CN114346597B - Remanufacturing and repairing process for aluminum alloy filter screen bracket of aircraft fuel electric pump - Google Patents
Remanufacturing and repairing process for aluminum alloy filter screen bracket of aircraft fuel electric pump Download PDFInfo
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- CN114346597B CN114346597B CN202111555785.5A CN202111555785A CN114346597B CN 114346597 B CN114346597 B CN 114346597B CN 202111555785 A CN202111555785 A CN 202111555785A CN 114346597 B CN114346597 B CN 114346597B
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Abstract
The invention relates to the technical field of remanufacturing of an aircraft fuel electric pump, in particular to a remanufacturing and repairing process of an aluminum alloy filter screen bracket of an aircraft fuel electric pump, which comprises the following steps: polishing and finishing: trimming and roughly polishing the broken part of the support lug by using an electric polishing head, manufacturing a part to be molded into a U-shaped groove, and then polishing by using sand paper or abrasive cloth to remove burrs and keep the end opening smooth; manufacturing a threaded hole: a blind hole with the depth of 8mm is drilled near the center line of the surface to be formed, and M2 multiplied by 0.25 internal threads are manufactured by a screw tap. The method effectively solves the problems of large heat input, easy part deformation, serious hot crack tendency, more molding body air hole defects and the like of the traditional repair method, solves the repair problem of the aluminum alloy filter screen bracket of the fuel electric pump, realizes the remanufacturing of parts, and avoids the problem that the whole fuel electric pump is replaced again due to the damage of the filter screen bracket; the repair rate and the repair effect of the damage can be obviously improved, and the scrappage of parts is reduced.
Description
Technical Field
The invention relates to the technical field of remanufacturing of aircraft fuel electric pumps, in particular to a remanufacturing and repairing process of an aluminum alloy filter screen bracket of an aircraft fuel electric pump.
Background
The fuel electric pump is an important part for fuel delivery of a fuel tank in an aircraft fuel system, and a filter screen bracket of the fuel electric pump is mainly used for supporting a filter screen and filtering impurities and pollutants in the system to prevent the impurities and the pollutants from entering an aircraft engine. The bracket is made of cast aluminum alloy, the bearing load is not large, but the bracket is easy to break due to the fact that the strength of the bracket is not high and the main supporting part is a thin-walled part and is damaged in the dismounting process, and the whole electric pump needs to be replaced if the part cannot be repaired due to the fact that spare part purchasing approaches are not needed and the remanufacturing cost is high, so that the part needs to be repaired from the consideration of necessity and economy.
In order to ensure the reliability of the repaired part, the main consideration during the repair is to perform additive forming on a part base body, the forming size of the support frame is about 4mm multiplied by 8mm multiplied by 20mm, and the wall thickness is between (3-4) mm. Repairing the damage by adopting argon arc welding surfacing and laser cladding methods, wherein the argon arc welding surfacing process has high heat input, is easy to cause part deformation and generates thermal stress cracks at the heat affected zone accessories; in the laser cladding process, the powder cannot be effectively deposited due to the high reflectivity of the aluminum powder, and a large amount of air holes are generated in the lugs after molding, so that the quality is poor.
Disclosure of Invention
Aiming at the technical problem, the invention provides a remanufacturing and repairing process of an aluminum alloy filter screen bracket of an aircraft fuel electric pump. By adopting the composite repair method of the embedded pillar cold spray molding, the cold-state additive molding of the aluminum alloy powder with better plasticity can be realized at lower temperature, the molding thickness is large, the molding porosity is low, and the remanufacturing repair of parts is realized on the basis of avoiding the repair defects of the conventional process. The problem that the whole fuel oil electric pump is replaced again due to the fact that the filter screen support cannot be repaired is solved.
