CN107299217A - A kind of aeroengine components surface residual stress electromagnetic field regulates and controls method - Google Patents
A kind of aeroengine components surface residual stress electromagnetic field regulates and controls method Download PDFInfo
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- CN107299217A CN107299217A CN201710418215.9A CN201710418215A CN107299217A CN 107299217 A CN107299217 A CN 107299217A CN 201710418215 A CN201710418215 A CN 201710418215A CN 107299217 A CN107299217 A CN 107299217A
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D10/00—Modifying the physical properties by methods other than heat treatment or deformation
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F3/00—Changing the physical structure of non-ferrous metals or alloys by special physical methods, e.g. treatment with neutrons
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/20—Recycling
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Abstract
Regulate and control method the invention discloses a kind of aeroengine components surface residual stress electromagnetic field, comprise the following steps：The aeroengine components to brand-new carry out electromagnetic field regulation and control processing at normal temperatures, processing time is 3~600s, the electromagnetic field is coupled to form by alternating magnetic field and impulse electric field, the intensity of alternating magnetic field is 500~30000A/m, the frequency of alternating magnetic field is 1~1000Hz, the peak inrush current of impulse electric field is 5~20000A, and the pulse period of impulse electric field is 0.01~1.0s.Present invention eliminates traditional shot-blast process, regulate and control construction material top layer using electromagnetic field and nearly surface residual stress is distributed, the accuracy of manufacture and surface roughness can be improved, shorten technological process, reduction manufacturing cost and cycle.
Description
Technical field
The invention belongs to aeroengine components technical field of surface, and in particular to a kind of aeroengine components table
Face residual stress electromagnetic field regulation and control method.
Background technology
Titanium alloy, powder metallurgy superalloy etc. have excellent high specific strength, high ratio modulus, high temperature resistant, anti-oxidant and fire-retardant
It is the main material of aero-engine key components and parts etc. performance.Blade, disk, the casing of active service engine blower and compressor
Mainly manufactured Deng component using such alloy.These key components and parts under arms in bear high temperature, vibration, pneumatic, centrifugal force etc.
Load, working environment is severe, and its surface texture state and residual stress distribution require very strict.
It is main on aircraft industry at present to improve engine component surface texture state and residual stress using shot peening strengthening
Distribution situation, is exactly specifically to make a large amount of bullets vertical at high speed by compressed air or continuously hammer alloy at a certain angle
Component surface, overlapping concave point is caused in cold worked form on surface, so that chilling layer and residual compressive stress field are formed, so that
Be conducive to mechanical strength and the life-span of lifting member.However, shot-blast process can make thin-wall member occur a certain degree of deformation, together
Shi Zeng great surface roughness values, influence its service behaviour；Moreover, shot-blast process improperly in the case of can also be produced in component surface
Damage and micro-crack, even result in component and scrap when serious.Therefore, exploitation engine component residual stress regulation and control new method, is replaced
Generation or part substitute stress peening process, global problem urgently to be resolved hurrily in being manufactured as aero-engine.
Regulate and control component residual stress distribution using electromagnetic field treatment technology, member for prolonging service life is a kind of new skill
Art, have the advantages that high treating effect, time it is short, without additional deformation and green non-pollution.At present, the electricity on residual stress
Magnetic field control technique, some existing document reports, but regulation and control method is generally magnetic field processing, and regulation and control object almost all is directed to steel
Deng ferrimagnet.Using electromagnetic field regulation and control nonferromugnetic material particularly titanium alloy, powder metallurgy superalloy component residual stress
Report but there is not yet.Therefore, the present invention proposes a kind of aeroengine components electromagnetic field control technique, for regulating and controlling brand-new
Aeroengine components surface residual stress, to substitute stress peening process, removes mechanical enhancer " dead angle ", improves manufacture essence
Degree, shortens technological process, reduction manufacturing cost and cycle.
The content of the invention
The defect of damage can be produced to component surface to solve shot-blast process in background technology, the present invention provides a kind of aviation
Engine component surface residual stress electromagnetic field regulates and controls method, and it eliminates traditional shot-blast process, and component is regulated and controled using electromagnetic field
Material surface and the distribution of nearly surface residual stress, can improve the accuracy of manufacture and surface roughness, shorten technological process, reduction system
Cause this and cycle.
The technical solution adopted for the present invention to solve the technical problems is：
A kind of aeroengine components surface residual stress electromagnetic field regulates and controls method, comprises the following steps：It is right at normal temperatures
The aeroengine components of brand-new carry out electromagnetic field regulation and control processing, and processing time is 3~600s, and the electromagnetic field is by alternating magnetic field
It is coupled to form with impulse electric field, the intensity of alternating magnetic field is 500~30000A/m, and the frequency of alternating magnetic field is 1~1000Hz, arteries and veins
The peak inrush current for rushing electric field is 5~20000A, and the pulse period of impulse electric field is 0.01~1.0s.
