CN117683997A - Device and method for strengthening aeroengine blade by pulse magnetic field - Google Patents
Device and method for strengthening aeroengine blade by pulse magnetic field Download PDFInfo
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- CN117683997A CN117683997A CN202311557953.3A CN202311557953A CN117683997A CN 117683997 A CN117683997 A CN 117683997A CN 202311557953 A CN202311557953 A CN 202311557953A CN 117683997 A CN117683997 A CN 117683997A
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- 238000000034 method Methods 0.000 title claims abstract description 28
- 238000005728 strengthening Methods 0.000 title claims abstract description 27
- 230000000694 effects Effects 0.000 claims abstract description 23
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 22
- 239000004917 carbon fiber Substances 0.000 claims abstract description 22
- 239000002131 composite material Substances 0.000 claims abstract description 22
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 22
- 239000010410 layer Substances 0.000 claims description 20
- 230000006698 induction Effects 0.000 claims description 4
- 239000002344 surface layer Substances 0.000 claims description 4
- 239000003990 capacitor Substances 0.000 claims description 3
- 238000007599 discharging Methods 0.000 claims description 3
- 238000009413 insulation Methods 0.000 claims description 2
- 239000000463 material Substances 0.000 description 17
- 238000005516 engineering process Methods 0.000 description 4
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 3
- 229910001069 Ti alloy Inorganic materials 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 229910045601 alloy Inorganic materials 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- UQZIWOQVLUASCR-UHFFFAOYSA-N alumane;titanium Chemical compound [AlH3].[Ti] UQZIWOQVLUASCR-UHFFFAOYSA-N 0.000 description 2
- 239000010949 copper Substances 0.000 description 2
- 229910052802 copper Inorganic materials 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 229910001369 Brass Inorganic materials 0.000 description 1
- 238000007545 Vickers hardness test Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000010951 brass Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000002500 effect on skin Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000005468 ion implantation Methods 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000035699 permeability Effects 0.000 description 1
- 238000005480 shot peening Methods 0.000 description 1
- 238000004381 surface treatment Methods 0.000 description 1
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- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The application provides a device for strengthening aero-engine blades by a pulsed magnetic field, which comprises: the magnetic collector device is arranged in the discharge loop and is used for amplifying current in the discharge loop; the aero-engine blade is arranged in the middle of the magnetic collector; the insulating layer is arranged between the magnetic collector and the aero-engine blade; the insulating layer has the function of preventing the magnetic collector from conducting current with the aero-engine blade; the carbon fiber composite material fastening barrel is arranged at the periphery of the magnetic collector; the application also provides a method for strengthening the aero-engine blade by the pulse magnetic field; aiming at the characteristics of special-shaped and curved surfaces of the aero-engine blade, the invention adopts the magnetic collectors with two sides shaped along with each other and tightly attached to the blade to be reinforced, and strengthens the surface of the blade by utilizing the near source effect of the pulse magnetic field.
Description
Technical Field
The application belongs to the technical field of metal material surface strengthening, and particularly relates to a device and a method for strengthening an aeroengine blade by a pulse magnetic field.
Background
The blade is used as a key core part of the aeroengine, plays an important role in improving the comprehensive performance of the engine, and is particularly important in researching the surface strengthening technology of the aeroengine blade.
Although the traditional surface treatment methods, such as laser impact, ion implantation, shot peening and the like, achieve the aim of enhancing the surface performance of the engine blade, some technologies can improve certain performance of the blade and simultaneously weaken the other performance; some technologies still have certain inherent limitations due to process reasons, so that micro deformation and the like occur on the surface of the blade.
In addition, the irregular shape of the engine blade also makes many surface modification techniques susceptible to uneven handling during implementation.
The pulsed magnetic field technology is an emerging material preparation or modification treatment method as an electromagnetic process with high energy density, which is obtained by the instantaneous discharge of high voltage and large capacitance in a discharge loop. The material to be processed in the loop is affected by exciting current, and the surface layer of the material can generate stronger induction current, namely skin effect.
According to the calculation formula of skin depth(omega angular frequency; mu magnetic permeability; sigma conductivity) it is known that the conductivity of a material is a key parameter affecting the strengthening effect of a pulsed magnetic field. Whereas the electrical conductivity of materials commonly used for aeroengines, such as titanium alloys, is very low, 5.85 x 10 at room temperature 5 S/m is only 1/100 of the conductivity of copper, and the same problems exist in materials such as titanium-aluminum alloy, high-temperature alloy and the like.