The technical problem to be solved by the invention is realized by adopting the following technical scheme:
the remanufacturing and repairing process of the aluminum alloy filter screen bracket of the aircraft fuel electric pump comprises the following steps:
grinding and finishing: trimming and roughly polishing the broken part of the support lug by using an electric polishing head, manufacturing a part to be molded into a U-shaped groove, and then polishing by using sand paper or abrasive cloth to remove burrs and keep the end opening smooth;
(II) manufacturing a threaded hole: drilling a blind hole with the depth of 8mm near the center line position on a surface to be formed, and manufacturing M2 multiplied by 0.25 internal threads by using a screw tap;
(III) embedding the support columns: processing an aluminum alloy strut by using a hard aluminum material, manufacturing an external thread with the length of 8mmdM2 multiplied by 0.25 at one end of the strut, coating J-168 metal adhesive on a thread section, screwing in the thread section, curing the thread section for 24 hours at room temperature, polishing residual adhesive liquid by using abrasive paper, and blowing clean and dry compressed air to clean the surface to be repaired;
(IV) protective cleaning: shielding and protecting a non-spraying area by using a high-temperature-resistant adhesive tape, carrying out ultrasonic cleaning on the part, carrying out local fine cleaning on the area to be sprayed by using a brush, and drying the surface of the part by using clean and dry compressed air after cleaning;
(V) surface pretreatment: blowing sand to roughen a part substrate by using 60-80 meshes of brown corundum sand, and polishing and roughening an aluminum alloy pillar by using No. 80 silicon carbide abrasive paper, wherein the surface to be sprayed is required to be rough and uniform without metallic luster and dark spots;
(VI) preheating before spraying: drying the parts in a drying box within 2h after pretreatment;
(seventh) spraying parts: spraying by adopting cold spraying according to set process parameters;
(eight) coating processing: polishing and trimming the coating according to requirements until the coating is smooth in transition, has no edge angle, and has roughness not inferior to Ra1.6 mu m;
(ninth) verification and installation: assembling the parts into a product, checking whether gaps among the impeller, the diffuser and the filter screen are between 0.3 and 0.7mm, and if not, repeating the step (eight) until the gaps are between;
(ten) stress relief treatment: performing low-temperature tempering stress relief treatment within 24 hours after polishing is finished;
(eleven) dye penetrant inspection: brushing a color penetrant and a spraying developer, observing whether a defect trace appears or not under natural light or a white light lamp, and if so, reworking and repeatedly executing the steps (I) to (ten) until the defect trace does not appear;
(twelve) Performance test: and carrying out a strength test and a running-in test according to the repair process of the fuel electric pump.
Preferably, the specific configuration process of the J-168 metal adhesive in the step (three) is as follows: epoxy resin, 200# polyamide, curing agent 703 and asbestos in a proportion of 100:20:12:5, and stirring for 5min.
Preferably, the preheating temperature in the step (six) is 50-60 ℃.
Preferably, the cold spraying process parameters in the step (seven) are as follows: the spraying powder is a mixed powder of 2024 aluminum alloy and aluminum oxide, the particle size range of the powder is 5-45 mu m, the proportion of the aluminum oxide is 20-30%, the spraying gas is nitrogen, the spraying temperature is 475-525 ℃, the spraying pressure is 160-190 psi, the spraying angle is 80 +/-10 degrees, the distance of a spray gun is 15-25 mm, and the powder feeding amount is 10-20 g/min.
Preferably, the step (seven) cold spraying specific process comprises the following steps:
(a) Controlling the moving speed of the spray gun to keep the thickness of a single layer of the coating between 0.05 and 0.1 mm;
(b) Stopping the gun for 1-min after spraying 2-3 layers, and cooling the part by using compressed air;
(c) And cooling the part to 50-60 ℃, spraying again, and stopping spraying when the thickness of the coating is required to be repeatedly coated for many times.
Preferably, the specific process of the coating processing in the step (eight) is as follows: according to the requirements of the size and the precision of parts in the pattern, an electric polishing head is adopted to polish and flatten the coating at high points, and then a bench worker is used for trimming to the size precision required by the pattern.