By above-mentioned technical proposal, the alternating current that the alternating magnetic field is exported by power supply is in containing cored magnet exciting coil
Produce.
By above-mentioned technical proposal, the impulse electric field exports periodic Pulse Electric Current with High Density by the pulse power, and
Periodicity electric field is produced inside processed material.
By above-mentioned technical proposal, the aeroengine components are added by precision forging, hot investment casting, powder metallurgy or numerical control
Work technique makes.
The present invention, has the advantages that：Present invention eliminates the shot-blast process of aeroengine components, so as to eliminate
The deformation that shot-blast process is caused to thin-wall member, produces damage in the case of thoroughly avoiding shot-blast process improperly in component surface
Micro-crack is injured, but directly using electromagnetic field control technique regulation and control construction material top layer and the distribution of nearly surface residual stress, can
To improve the accuracy of manufacture and surface roughness, shorten technological process, save production cost and period.
The present invention operation principle be：Due to brand-new aeroengine components in process, surface metal dislocation, sky
The increase of the crystal defects such as position, causes a certain degree of distortion of lattice, changes the ordered state of original lattice atoms, internal material
Energy distribution is uneven, causes top layer to produce residual stress, present invention eliminates shot-blast process, but directly brand-new aviation is sent out
Motivation component carries out electromagnetic field regulation and control processing, and because electric field produces instantaneous heat energy in component surface, magnetic field is in material magnetics particle
Middle internal generation electromagnetic force, can cause the high-energy regions such as component crystal boundary, sub boundary to make in the superposition of energy of electromagnetic field, heat energy
Under, more than the transition energy of microcell phase transformation, and then precipitation secondary phase particle is undergone phase transition, send out the form of matrix phase (α phases)
It is raw to change, and play a part of strong pinning dislocation and substructure, the motion and crystal boundary, sub boundary migration of dislocation are hindered, is caused
Compression is integrally raised.Because brand-new aeroengine components internal energy is distributed and uneven, locally occur second phase particles
Separate out and also differed with the probability of α phases deformity, then pass through application external electromagnetic field so that aeroengine components internal energy
Also higher microcell is undergone phase transition higher and internal stress, the higher internal stress in release part, and then make remnants to a certain extent
Compression uniformity gets a promotion.
Embodiment
In order to make the purpose , technical scheme and advantage of the present invention be clearer, with reference to embodiments, to the present invention
It is further elaborated.It should be appreciated that specific embodiment described herein is not used to limit only to explain the present invention
The fixed present invention.
In the preferred embodiment, a kind of aeroengine components surface residual stress electromagnetic field regulation and control method,
Comprise the following steps：At normal temperatures the aeroengine components of brand-new are carried out with electromagnetic field regulation and control processing, processing time is 3~
600s, the electromagnetic field is coupled to form by alternating magnetic field and impulse electric field, and the intensity of alternating magnetic field is 500~30000A/m, is handed over
The frequency of varying magnetic field is 1~1000Hz, and the peak inrush current of impulse electric field is 5~20000A, the pulse period of impulse electric field
For 0.01~1.0s.
In a preferred embodiment of the invention, the alternating current that the alternating magnetic field is exported by power supply is encouraged containing cored
Produced in magnetic coil.
In a preferred embodiment of the invention, the impulse electric field exports periodic high density pulse electricity by the pulse power
Stream, and the generation periodicity electric field inside processed material.
In a preferred embodiment of the invention, the aeroengine components are by precision forging, hot investment casting, powder metallurgy
Or numerical control processing technology makes.
It is exemplified below three embodiments of the present invention.
Embodiment 1
When aeroengine components are TC11 titanium alloy compressor blades, the present invention comprises the following steps：
S1, titanium alloy compressor blade is made using techniques such as precision forging, digital control processings；
S2, the titanium alloy blade of brand-new is placed in special electromagnetic field generator at normal temperatures, utilizes electromagnetic field pair
Titanium alloy blade is handled, and electromagnetic field regulation and control processing time is 3~10s, and electromagnetic field is mainly by alternating magnetic field and impulse electric field
It is coupled to form, magnetic field main process parameter is 500~5000A/m of magnetic field intensity, 1~20Hz of frequency, electric field is mainly handled
Technological parameter be 5~500A of peak inrush current, pulse period be 0.01~0.08s.