When the pulse magnetic field is applied to the material, the formed induced current cannot be concentrated on the surface of the material, even the whole material is distributed with current, and the material cannot form pressure difference due to the magnetic field force, so that the strengthening effect cannot be achieved.
Disclosure of Invention
In view of the foregoing technical problem, in a first aspect, the present application provides a device for strengthening an aero-engine blade by using a pulsed magnetic field, the device comprising:
the magnetic collector device is arranged in the discharge loop and is used for amplifying current in the discharge loop, wherein a gap is reserved between the magnetic collector device and the discharge loop;
the aero-engine blade is arranged in the middle of the magnetic collector, and the aero-engine blade is tightly attached to the magnetic collector;
the insulating layer is arranged between the magnetic collector and the aero-engine blade; the insulating layer has the function of preventing the magnetic collector from conducting current with the aero-engine blade;
the carbon fiber composite material fastening barrel is arranged at the periphery of the magnetic collector; the carbon fiber composite material hooping barrel and the magnetic collector are the same in length and are tightly sleeved on the periphery of the magnetic collector; the carbon fiber composite material clamping barrel has the function of limiting the magnetic collector from bouncing and insulating.
Preferably, the magnetic collector includes:
a first magnetic collector;
the second magnetic collector is symmetrically arranged in the discharge loop with the first magnetic collector; the aero-engine blade is arranged between the first magnetic collector and the second magnetic collector and is tightly attached to the first magnetic collector and the second magnetic collector.
Preferably, the whole first magnetic collector is in a semicircular structure, the outer side is identical to the shape of a solenoid in the discharge loop, and the inner side is identical to the shape of one side of the blade to be reinforced.
Preferably, the second magnetic collector is in a semicircular structure, the outer side is identical to the shape of a solenoid in the discharge loop, and the inner side is identical to the shape of the other side of the blade to be reinforced.
Preferably, the insulating layer is disposed between the first magnetic collector, the second magnetic collector and the aero-engine blade, and has a function of preventing conduction of current in the magnetic collector and the aero-engine blade.
Preferably, the carbon fiber composite material clamping barrel is tightly sleeved on the periphery of the magnetic collector, and has the functions of limiting the magnetic collector from bouncing and insulating.
Preferably, the apparatus further comprises:
pulse magnetic field generating device
The pulse magnetic field generating device forms a discharge loop, and the discharge current in the discharge loop is high-frequency and high-energy current, so that the induction current formed on the surface layer of the aero-engine blade is more concentrated, and the realization of the surface strengthening effect of the aero-engine blade is more facilitated.
In a second aspect, the present application also provides a method of pulsed magnetic field strengthening an aircraft engine blade, the method comprising:
inserting the engine blade to be reinforced into the middle of Huang Lazhi and embedding the engine blade into the central concave part of the magnetic collector;
combining the first magnetic collector and the second magnetic collector, and sleeving a carbon fiber composite material fastening barrel on the outer layer to complete the assembly work of the parts;
connecting a conductive straight rod led out by a solenoid with a discharge binding post of a high-voltage pulse power supply unit, and fastening the binding post by using a bolt;
and charging the capacitor to the voltage of 10kV, then opening a high-voltage discharge switch, and discharging the loop to finish the primary impact process.
The application has the following beneficial technical effects:
aiming at the characteristics of special shape and curved surface of the aero-engine blade, the invention adopts the magnetic collectors with two sides being shaped and tightly attached to the blade to be reinforced, and utilizes the near source effect of the pulse magnetic field to carry out the strengthening treatment on the surface of the blade, thereby solving the problem that the material of the aero-engine blade has low conductivity and is difficult to strengthen by the pulse magnetic field, and ensuring that the strengthening effect of the aero-engine blade is more uniform.
Drawings
FIG. 1 is a schematic diagram of a circuit according to an embodiment of the present invention;
FIG. 2 is a cross-sectional view of an apparatus according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a device according to an embodiment of the present invention;
FIG. 4 is a graph showing the comparison of Vickers hardness results of a preferred embodiment of the present invention applied to TC4 materials;
wherein: 1-a magnetic collector; 2-an insulating layer; 3-leaf blades; 4-hooping barrel.