Preferably, the heat treatment process parameters in the step (ten) are as follows: the temperature is 140 +/-10 ℃ and the time is 4h.
Preferably, the specific process of dye penetrant inspection in step (eleven) is as follows:
(A) Dipping the coloring penetrant by a brush pen or a brush, brushing the coloring penetrant on the detected surface, waiting for 2-3 min after brushing, and repeatedly brushing for 3-4 times;
(B) After the permeation time is at least 20min, spraying and applying a developer, and observing traces in sufficient natural light or under a white light within 10-30 min;
(C) And (5) detecting whether a defect trace appears, if so, reworking and repeatedly executing the steps (one) to (ten) until no defect trace appears.
Preferably, the specific process of the strength test in the step (twelve) is as follows:
(1) The electric pump is assembled under the environment that the working environment temperature is 20 +/-10 ℃ and the relative humidity is 20-80%;
(2) Connecting the oil inlet pipe nozzle to a fuel oil test bed, blocking the oil outlet pipe nozzle, supplying pressure according to the highest design working pressure of 1.5 times, and keeping the pressure for 3min;
(3) And (5) observing whether the oil leakage phenomenon exists or not, and whether the support is permanently deformed or not after the test.
Preferably, the running-in test in the step (twelve) comprises the following specific processes:
(S1) connecting the electric pump into a test bed;
(S2) respectively operating for 5min and 10min at zero flow and full flow, and repeatedly and continuously operating for 2h;
(S3) observing whether the operation is stable or not, whether the pump outlet pressure is qualified or not, and whether abnormal abrasion and other fault phenomena exist on the surfaces of the main moving part and the support after the test.
The invention has the beneficial effects that:
the method effectively solves the problems of large heat input, easy part deformation, serious hot crack tendency, more molding body air hole defects and the like of the traditional repair method, solves the repair problem of the aluminum alloy filter screen bracket of the fuel electric pump, realizes the remanufacturing of parts, and avoids the problem that the whole fuel electric pump is replaced again due to the damage of the filter screen bracket; the repair rate and the repair effect of the damage can be obviously improved, and the scrappage of parts is reduced.
Drawings
The invention is further illustrated with reference to the following figures and examples:
FIG. 1 is a flow chart of the present invention;
FIG. 2 is a schematic structural diagram of an aluminum alloy screen bracket of an aircraft fuel electric pump;
FIG. 3 is a comparison of welded and cold sprayed repair tissue.
In the figure: 1. a screen bracket body; 2. supporting a lug; 3. forming the support lug by cold spraying; 4. and (6) pre-burying the support columns.
Detailed Description
In order to make the technical means, the creation features, the achievement purposes and the effects of the invention easy to understand, the invention is further explained in the following with the accompanying drawings and the embodiments.
As shown in figure 2, the structural schematic diagram of the aluminum alloy filter screen support of the fuel electric pump on the airplane comprises a filter screen support body 1, a support lug 2, a cold spray molding support lug 3 and an embedded support post 4. The journal stirrup 2 is used for supporting the filter screen, and the journal stirrup 2 is provided with threely at the filter screen support body 1, is 120 distributions, and the journal stirrup 2 is thin wall spare, and thickness 3mm easily breaks when the dismouting.
As shown in figure 1, the remanufacturing and repairing process of the aluminum alloy filter screen bracket of the aircraft fuel electric pump comprises the following steps:
grinding and finishing: and (3) trimming and roughly polishing the broken part of the support lug by using an electric polishing head, controlling the polishing by taking the principle of completely removing the broken source region of the support, manufacturing a U-shaped groove at the part to be molded after polishing, and polishing by using sand paper or abrasive cloth of no less than 180 to remove edge burrs and keep the port smooth.
(II) manufacturing a threaded hole: and drilling a blind hole with the depth of about 8mm near the central line position on the surface to be molded, and threading an M2 multiplied by 0.25 internal thread in the blind hole.
