-resistant block and ensuring that a brazing gap between the wear-resistant block and a contact surface is 0.05-0.07 mm;
s4, vacuum brazing
Welding by adopting nickel-based brazing filler metal, and filling the nickel-based brazing filler metal into a gap between the wear-resistant block and the contact surface;
s5, fine grinding
Grinding the wear-resistant block by using a grinding wheel with the thickness not more than 15mm to restore the size of the contact surface to the original size;
and S6, after ultrasonic and fluorescence detection, removing the original thermal barrier coating on the blade, recovering the original size, spraying the thermal barrier coating with the thickness of 0.06-0.08 mm, and finally, detecting whether the blade is qualified through fluorescence inspection.
Further, in S1, the grinding wheel may be divided into three groups of +0.15 to +0.05, +0.05 to-0.05 and-0.05 to-0.15 according to the measured size, and then the front and rear positions of the grinding wheel and the grinding depth may be adjusted according to the measured size.
Further, the grinding depth was 1.5 mm.
Further, the wear-resistant block is made of hard alloy and is 1.8mm thick.
Further, the aluminum content and the titanium content in the wear-resistant block are both 9-15%.
Further, the nickel-based brazing filler metal in the S4 is a common high-temperature-resistant nickel-based brazing filler metal and comprises powdered brazing filler metal and a binder.
Further, the specific process of vacuum brazing is as follows:
(1) pre-vacuum to the pressure in the furnace lower than 3.0X 10-2After Pa, the temperature starts to rise to 500 ℃, the temperature rise rate is 2-5 ℃/min, and the temperature is kept at 500 +/-30 ℃ for 25-35 min;
(2) heating from 500 ℃ to 950 ℃, wherein the heating rate is 6-10 ℃/min, and keeping the temperature at 950 +/-10 ℃ for 25-35 min;
(3) heating from 950 ℃ to 1162 ℃, wherein the heating rate is 8-12 ℃/min, and keeping the temperature at 1162 +/-10 ℃ for 12 +/-1 min;
(4) cooling the furnace to below 1000 ℃, refilling 0.8-2.0 bar of argon and starting a fan for cooling, and discharging the product when the temperature is lower than 100 ℃.
Furthermore, the fine grinding is performed by positioning the radial contact surface of the tenon tooth and the blade back, and meanwhile, a groove for placing the wear-resistant block is formed in the grinding clamp, so that the interference positioning of the wear-resistant block is avoided.
Further, before the rough grinding in S1, performing fluorescence inspection to detect whether the blade body and the blade shroud to be repaired have superscript defects such as corrosion pits and cracks or not; after the rough grinding in S2, the fluorescent inspection is also needed, whether the surface to be welded has defects such as cracks or the like is checked, and the brazing can be carried out only after the surface has no defects, so that the subsequent brazing quality is ensured.
Further, the process of ultrasonic detection is as follows:
due to the structural limitation of the blade, the conventional method for detecting the internal quality of the brazing seam (such as X-ray inspection) cannot detect the brazing seam. Therefore, after the brazing seam is inspected to be qualified visually, the internal quality of the brazing seam is detected by adopting a contact type pulse reflection ultrasonic detection technology.
The OLYMPUS probe with the model M208, the frequency of 20MHz and the diameter of 3.2mm is used for detection, and the internal defects of the drill seam can be found sensitively. The area of the ultrasonic inspection which allows the lack of penetration is not more than 1.5mm2Before detecting the parts, the ultrasonic reference test block is used for verifying the detection parameters, and the detection of the brazing seams of the parts is carried out after the detection parameters are qualified. When the ultrasonic contrast test block is manufactured, flat-bottom holes with the diameter of phi 1.2 +/-0.1 mm are manufactured in a blade basin and a blade back area of a blade shroud to serve as artificial defects, and the flat-bottom holes extend to a brazing surface. Because the detection area is small, the repair thickness is thin, the requirements for ultrasonic detection sensitivity and resolution are high after the radial contact surface of the blade crown is brazed and repaired, and the size of the contact surface of the high-frequency ultrasonic probe is difficult to manufacture to be smaller than that of the repair area due to process reasons, the ultrasonic probe is well contacted with the detection area by adding the matched delay block on the probe and adjusting the size of the delay block, as shown in fig. 6.