Detailed Description
The invention discloses a method and a device for strengthening an aeroengine blade by a pulse magnetic field, which aim at the characteristics of special shape and curved surface of the aeroengine blade, adopt a magnetic collector with two sides being shaped along with each other and tightly attached to the blade to be strengthened, and strengthen the surface of the blade by utilizing the near source effect of the pulse magnetic field. Comprising the following steps: a set of magnetic field concentration tool, namely a magnetic collector, is arranged in the pulse magnetic field generating device, the part to be strengthened of the engine blade is arranged in the center of the magnetic collector, the shape of the center of the magnetic collector is consistent with that of the blade, the magnetic collector is tightly attached to the blade, an insulating layer is arranged between the magnetic collector and the blade to prevent current conduction, and the periphery of the magnetic collector is wrapped with a carbon fiber composite material tight barrel to bind. When the loop discharges, the surface of the magnetic collector in the loop can generate induced current and is also the exciting current of the blade to be reinforced, and the surface of the blade in the center of the magnetic collector can also generate strong induced current under the influence of the near source effect. Magnetic pressure up to GPa level can be formed between the magnetic collector and the reverse current generated on the surface of the blade and acts on the surface of the blade to be reinforced. By the method and the device, the aim of strengthening the surface of the special-shaped and curved aero-engine blade by the pulse magnetic field is fulfilled.
Referring to fig. 1-4, the invention provides a method and a device for strengthening an aero-engine blade by a pulse magnetic field, wherein the method comprises the following steps: the pulse magnetic field near source effect can play a very strong role in amplifying magnetic field force when a part to be reinforced is tightly attached to the exciting current generating device, namely, the pulse magnetic field near source effect, and the defect of non-centralized induced current distribution caused by low conductivity of a material can be overcome by the effect of amplifying the magnetic field force when the two surfaces are sufficiently close.
In an embodiment of the present application, an apparatus includes:
and the magnetic collector device is arranged in the discharge loop and is used for amplifying the current in the discharge loop, wherein a gap is reserved between the magnetic collector device and the discharge loop.
And the aero-engine blade is arranged in the middle of the magnetic collector, wherein the aero-engine blade is tightly attached to the magnetic collector.
The insulating layer is arranged between the magnetic collector and the aero-engine blade; the insulating layer has the function of preventing the magnetic collector from conducting current with the aero-engine blade;
the carbon fiber composite material fastening barrel is arranged at the periphery of the magnetic collector; the carbon fiber composite material hooping barrel and the magnetic collector are the same in length and are tightly sleeved on the periphery of the magnetic collector; the carbon fiber composite material clamping barrel has the function of limiting the magnetic collector from bouncing and insulating.
Wherein, the concentrator includes:
a first magnetic collector;
the second magnetic collector is symmetrically arranged in the discharge loop with the first magnetic collector; the aero-engine blade is arranged between the first magnetic collector and the second magnetic collector and is tightly attached to the first magnetic collector and the second magnetic collector.
The first magnetic collector is of a semicircular structure, the outer side of the first magnetic collector is identical to the shape of a solenoid in a discharge loop, and the inner side of the first magnetic collector is identical to the shape of one side of a blade to be reinforced; the second magnetic collector is of a semicircular structure, the outer side of the second magnetic collector is identical to the shape of a solenoid in a discharge loop, and the inner side of the second magnetic collector is identical to the shape of the other side of the blade to be reinforced.
Wherein, the thickness of the insulating layer is as thin as possible and the insulating effect is good. The insulation layer is arranged between the first magnetic collector, the second magnetic collector and the aero-engine blade, and has the function of preventing the magnetic collector from conducting current with the aero-engine blade.
Wherein, the carbon fiber composite material hooping barrel is as thin as possible. The carbon fiber composite material clamping barrel is tightly sleeved on the periphery of the magnetic collector, and has the functions of limiting the magnetic collector from bouncing and insulating.
Wherein the apparatus further comprises:
pulse magnetic field generating device
The pulse magnetic field generating device forms a discharge loop, and the discharge current in the discharge loop is high-frequency and high-energy current, so that the induction current formed on the surface layer of the aero-engine blade is more concentrated, and the realization of the surface strengthening effect of the aero-engine blade is more facilitated.