(III) embedding the support columns: processing an aluminum alloy strut by using a hard aluminum material (LY 12), manufacturing an M2X 0.25 external thread with the length of about 8mm at one end of the strut, coating a J-168 metal adhesive on a thread section, screwing the thread section into a blind hole, curing at room temperature for 24 hours, polishing off residual adhesive liquid by using No. 80 abrasive paper, blowing clean and dry compressed air to clean the surface to be repaired, and ensuring that no polished and processed residual scraps exist.
Further, the method for preparing the J-168 metal adhesive comprises the following steps: epoxy resin, 200# polyamide, curing agent 703 and asbestos in a proportion of 100:20:12:5, stirring for 5min, and immediately using after uniformly mixing.
(IV) protection: and (5) shielding and protecting the non-spraying area by using a high-temperature-resistant adhesive tape.
(V) cleaning: and ultrasonically cleaning the part, locally and finely cleaning the to-be-sprayed area by using a brush, and drying the surface of the part by using clean and dry compressed air after cleaning.
(VI) surface pretreatment: blowing sand to roughen a part matrix by using 60-80-mesh brown corundum sand, polishing and roughening an aluminum alloy pillar by using No. 80 silicon carbide abrasive paper, and spraying within 2 hours after pretreatment, wherein the surface to be sprayed is required to be rough and uniform and has no metallic luster and dark spots after surface pretreatment.
(VII) preheating before spraying: in order to improve the bonding performance of the coating, the parts are dried and preheated in a drying box at the temperature of 50-60 ℃, the parts to be subjected to cold spraying are picked up and touched by clean lint-free gloves or other methods for avoiding surface pollution in the preheating process, and the parts to be subjected to cold spraying are forbidden to be directly touched by hands.
(eight) spraying parts: and (5) performing additive forming by adopting cold spraying. The main technological parameters are as follows:
specification of powder: 2024 aluminum alloy and alumina mixed powder, wherein the particle size range of the powder is 5-45 μm, and the alumina accounts for 20-30%. Spraying process gas: nitrogen gas; the temperature of the spraying process is as follows: 475 to 525 ℃; spraying process pressure: 160-190 psi; spraying angle: 80 +/-10 degrees; distance of the spray gun: 15-25 mm; powder feeding amount: 10-20 g/min.
In order to prevent the parts from being over-heated in the spraying process, the moving speed of a spray gun is controlled to ensure that the thickness of a single layer of the coating is between 0.05 and 0.1mm, the spray gun is stopped for 1 to 2min after 2 to 3 layers of the coating are sprayed, the workpiece is cooled by compressed air, the spraying is carried out again when the matrix is cooled to between 50 and 60 ℃, and the spraying is stopped when the matrix is repeatedly carried out for multiple times to reach the required coating thickness.
(nine) coating processing: according to the requirements of the size and the precision of parts in the pattern, firstly, an electric polishing head is adopted to polish the high points of the coating to be flat, then, a bench worker is used for trimming the coating to the size precision required by the pattern, and after polishing, the coating is required to be smooth in transition, free of edges and corners and not inferior to Ra1.6 microns in roughness.
(ten) verification and installation: and (3) according to the assembly requirement of the fuel electric pump, assembling the filter screen into a product, fixing the filter screen, checking the gap between the main moving parts such as an impeller and a diffuser and the filter screen after fixing, wherein the gap is required to be 0.3-0.7 mm, and if the gap is not qualified, manually polishing the size of the support arm in the step (nine) to adjust the local gap.
(eleven) stress relief treatment: and (3) carrying out low-temperature tempering stress relief treatment within 24 hours after polishing is finished, wherein the heat treatment system is as follows: keeping the temperature for 4 hours at the temperature of 140 plus or minus 10 ℃.