The invention has the beneficial effects that:
1. the L size L +/-0.1 on the back of the radial contact surface of the leaf crown and the A size A +/-0.05 on the basin are different, the abrasion conditions of all parts are different after the parts are used, the radial contact surface is required to be restored to the A size A +/-0.05 of a new part in design, the requirement on size precision is high, and the requirement on size is shown in figure 1 (unit:mm). The invention adopts a method of vacuum brazing the wear-resistant alloy block, the whole part is heated in a furnace, the deformation of the brazed part is small, the wear-resistant alloy block is processed by fine grinding to recover the size of the radial surface of the blade shroud, the use requirement of the repaired part can be met, the wear resistance of the part is enhanced, the wear of the high-pressure turbine blade in the subsequent use process is reduced, and the service life of the part is prolonged.
2. The invention can be grouped according to different sizes during rough grinding, and can ensure the size requirement, avoid the time waste of adjustment during each live grinding and improve the processing efficiency by a grouping processing mode.
3. Because the aluminum and titanium content in the wear-resistant block is too high (9% -15%), when the pretreatment is not carried out, the aluminum and titanium are oxidized at high temperature to hinder the wetting of the brazing filler metal and reduce the brazing quality, the wear-resistant block needs to be plated with nickel to improve the wetting property of the brazing filler metal.
Drawings
FIG. 1 is a tip shroud size diagram;
FIG. 2 is a rough grind size plot;
FIG. 3 is a schematic view of wide wheel grinding;
FIG. 4 is a schematic view of a narrow grinding wheel (15 mm thick) grinding;
FIG. 5 is a schematic view of a grooved grinding fixture;
FIG. 6 is a process flow diagram.
Detailed Description
The following description of the embodiments of the present invention is provided to facilitate the understanding of the present invention by those skilled in the art, but it should be understood that the present invention is not limited to the scope of the embodiments, and it will be apparent to those skilled in the art that various changes may be made without departing from the spirit and scope of the invention as defined and defined in the appended claims, and all matters produced by the invention using the inventive concept are protected.
Examples
A method for repairing a blade shroud of a working blade of a high-pressure turbine of an aircraft engine comprises the following steps:
s1, fluorescent inspection: and detecting whether the used blade body and the blade shroud to be repaired have superscript defects such as corrosion pits, cracks and the like.
S2, grinding the to-be-welded part of the radial surface of the blade crown: after the blade is used, the abrasion condition of the radial contact surface of each blade crown is inconsistent, the radial contact surface of the cone back of the blade crown is retested before repair, the size of the detected lowest point is compared with the size of the cone back of a new blade (namely the size needing repair and guarantee), a notch with the theoretical grinding depth of 1.5mm during rough grinding can be guaranteed to be completely removed, the rough grinding size is controlled according to a graph 2, and therefore the thickness of a brazed hard alloy block is guaranteed to be 1.8 mm.
S3, when the part is roughly ground and faces away from the contact surface, the tenon tooth is used for positioning and processing, and due to torsional deformation of the blade crown, the grinding amount of each blade is not consistent in direct processing, so that the specified step size cannot be guaranteed. Aiming at the problem, before processing, the size of the root part of the switching between the low surface of the step surface of the whole blade and the contact surface is measured, the parts are grouped in advance, and the parts can be divided into three groups of +0.15 to +0.05 and +0.05 to-0.05 and-0.05 to-0.15, and are processed according to the groups.
Aiming at each group of blades, the front and rear positions of the grinding wheel are adjusted by adjusting the main shaft of the machine tool, then the grinding depth of parts is adjusted, and meanwhile, the size of a contact surface and the size of a specified step are ensured.