Surface is carried out to blade using X-ray diffraction method and nearly surface residual stress is tested.As a result find, with brand-new blade
Surface residual stress is compared, and 17%-33%, residual stress are improved through electromagnetic field modulation process processing rear blade residual compressive stress
Mean square deviation reduces 15MPa, that is, eliminates the uneven result of residual stress distribution that precision forging is caused with machining；Together
When blade form stronger residual compressive stress field along layer depth direction Shang Jin top layers, wherein 19~41 μm of region residual pressures of layer depth should
The blade of power brand-new improves 91%.
Embodiment 2
When aeroengine components are TC17 titanium alloy turbo blades, the present invention comprises the following steps：
S1, titanium alloy turbo blade is made using techniques such as hot investment casting, digital control processings；
S2, the titanium alloy blade of brand-new is placed in special electromagnetic field generator at normal temperatures, utilizes electromagnetic field pair
Blade carries out regulation and control processing, and electromagnetic field regulation and control processing time is 100~160s, and electromagnetic field is mainly by alternating magnetic field and impulse electric field
It is coupled to form, magnetic field main process parameter is 10000~15000A/m of magnetic field intensity, 40~50Hz of frequency, electric field is main
Handling process parameter be 8000~120000A of peak inrush current, pulse period be 0.45~0.75s.
Surface is carried out to blade using X-ray diffraction method and nearly surface residual stress is tested.As a result find, the leaf with brand-new
Piece surface residual stress is compared, and 10%-15% is improved through electromagnetic field modulation process processing rear blade residual compressive stress, and remnants should
Power mean square deviation reduces 37MPa, that is, eliminates hot investment casting, is machined the uneven result of residual stress distribution caused；
Simultaneously stronger residual compressive stress field, wherein 18~35 μm of region remnants of layer depth are formd along blade along layer depth direction Shang Jin top layers
The blade of compression brand-new improves 55%.
Embodiment 3
When aeroengine components are high-temperature alloy turbine disc, the present invention comprises the following steps：
S1, high-temperature alloy turbine disc is made using techniques such as powder metallurgy；
S2, the high-temperature alloy turbine disc of brand-new is placed in special electromagnetic field generator at normal temperatures, utilizes electromagnetism
The turbine disk is handled, processing time is 500~600s, magnetic field main process parameter be magnetic field intensity 25000~
30000A/m, 800~1000Hz of frequency, electric field main process parameter are 18000~20000A of peak inrush current, pulse
Cycle is 0.8~1.0s.
Surface is carried out to the turbine disk using X-ray diffraction method and nearly surface residual stress is tested.As a result find, with brand-new
Turbine disk surface residual stress is compared, and turbine disk residual compressive stress improves 20%-25% after being handled through electromagnetic field modulation process,
Residual stress mean square deviation reduces 21MPa, that is, eliminates the uneven result of residual stress distribution that powder metallurgy etc. is caused；Simultaneously
The turbine disk forms stronger residual compressive stress field along layer depth direction Shang Jin top layers, and wherein 20~32 μm of region residual pressures of layer depth should
The turbine disk of power brand-new improves 72%.
It should be appreciated that for those of ordinary skills, can according to the above description be improved or converted,
And all these modifications and variations should all belong to the protection domain of appended claims of the present invention.
Claims (4)
1. a kind of aeroengine components surface residual stress electromagnetic field regulates and controls method, it is characterised in that this method includes following
Step：The aeroengine components to brand-new carry out electromagnetic field regulation and control processing at normal temperatures, and processing time is 3~600s, described
Electromagnetic field is coupled to form by alternating magnetic field and impulse electric field, and the intensity of alternating magnetic field is 500~30000A/m, the frequency of alternating magnetic field
Rate is 1~1000Hz, and the peak inrush current of impulse electric field is 5~20000A, pulse period of impulse electric field for 0.01~
1.0s。
2. aeroengine components surface residual stress electromagnetic field according to claim 1 regulates and controls method, it is characterised in that
The alternating current that the alternating magnetic field is exported by power supply is produced in containing cored magnet exciting coil.
3. aeroengine components surface residual stress electromagnetic field according to claim 1 regulates and controls method, it is characterised in that
The impulse electric field exports periodic Pulse Electric Current with High Density by the pulse power, and is produced periodically inside processed material
Electric field.
4. aeroengine components surface residual stress electromagnetic field according to claim 1 regulates and controls method, it is characterised in that
The aeroengine components are made by precision forging, hot investment casting, powder metallurgy or numerical control processing technology.