(twelfth) dye penetrant inspection: after stress removal treatment, dipping a coloring penetrant by a brush pen or a brush, brushing the coloring penetrant on the surface to be detected, after waiting for 2-3 min, repeatedly brushing for 3-4 times to ensure that the surface to be detected is completely covered, after at least 20min of penetration, spraying and applying a developer, and observing traces in sufficient natural light or under a white light within 10-30 min, wherein the defects and traces are not allowed to be displayed, otherwise, reworking and repeatedly executing the steps (one) - (eleven) until the defects and traces are qualified.
(thirteen) Performance tests: the following performance tests were carried out according to the fuel electric pump repair process:
and (3) strength test: after the electric pump is assembled, under the conditions that the temperature of a working environment is 20 +/-10 ℃ and the relative humidity is 20-80%, the oil inlet pipe nozzle is connected into a fuel oil test bed, the oil outlet pipe nozzle is blocked, the pressure is supplied according to the highest design working pressure of 1.5 times, the pressure is kept for 3min, oil leakage and the like should not occur in the test, and the support is not allowed to permanently deform after the test.
Running-in test: the electric pump is connected into a test bed, the electric pump is respectively operated for 5min and 10min under zero flow and full flow, the electric pump is repeatedly and continuously operated for 2h, the operation is required to be stable, the pressure of the outlet of the pump is qualified, the surface quality of main moving parts and a support is decomposed and checked after the test, and abnormal abrasion and other fault phenomena are not allowed.
Through the technical scheme, compared with the prior art, as shown in fig. 3, (a) in fig. 3 shows that a large number of holes and microcracks can appear in the tissue of a repair layer for the existing welding repair, and the defects can cause the parts to expand in the using process and finally cause the parts to fail; and (b) in fig. 3 shows that the repair layer is repaired by cold spraying, the tissue state of the repair layer is good, the coating tissue can be more compact by adding alumina into the coating powder, and the porosity of the coating is only about 0.2% after measurement and calculation.
Therefore, the repairing method of the embedded support cold spray molding can solve the repairing problem of the aluminum alloy filter screen bracket of the fuel electric pump, realizes the remanufacturing of parts, avoids the problem that the whole fuel electric pump is replaced again due to the damage of the filter screen bracket, can obviously improve the repairing rate and the repairing effect of the damage and reduce the scrapping of the parts.
According to the invention, by adopting the composite method of pre-embedded strut cold spray forming, cold-state additive forming of aluminum alloy powder with better plasticity can be realized at a lower temperature, and remanufacturing of damaged parts is realized. And recovering the broken support arm of the part by using the advantage of small internal stress of cold spraying and replacing welding with cold spraying to perform additive forming.
Furthermore, the pre-embedded aluminum alloy support is formed by cold spraying, so that the structural strength of the material increase support arm is ensured.
And J-168 metal adhesive is further coated on the threaded end of the strut for fixation, and the proportion of the metal adhesive is stated, so that the combination effect of the aluminum alloy strut and the part is ensured.
The mixed powder of 2024 aluminum alloy and aluminum oxide is further adopted for spraying, a cold spraying coating with the porosity of 0.2% is prepared, the spraying process parameters are optimized, and the performance of the spraying coating is ensured.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are merely illustrative of the principles of the invention, but that various changes and modifications may be made without departing from the spirit and scope of the invention, which is defined by the appended claims. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (10)
1. The remanufacturing and repairing process of the aluminum alloy filter screen bracket of the aircraft fuel oil electric pump is characterized in that: the method comprises the following steps:
grinding and finishing: trimming and roughly polishing the broken part of the support lug by using an electric polishing head, manufacturing a part to be molded into a U-shaped groove, and then polishing by using sand paper or abrasive cloth to remove burrs and keep the end opening smooth;