S4, when the part is roughly ground towards the contact surface, positioning and processing are carried out on the tenon tooth, the radial rough grinding notch of the blade shroud back and the step height surface, and each piece of blade is measured and processed in groups to ensure the specified step size.
By means of grouping processing, the size requirement can be guaranteed, time waste caused by adjustment during each movable grinding process can be avoided, and processing efficiency is improved.
S5, fluorescent inspection: and (4) checking whether the surface to be welded has defects such as cracks or not, and brazing can be carried out only after the surface has no defects, so that the brazing quality is ensured.
S6, nickel plating treatment before brazing: because the aluminum and titanium content in the wear-resistant block is too high (9% -15%), when the pretreatment is not carried out, the aluminum and titanium are oxidized at high temperature to hinder the wetting of the brazing filler metal and reduce the brazing quality, the wear-resistant block needs to be plated with nickel to improve the wettability of the brazing filler metal.
S7, assembling, positioning and welding the wear-resistant blocks: the wear-resistant block and the stainless steel strip are fixed together in a spot welding mode through energy storage spot welding, and then the stainless steel strip is in the position of the blade shroud through energy storage spot welding to fix the wear-resistant block and guarantee a brazing gap.
S8, vacuum brazing: the working temperature of the high-pressure turbine blade is above 900 ℃, the factors such as the fluidity, the bonding strength and the high temperature resistance of the brazing filler metal are considered, the high-temperature nickel-based brazing filler metal is adopted during repair, a paste brazing filler metal is preset at a position to be welded, the paste brazing filler metal is prepared by blending the powdery brazing filler metal and a bonding agent, the blade is dried after the brazing filler metal is preset, the blade is charged in a mode that a tenon faces upwards and is hung on a brazing frame, and the charging mode can reduce the deformation of parts and facilitate the filling of the brazing filler metal into a welding seam.
The specific process comprises the following steps:
(1) pre-vacuum to the pressure in the furnace lower than 3.0X 10-2After Pa, the temperature starts to rise to 500 ℃, the temperature rise rate is 2-5 ℃/min, and the temperature is kept at 500 +/-30 ℃ for 25-35 min;
(2) heating from 500 ℃ to 950 ℃, wherein the heating rate is 6-10 ℃/min, and keeping the temperature at 950 +/-10 ℃ for 25-35 min;
(3) heating from 950 ℃ to 1162 ℃, wherein the heating rate is 8-12 ℃/min, and keeping the temperature at 1162 +/-10 ℃ for 12 +/-1 min;
(4) cooling the furnace to below 1000 ℃, refilling 0.8-2.0 bar of argon and starting a fan for cooling, and discharging the product when the temperature is lower than 100 ℃.
S9, grinding the wear-resistant alloy block: after the hard alloy blocks are brazed on the parts, the alloy blocks on the back of the basin need to be ground, the contact surface is restored to the size required by the design, and a numerical control grinding machine and a diamond roller are used for fine grinding to ensure the processing precision and quality.
S10, when the contact surface is finely ground, because the blade crown is deformed, the angles of two adjacent step surfaces of the contact surface are changed compared with the theoretical angle, if a wide grinding wheel is used, the grinding wheel can grind the tilted surfaces of the two step surfaces as shown in figure 3, therefore, the grinding wheel with the narrowest thickness of 15mm needs to be used after being improved, and the grinding surface of the grinding wheel is close to the right side of the grinding wheel as shown in figure 4.
S11, when the wear-resistant block on the basin side of the blade is finely ground, the wear-resistant block is positioned and processed by the tenon tooth and the back radial surface, and the hard alloy block is brazed on the blade back, so that the back radial surface is used for positioning, the clamping of a part is unstable and cannot be normally processed, the size is easily out of tolerance, and a groove is formed between the back radial contact surface and the step surface, as shown in figure 5, the protruding alloy block is positioned without interference, the clamping and processing stability is ensured, the A size (A +/-0.05) mm is qualified, and the goal of repairing the radial contact surface of the blade crown is achieved.