The invention has the following technical effects:
aiming at the characteristics of special shape and curved surface of the aero-engine blade, the invention adopts the magnetic collectors with two sides being shaped and tightly attached to the blade to be reinforced, and utilizes the near source effect of the pulse magnetic field to carry out the strengthening treatment on the surface of the blade, thereby solving the problem that the material of the aero-engine blade has low conductivity and is difficult to strengthen by the pulse magnetic field, and ensuring that the strengthening effect of the aero-engine blade is more uniform.
In other embodiments of the present application, referring to fig. 1-4, the present invention provides a method and an apparatus for strengthening an aero-engine blade by using a magnetic field generating device with high voltage and large capacitance and a magnetic collector to perform surface strengthening treatment on the aero-engine blade, where the apparatus mainly comprises an upper magnetic collector, a lower magnetic collector, and an insulating layer, as shown in fig. 2.
Referring to fig. 1-3, one embodiment of the present invention is as follows:
1. tool preparation
A solenoid was fabricated using 3mm x 5mm flat copper wire wound 30 turns with an inside diameter of 90mm and a length of 150mm. The magnetic collectors 1-1 and 1-2 are made of red copper, the length is 150mm, the outer diameter is 80mm, the radius of the upper bottom surface of each upper bottom surface is 10mm, the radius of the lower bottom surface is 35mm, the height of each lower bottom surface is 60mm, and the shape of the core of the magnetic collector is identical to the shape of the blade to be reinforced. Two layers of yellow wax paper with the thickness of 0.02mm are paved between the upper and lower magnetic collectors as insulating layers. The periphery of the magnetic collector is wrapped with a carbon fiber composite material tightening barrel with the length of 150mm, the inner diameter of 80mm and the thickness of 3 mm.
2. Implementation steps
(1) Inserting the engine blade to be reinforced into the middle of Huang Lazhi and embedding the engine blade into the central concave part of the magnetic collector;
(2) Combining the upper and lower magnetic collectors and sleeving a carbon fiber composite material clamping barrel on the outer layer to complete the assembly work of the parts;
(3) Connecting a conductive straight rod led out by a solenoid with a discharge binding post of a high-voltage pulse power supply unit, and fastening the binding post by using a bolt;
(4) Charging the capacitor to a voltage of 10kV, then opening a high-voltage discharge switch, and discharging the loop to finish a primary impact process;
(5) The impulse voltage and the impulse times can be adjusted according to actual needs.
(6) FIG. 4 shows the Vickers hardness test results of the sample before and after impact of TC4 titanium alloy with pulse magnetic field using the method and device, showing that the maximum hardness of the sample after 20 times of impact is improved by 7.5% compared with the original hardness, and confirming the effectiveness of the method and device.
The invention discloses a method and a device for strengthening an aeroengine blade by a pulse magnetic field, which aim at the characteristics of special shape and curved surface of the aeroengine blade, adopt a magnetic collector with two sides being shaped along with each other and tightly attached to the blade to be strengthened, and strengthen the surface of the blade by utilizing the near source effect of the pulse magnetic field.
The method specifically comprises the following steps: a set of magnetic field concentration tool, namely a magnetic collector, is arranged in the pulse magnetic field generating device, the part to be strengthened of the engine blade is arranged in the center of the magnetic collector, the shape of the center of the magnetic collector is consistent with that of the blade, the magnetic collector is tightly attached to the blade, an insulating layer is arranged between the magnetic collector and the blade to prevent current conduction, and the periphery of the magnetic collector is wrapped with a carbon fiber composite material tight barrel to bind.
When the loop discharges, the surface of the magnetic collector in the loop can generate induced current and is also the exciting current of the blade to be reinforced, and the surface of the blade in the center of the magnetic collector can also generate strong induced current under the influence of the near source effect. Magnetic pressure up to GPa level can be formed between the magnetic collector and the reverse current generated on the surface of the blade and acts on the surface of the blade to be reinforced. By the method and the device, the aim of strengthening the surface of the special-shaped and curved aero-engine blade by the pulse magnetic field is fulfilled.
The magnetic collector in the loop can be made of brass or other high-conductivity materials. The method is implemented according to the pulse magnetic field near source effect, and the central magnetic field enhancement parts of the two side magnetic collectors are tightly attached to the surfaces of the blades to be enhanced.