(II) manufacturing a threaded hole: drilling a blind hole with the depth of 8mm near the center line position on a surface to be formed, and manufacturing M2 multiplied by 0.25 internal threads by using a screw tap;
(III) embedding the support columns: processing an aluminum alloy support column by using a hard aluminum material, manufacturing an external thread with the length of 8mmdM2 multiplied by 0.25 at one end of the support column, smearing J-168 metal adhesive on a thread section, screwing in the thread section, curing the thread section for 24 hours at room temperature, polishing residual glue solution by using abrasive paper, and blowing clean and dry compressed air to clean the surface to be repaired;
(IV) protection and cleaning: shielding and protecting a non-spraying area by using a high-temperature-resistant adhesive tape, carrying out ultrasonic cleaning on the part, carrying out local fine cleaning on the area to be sprayed by using a brush, and drying the surface of the part by using clean and dry compressed air after cleaning;
(V) surface pretreatment: blowing sand to roughen a part substrate by using 60-80 meshes of brown corundum sand, and polishing and roughening an aluminum alloy pillar by using No. 80 silicon carbide abrasive paper, wherein the surface to be sprayed is required to be rough and uniform without metallic luster and dark spots;
(VI) preheating before spraying: drying the parts in a drying box within 2 hours after pretreatment;
(VII) spraying parts: spraying by adopting cold spraying according to set process parameters;
(eight) coating processing: polishing and trimming the coating according to requirements until the coating is smooth in transition, has no edge angle, and has roughness not inferior to Ra1.6 mu m;
(nine) verification of the test and installation: assembling the parts into a product, checking whether gaps among the impeller, the diffuser and the filter screen are between 0.3 and 0.7mm, and if not, repeating the step (eight) until the gaps are between;
(ten) stress relief treatment: performing low-temperature tempering stress relief treatment within 24 hours after polishing is finished;
(eleven) dye penetrant inspection: brushing a color penetrant and spraying a developer, observing whether a defect trace appears under natural light or a white light, and if so, reworking and repeatedly executing the steps (I) to (ten) until the defect trace does not appear;
(twelfth) Performance test: and carrying out a strength test and a running-in test according to the repair process of the fuel electric pump.
2. The remanufacturing and repairing process of the aluminum alloy filter screen bracket of the aircraft fuel electric pump as claimed in claim 1, wherein the remanufacturing and repairing process comprises the following steps: the specific preparation process of the J-168 metal adhesive in the step (III) comprises the following steps: epoxy resin, 200# polyamide, curing agent 703 and asbestos in a proportion of 100:20:12:5, and stirring for 5min.
3. The remanufacturing and repairing process of the aluminum alloy filter screen bracket of the aircraft fuel electric pump as claimed in claim 1, wherein the remanufacturing and repairing process comprises the following steps: in the step (VI), the preheating temperature is 50-60 ℃.
4. The remanufacturing and repairing process of the aluminum alloy filter screen bracket of the aircraft fuel oil electric pump as claimed in claim 1, wherein the remanufacturing and repairing process comprises the following steps: the cold spraying process parameters in the step (VII) are as follows: the spraying powder is mixed powder of 2024 aluminum alloy and aluminum oxide, the particle size range of the powder is 5-45 mu m, the proportion of the aluminum oxide is 20-30%, the spraying gas is nitrogen, the spraying temperature is 475-525 ℃, the spraying pressure is 160-190 psi, the spraying angle is 80 +/-10 degrees, the distance of a spray gun is 15-25 mm, and the powder feeding amount is 10-20 g/min.
5. The remanufacturing and repairing process of the aluminum alloy filter screen bracket of the aircraft fuel electric pump as claimed in claim 1, wherein the remanufacturing and repairing process comprises the following steps: the step (VII) of cold spraying comprises the following specific processes:
(a) Controlling the moving speed of the spray gun to keep the thickness of a single layer of the coating between 0.05 and 0.1 mm;
(b) Stopping the gun for 1-min after spraying 2-3 layers, and cooling the part by using compressed air;
(c) And cooling the part to 50-60 ℃, spraying again, and stopping spraying when the thickness of the coating is required to be repeatedly coated for many times.