S12, ultrasonic detection of brazing quality: due to the structural limitation of the blade, the conventional method for detecting the internal quality of the brazing seam (such as X-ray inspection) cannot detect the brazing seam. Therefore, after the brazing seam is inspected to be qualified visually, the internal quality of the brazing seam is detected by adopting a contact type pulse reflection ultrasonic detection technology.
The OLYMPUS probe with the model M208, the frequency of 20MHz and the diameter of 3.2mm is used for detection, and the internal defects of the drill seam can be found sensitively. The area of the ultrasonic inspection which allows the lack of penetration is not more than 1.5mm2Before detecting the parts, the ultrasonic reference test block is used for verifying the detection parameters, and the detection of the brazing seams of the parts is carried out after the detection parameters are qualified. When the ultrasonic contrast test block is manufactured, flat-bottom holes with the diameter of phi 1.2 +/-0.1 mm are manufactured in a blade basin and a blade back area of a blade shroud to serve as artificial defects, and the flat-bottom holes extend to a brazing surface. The detection area is small, the repair thickness is thin, the requirements for ultrasonic detection sensitivity and resolution are high after the radial contact surface of the blade crown is repaired by brazing, and the size of the contact surface of the high-frequency ultrasonic probe is difficult to manufacture to be smaller than that of the repair area due to process reasons, so that the good contact between the ultrasonic probe and the detection area is realized by adding the delay block made of resin on the probe and adjusting the size of the delay block to be matched with the brazing area.
S13, fluorescent inspection: and after the ultrasonic inspection is qualified, carrying out fluorescence inspection on the surface of the drill seam, and inspecting whether the surface of the drill seam has defects such as cracks.
S14, removing the AlSiY thermal barrier coating: because the thermal barrier coatings exist on the blade body and the edge plate, after the blade is used, the coating is locally damaged, the subsequent use requirement is not met, the coating needs to be removed, the size of the blade shroud needs to be recovered, and then the coating is recovered, so that the use requirement is met. The coating is removed by a chemical method, so that the cleaning can be ensured, and the blade material is not damaged.
S15, spraying a thermal barrier coating AlSiY: after the size of the blade is repaired, the thermal barrier coating AlSiY on the surface of the blade body needs to be recovered, and the high-temperature resistance of the blade is improved.
S16, fluorescent inspection: and after the coating is restored, carrying out fluorescence inspection on the brazing seam, and checking whether the surface of the brazing seam has defects caused by the restored coating.
Claims (8)
1. A method for repairing a blade shroud of a working blade of a high-pressure turbine of an aircraft engine is characterized by comprising the following steps:
s1, roughly grinding to-be-welded positions of contact surfaces of blade backs
Measuring the size of the root position of the step surface of the blade back and the switching of the contact surface, positioning and processing by using the tenon teeth, and then determining the position of the grinding wheel according to different sizes;
s2, roughly grinding the to-be-welded part of the contact surface of the leaf basin
Positioning and processing the tenon tooth, the radial rough grinding notch of the blade shroud back and the step high surface, measuring and grouping each blade to ensure the specified step size, and then determining the position of the grinding wheel according to different sizes;
s3, assembling wear-resistant blocks
Welding the wear-resistant block with the nickel-plated thickness of 0.01-0.03 mm with a stainless steel strip, then welding the stainless steel strip to the leaf crown, fixing the wear-resistant block and ensuring that a brazing gap between the wear-resistant block and a contact surface is 0.05-0.07 mm;
s4, vacuum brazing
Welding by adopting nickel-based brazing filler metal, and filling the nickel-based brazing filler metal into a gap between the wear-resistant block and the contact surface;
s5, fine grinding
Grinding the wear-resistant block by using a grinding wheel with the thickness not more than 15mm to restore the size of the contact surface to the original size;
and S6, after ultrasonic and fluorescence detection, removing the original thermal barrier coating on the blade, recovering the original size, spraying the thermal barrier coating with the thickness of 0.06-0.08 mm, and finally, detecting whether the blade is qualified through fluorescence inspection.
