CN114776747B - Composite hyperbolic corrugated sandwich structure for inhibiting vibration of lubricating oil tank of aero-engine and application thereof - Google Patents
Composite hyperbolic corrugated sandwich structure for inhibiting vibration of lubricating oil tank of aero-engine and application thereof Download PDFInfo
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- CN114776747B CN114776747B CN202210250456.8A CN202210250456A CN114776747B CN 114776747 B CN114776747 B CN 114776747B CN 202210250456 A CN202210250456 A CN 202210250456A CN 114776747 B CN114776747 B CN 114776747B
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- corrugated
- magnetorheological
- composite
- lubricating oil
- plates
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- 239000002131 composite material Substances 0.000 title claims abstract description 42
- 239000010687 lubricating oil Substances 0.000 title claims abstract description 40
- 230000002401 inhibitory effect Effects 0.000 title claims description 11
- 230000017525 heat dissipation Effects 0.000 claims abstract description 21
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 16
- 229910052802 copper Inorganic materials 0.000 claims abstract description 16
- 239000010949 copper Substances 0.000 claims abstract description 16
- 239000002184 metal Substances 0.000 claims abstract description 12
- 229910052751 metal Inorganic materials 0.000 claims abstract description 12
- 239000006260 foam Substances 0.000 claims abstract description 9
- 239000012530 fluid Substances 0.000 claims abstract description 8
- 229920000728 polyester Polymers 0.000 claims abstract description 6
- 238000004804 winding Methods 0.000 claims abstract description 5
- 239000007788 liquid Substances 0.000 claims description 6
- 239000006249 magnetic particle Substances 0.000 claims description 6
- 239000010705 motor oil Substances 0.000 claims description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 3
- 238000000498 ball milling Methods 0.000 claims description 3
- 238000009775 high-speed stirring Methods 0.000 claims description 3
- 239000000314 lubricant Substances 0.000 claims description 3
- 239000002480 mineral oil Substances 0.000 claims description 3
- 235000010446 mineral oil Nutrition 0.000 claims description 3
- 229910021392 nanocarbon Inorganic materials 0.000 claims description 3
- 229920002545 silicone oil Polymers 0.000 claims description 3
- 239000004094 surface-active agent Substances 0.000 claims description 3
- 229910002804 graphite Inorganic materials 0.000 claims description 2
- 239000010439 graphite Substances 0.000 claims description 2
- 238000002360 preparation method Methods 0.000 claims description 2
- 238000013016 damping Methods 0.000 abstract description 23
- 239000010410 layer Substances 0.000 abstract description 9
- 239000011229 interlayer Substances 0.000 abstract description 5
- 230000001629 suppression Effects 0.000 abstract description 3
- 230000000694 effects Effects 0.000 description 8
- 239000000463 material Substances 0.000 description 8
- 239000012792 core layer Substances 0.000 description 4
- 238000013461 design Methods 0.000 description 4
- 239000003921 oil Substances 0.000 description 4
- 230000003139 buffering effect Effects 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 239000003733 fiber-reinforced composite Substances 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 230000001050 lubricating effect Effects 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000003607 modifier Substances 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 230000008719 thickening Effects 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 230000003044 adaptive effect Effects 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
- 230000005672 electromagnetic field Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 230000005764 inhibitory process Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002120 nanofilm Substances 0.000 description 1
- 230000001376 precipitating effect Effects 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F1/00—Springs
- F16F1/36—Springs made of rubber or other material having high internal friction, e.g. thermoplastic elastomers
- F16F1/3605—Springs made of rubber or other material having high internal friction, e.g. thermoplastic elastomers characterised by their material
- F16F1/361—Springs made of rubber or other material having high internal friction, e.g. thermoplastic elastomers characterised by their material comprising magneto-rheological elastomers [MR]
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F9/00—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium
- F16F9/32—Details
- F16F9/53—Means for adjusting damping characteristics by varying fluid viscosity, e.g. electromagnetically
- F16F9/535—Magnetorheological [MR] fluid dampers
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention belongs to the technical field of vibration suppression, and particularly relates to a composite hyperbolic corrugated sandwich structure for suppressing vibration of an aircraft engine lubricating oil tank and application thereof. The technical proposal is as follows: the magnetorheological damper comprises two panels, two corrugated plates and a plurality of magnetorheological cores, wherein the panels and the corrugated plates are made of composite materials; the two corrugated plates are bonded together in a buckling way, a plurality of mounting holes are formed between the two corrugated plates, and the magnetorheological core is placed in the mounting holes; the two panels are respectively arranged at the outer sides of the two corrugated plates, and the panels are bonded with the corrugated plates through filled polyester foam; the magnetorheological core comprises a core rod, a metal cap, copper coils and a heat dissipation film, wherein magnetorheological fluid is filled in the core rod, the metal caps are respectively arranged at two ends of the core rod, and a plurality of groups of copper coils are arranged outside the core rod in a mode of winding a group of copper coils and then covering a layer of heat dissipation film. The invention realizes the vibration suppression effect on the lubricating oil tank mounting structure by actively controlling the damping performance of the magnetorheological interlayer.