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108546801A (en) * | 2018-04-27 | 2018-09-18 | 北京科技大学 | A method of extending hot-forging die service life using magnetic, electric field compound action |
| CN111855717A (en) * | 2020-05-29 | 2020-10-30 | 中国人民解放军陆军装甲兵学院 | Method for analyzing influence of pulsed magnetic field treatment on residual stress of metal part |
| CN112251597A (en) * | 2020-09-29 | 2021-01-22 | 武汉理工大学 | High-performance bearing matrix multi-energy-field co-forming manufacturing method |
| CN112935256A (en) * | 2021-01-26 | 2021-06-11 | 四川大学 | Method for modifying non-ferromagnetic powder sintered metal parts based on pulsed magnetic field |
| CN113667915A (en) * | 2021-07-27 | 2021-11-19 | 四川大学 | Treatment method for improving fatigue life of titanium alloy by using pulsed magnetic field treatment |
| CN113699472A (en) * | 2021-09-16 | 2021-11-26 | 四川大学 | Method for regulating residual stress of bearing frame of aluminum alloy engine through electromagnetic coupling |
| CN113718340A (en) * | 2021-08-25 | 2021-11-30 | 中国联合重型燃气轮机技术有限公司 | Method for controlling recrystallization of single crystal superalloys |
| CN113774301A (en) * | 2021-09-16 | 2021-12-10 | 四川大学 | Method for prolonging fatigue life of welding seam of titanium alloy electron beam welding part through electromagnetic coupling treatment |
| CN114032382A (en) * | 2021-11-10 | 2022-02-11 | 中国航发北京航空材料研究院 | Equipment for strengthening titanium alloy plate by pulse magnetic field |
| CN114309231A (en) * | 2021-12-20 | 2022-04-12 | 华中科技大学 | Device and method for eliminating and regulating residual stress of alloy ring piece |
| CN116694871A (en) * | 2023-05-31 | 2023-09-05 | 武汉理工大学 | Electromagnetic impact improving method for rolling contact fatigue performance of bearing steel |
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| CN108546801B (en) * | 2018-04-27 | 2019-07-12 | 北京科技大学 | A method of extending hot-forging die service life using magnetic, electric field compound action |
| CN108546801A (en) * | 2018-04-27 | 2018-09-18 | 北京科技大学 | A method of extending hot-forging die service life using magnetic, electric field compound action |
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| CN112251597A (en) * | 2020-09-29 | 2021-01-22 | 武汉理工大学 | High-performance bearing matrix multi-energy-field co-forming manufacturing method |
| CN112251597B (en) * | 2020-09-29 | 2021-09-07 | 武汉理工大学 | High-performance bearing matrix multi-energy-field co-forming manufacturing method |
| CN112935256B (en) * | 2021-01-26 | 2023-02-17 | 成都昆吾科技有限公司 | Method for modifying non-ferromagnetic powder sintered metal parts based on pulsed magnetic field |
| CN112935256A (en) * | 2021-01-26 | 2021-06-11 | 四川大学 | Method for modifying non-ferromagnetic powder sintered metal parts based on pulsed magnetic field |
| CN113667915A (en) * | 2021-07-27 | 2021-11-19 | 四川大学 | Treatment method for improving fatigue life of titanium alloy by using pulsed magnetic field treatment |
| CN113718340A (en) * | 2021-08-25 | 2021-11-30 | 中国联合重型燃气轮机技术有限公司 | Method for controlling recrystallization of single crystal superalloys |
| CN113774301A (en) * | 2021-09-16 | 2021-12-10 | 四川大学 | Method for prolonging fatigue life of welding seam of titanium alloy electron beam welding part through electromagnetic coupling treatment |
| CN113699472A (en) * | 2021-09-16 | 2021-11-26 | 四川大学 | Method for regulating residual stress of bearing frame of aluminum alloy engine through electromagnetic coupling |
| CN114032382A (en) * | 2021-11-10 | 2022-02-11 | 中国航发北京航空材料研究院 | Equipment for strengthening titanium alloy plate by pulse magnetic field |
| CN114032382B (en) * | 2021-11-10 | 2023-01-13 | 中国航发北京航空材料研究院 | Equipment for strengthening titanium alloy plate by pulse magnetic field |
| CN114309231A (en) * | 2021-12-20 | 2022-04-12 | 华中科技大学 | Device and method for eliminating and regulating residual stress of alloy ring piece |
| CN114309231B (en) * | 2021-12-20 | 2022-11-01 | 华中科技大学 | Device and method for eliminating and regulating residual stress of alloy ring piece |
| CN116694871A (en) * | 2023-05-31 | 2023-09-05 | 武汉理工大学 | Electromagnetic impact improving method for rolling contact fatigue performance of bearing steel |
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