2. The method for repairing a shroud of a working blade of a high pressure turbine of an aircraft engine as claimed in claim 1, wherein the step S1 is divided into three groups of +0.15 to +0.05, +0.05 to-0.05 and-0.05 to-0.15 according to the measured size, and then the front and rear positions of the grinding wheel are adjusted according to the measured size to ensure that the depth of the grinding gap is 1.5mm and the worn part is completely removed.
3. The aircraft engine high pressure turbine working blade shroud repair method according to claim 1 or 2, characterized in that the grinding depth is 1.5 mm.
4. The method for repairing a shroud of a working blade of a high pressure turbine of an aircraft engine according to claim 1, wherein the wear resistant block is a cemented carbide block having a thickness of 1.8 mm.
5. The method for repairing the shroud of the working blade of the high-pressure turbine of the aircraft engine according to claim 4, wherein the aluminum and titanium contents in the wear-resistant block are both 9-15%.
6. The aircraft engine high pressure turbine working blade shroud repair method as claimed in claim 1, wherein the nickel-based brazing filler metal in S4 is a high temperature resistant nickel-based brazing filler metal.
7. The aircraft engine high pressure turbine working blade shroud repair method according to claim 1, wherein the specific process of vacuum brazing is as follows:
(1) pre-vacuum to the pressure in the furnace lower than 3.0X 10-2After Pa, the temperature starts to rise to 500 ℃, the temperature rise rate is 2-5 ℃/min, and the temperature is kept at 500 +/-30 ℃ for 25-35 min;
(2) heating from 500 ℃ to 950 ℃, wherein the heating rate is 6-10 ℃/min, and keeping the temperature at 950 +/-10 ℃ for 25-35 min;
(3) heating from 950 ℃ to 1162 ℃, wherein the heating rate is 8-12 ℃/min, and keeping the temperature at 1162 +/-10 ℃ for 12 +/-1 min;
(4) cooling the furnace to below 1000 ℃, refilling 0.8-2.0 bar of argon and starting a fan for cooling, and discharging the product when the temperature is lower than 100 ℃.
8. The method for repairing the shroud of the working blade of the high-pressure turbine of the aircraft engine according to claim 1, wherein the fine grinding is performed by positioning the radial contact surface of the tenon tooth and the blade back, and meanwhile, a groove for placing the wear-resistant block is formed in the grinding fixture, so that the wear-resistant block is prevented from interfering with positioning.
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| CN114991876A (en) * | 2022-07-15 | 2022-09-02 | 北京航空航天大学 | Circumferential modeling design method for partial shroud turbine blade shroud |
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| CN115635243A (en) * | 2022-11-14 | 2023-01-24 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for replacing and repairing blades of spoke type air inlet casing |
| CN115722866A (en) * | 2022-12-07 | 2023-03-03 | 中国航发动力股份有限公司 | Repairing method for welding cover plate of single crystal blade |
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| CN113878301A (en) * | 2021-10-27 | 2022-01-04 | 镇江同舟螺旋桨有限公司 | Surface defect repairing process for propeller casting |
| CN114991876A (en) * | 2022-07-15 | 2022-09-02 | 北京航空航天大学 | Circumferential modeling design method for partial shroud turbine blade shroud |
| CN115502654A (en) * | 2022-09-14 | 2022-12-23 | 哈电发电设备国家工程研究中心有限公司 | Gap repairing insert and gap repairing method for turbine titanium alloy blade shroud band |
| CN115635243A (en) * | 2022-11-14 | 2023-01-24 | 中国航发沈阳黎明航空发动机有限责任公司 | Method for replacing and repairing blades of spoke type air inlet casing |
| CN115635243B (en) * | 2022-11-14 | 2024-04-26 | 中国航发沈阳黎明航空发动机有限责任公司 | Replacing and repairing method for spoke type air inlet casing blade |
| CN115722866A (en) * | 2022-12-07 | 2023-03-03 | 中国航发动力股份有限公司 | Repairing method for welding cover plate of single crystal blade |
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