The method is implemented according to the pulse magnetic field near source effect, and the shape of the central magnetic field enhancement parts of the two side magnetic collectors is changed along with the shape of the blade to be enhanced. An insulating layer is arranged between the magnetic collector and the blade to prevent current conduction. The material of the blade to be reinforced can be low-conductivity materials such as titanium alloy, titanium-aluminum alloy, high-temperature alloy and the like. The length of the carbon fiber composite material hooping barrel is the same as that of the magnetic collector, and the carbon fiber composite material hooping barrel is tightly sleeved on the periphery of the magnetic collector.
Claims (8)
1. An apparatus for pulsed magnetic field strengthening of aircraft engine blades, the apparatus comprising:
the magnetic collector device is arranged in the discharge loop and is used for amplifying current in the discharge loop, wherein a gap is reserved between the magnetic collector device and the discharge loop;
the aero-engine blade is arranged in the middle of the magnetic collector, and the aero-engine blade is tightly attached to the magnetic collector;
the insulating layer is arranged between the magnetic collector and the aero-engine blade; the insulating layer has the function of preventing the magnetic collector from conducting current with the aero-engine blade;
the carbon fiber composite material fastening barrel is arranged at the periphery of the magnetic collector; the carbon fiber composite material hooping barrel and the magnetic collector are the same in length and are tightly sleeved on the periphery of the magnetic collector; the carbon fiber composite material clamping barrel has the function of limiting the magnetic collector from bouncing and insulating.
2. The apparatus of claim 1, wherein the concentrator comprises:
a first magnetic collector;
the second magnetic collector is symmetrically arranged in the discharge loop with the first magnetic collector; the aero-engine blade is arranged between the first magnetic collector and the second magnetic collector and is tightly attached to the first magnetic collector and the second magnetic collector.
3. The apparatus of claim 2, wherein the first concentrator is formed in a semicircular structure as a whole, and has the same shape as the solenoid in the discharge circuit on the outside and the same shape as the side of the blade to be reinforced on the inside.
4. The device according to claim 2, wherein the second magnetic collector has a semicircular structure as a whole, the outer side is identical to the shape of the solenoid in the discharge circuit, and the inner side is identical to the shape of the other side of the blade to be reinforced.
5. The apparatus of claim 2, wherein the insulating layer is disposed between the first concentrator, the second concentrator, and the aircraft engine blade, and has the effect of preventing electrical conduction in the concentrator and the aircraft engine blade.
6. The device of claim 1, wherein the carbon fiber composite material clamping barrel is tightly sleeved on the periphery of the magnetic collector, and has the function of limiting the movement and insulation of the magnetic collector.
7. The apparatus of claim 1, wherein the apparatus further comprises:
pulse magnetic field generating device
The pulse magnetic field generating device forms a discharge loop, and the discharge current in the discharge loop is high-frequency and high-energy current, so that the induction current formed on the surface layer of the aero-engine blade is more concentrated, and the realization of the surface strengthening effect of the aero-engine blade is more facilitated.
8. A method of pulsed magnetic field strengthening an aircraft engine blade, the method comprising:
inserting the engine blade to be reinforced into the middle of Huang Lazhi and embedding the engine blade into the central concave part of the magnetic collector;
combining the first magnetic collector and the second magnetic collector, and sleeving a carbon fiber composite material fastening barrel on the outer layer to complete the assembly work of the parts;
connecting a conductive straight rod led out by a solenoid with a discharge binding post of a high-voltage pulse power supply unit, and fastening the binding post by using a bolt;
and charging the capacitor to the voltage of 10kV, then opening a high-voltage discharge switch, and discharging the loop to finish the primary impact process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311557953.3A CN117683997A (en) | 2023-11-21 | 2023-11-21 | Device and method for strengthening aeroengine blade by pulse magnetic field |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311557953.3A CN117683997A (en) | 2023-11-21 | 2023-11-21 | Device and method for strengthening aeroengine blade by pulse magnetic field |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117683997A true CN117683997A (en) | 2024-03-12 |
Family
ID=90129181
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311557953.3A Pending CN117683997A (en) | 2023-11-21 | 2023-11-21 | Device and method for strengthening aeroengine blade by pulse magnetic field |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117683997A (en) |
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2023
- 2023-11-21 CN CN202311557953.3A patent/CN117683997A/en active Pending
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