6. The remanufacturing and repairing process of the aluminum alloy filter screen bracket of the aircraft fuel oil electric pump as claimed in claim 1, wherein the remanufacturing and repairing process comprises the following steps: the specific process of coating processing in the step (eight) comprises the following steps: according to the size and precision requirements of parts in the pattern, an electric polishing head is adopted to polish and flatten the coating high points, and then a bench worker is used for trimming to the size precision required by the pattern.
7. The remanufacturing and repairing process of the aluminum alloy filter screen bracket of the aircraft fuel electric pump as claimed in claim 1, wherein the remanufacturing and repairing process comprises the following steps: the heat treatment process parameters in the step (ten) are as follows: the temperature is 140 +/-10 ℃ and the time is 4h.
8. The remanufacturing and repairing process of the aluminum alloy filter screen bracket of the aircraft fuel oil electric pump as claimed in claim 1, wherein the remanufacturing and repairing process comprises the following steps: the concrete process of dye penetrant inspection in the step (eleven) comprises the following steps:
(A) Dipping the coloring penetrant by a brush pen or a brush, brushing the coloring penetrant on the detected surface, waiting for 2-3 min after brushing, and repeatedly brushing for 3-4 times;
(B) After the permeation time is at least 20min, spraying and applying a developer, and observing traces in sufficient natural light or under a white light within 10-30 min;
(C) And (5) checking whether a defect trace appears, if so, reworking and repeatedly executing the steps (I) to (ten) until no defect trace appears.
9. The remanufacturing and repairing process of the aluminum alloy filter screen bracket of the aircraft fuel electric pump as claimed in claim 1, wherein the remanufacturing and repairing process comprises the following steps: the specific process of the strength test in the step (twelve) is as follows:
(1) The electric pump is assembled in the environment with the working environment temperature of 20 +/-10 ℃ and the relative humidity of 20-80%;
(2) Connecting the oil inlet pipe nozzle to a fuel oil test bed, blocking the oil outlet pipe nozzle, supplying pressure according to the highest design working pressure of 1.5 times, and keeping the pressure for 3min;
(3) And (5) observing whether the oil leakage phenomenon exists or not, and whether the support is permanently deformed or not after the test.
10. The remanufacturing and repairing process of the aluminum alloy filter screen bracket of the aircraft fuel electric pump as claimed in claim 1, wherein the remanufacturing and repairing process comprises the following steps: the running-in test in the step (twelve) comprises the following specific processes:
(S1) connecting the electric pump into a test bed;
(S2) respectively operating for 5min and 10min at zero flow and full flow, and repeatedly and continuously operating for 2h;
and (S3) observing whether the operation is stable or not, whether the pump outlet pressure is qualified or not, and whether abnormal abrasion and other fault phenomena exist on the surfaces of the main moving part and the support after the test.
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DE102006009751A1 (en) * | 2006-03-02 | 2007-09-06 | Praxair Surface Technologies Gmbh | Repairing and re-manufacturing dynamically-stressed aluminum alloy components for aircraft or aerospace applications, adds fatigue-resistant coating by cold-spraying |
CN102152074A (en) * | 2011-03-14 | 2011-08-17 | 沈阳飞机工业(集团)有限公司 | Processing method of seamless joint of aluminum alloy |
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CN107756830A (en) * | 2017-09-28 | 2018-03-06 | 国营芜湖机械厂 | One kind is applied to outfield radome damage technique for rapidly repairing method |
CN111842909A (en) * | 2019-04-28 | 2020-10-30 | 中车唐山机车车辆有限公司 | Bogie repairing method and bogie repairing system |
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CN111036520A (en) * | 2019-11-21 | 2020-04-21 | 大连长丰实业总公司 | Method for in-situ reinforced repairing of airplane landing gear beam cracks |
CN112916998A (en) * | 2021-02-01 | 2021-06-08 | 中车工业研究院有限公司 | Deep hole structure repairing method based on friction plunger welding and stopper rod applied by same |
CN113245562A (en) * | 2021-06-22 | 2021-08-13 | 北京煜鼎增材制造研究院有限公司 | Equipment for preparing metal test piece and structural part by high-energy beam |
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