Description
Technical Field
The invention belongs to the technical field of vibration suppression, and particularly relates to a composite hyperbolic corrugated sandwich structure for suppressing vibration of an aircraft engine lubricating oil tank and application thereof.
Background
In recent years, as high performance aircraft engines continue to pursue high thrust to weight ratios and low fuel consumption rates, thin-wall structures have been largely adopted, thereby causing problems of vibration overscaling and fatigue failure of many components. The lubricating oil system is used as the most important part in an aeroengine and mainly plays roles of lubricating a bearing, reducing friction and cooling accessories. The lubricating tanks often produce severe vibrations and even structural failure due to casing vibration and pressure pulsations of the internal oil. The lubricating oil tank is an important part of an aircraft engine lubricating oil system, and is mainly used for storing lubricating oil and playing roles of radiating heat, separating air in a lubricating oil medium and precipitating impurities in the lubricating oil medium.
In order to effectively restrain vibration of an aircraft engine lubricating oil tank system, a great deal of research and study with great success is carried out by many scientific researchers. Some researchers have designed new types of lubricant tank structures, such as: wang et al (university of capital (natural science edition), 2019,38 (1): 91-93, 97.) propose an integral air inlet-lubricating oil tank structure analysis, design the lubricating oil tank system, the air inlet system and the cooling system into an integral structure, take away the lubricating oil temperature by utilizing the high-speed air flow of the air inlet, and solve the problems of oil supply, heat dissipation and lubrication of a certain engine model; jing Guoqing et al (gas turbine test and research 2014 (1): 39-44, 56.) propose a numerical simulation for the structural integration and optimization of a circular oil tank, and analyze the structural integration design of the circular oil tank by adopting a method combining theoretical calculation and numerical simulation, and propose an optimization scheme. The patent CN202110404817.5 discloses an integrated aeroengine lubricating oil tank which can be integrally cast with a casting casing of an aeroengine.
In addition, some research and development personnel develop innovative design or vibration reduction methods for auxiliary supporting structures (hereinafter referred to as aeroengine mounting structures) on the basis of not changing the structure of the lubricating oil tank and the manufacturing method thereof in order to reduce the cost, but still have some problems. For example, patent CN102179978A discloses a sandwich damping composite structure, in which the outer layer is made of a fiber-reinforced resin matrix, the inner layer is made of a closed-cell rigid foam, and the foam has a certain damping effect, but the damping effect is poor, and particularly, the damping performance of the foam is difficult to maintain in a thermal environment without considering the temperature influence. The patent CN106313761.A adopts a nano modified vibration damping material, the upper and lower panels are composed of a composite material matrix, a composite reinforcing layer and a nano modifier, and the middle layer adopts a honeycomb structure. Although the vibration response level is reduced, the use requirement of the aviation structure with the characteristic of low vibration level can be met, and meanwhile, the high-damping nano modifier converts the mechanical vibration energy of the solid structural material into heat energy, so that the heat energy of the system is increased, the damping is reduced, and the vibration reduction effect is weakened. Patent CN 110406178A proposes a metal/composite multilayer dual-gradient energy-absorbing and vibration-damping sandwich structure comprising a panel and a core layer, wherein the core layer consists of a thin-walled hollow tubular unit cell structure, although the propagation of vibration can be damped through impedance, excessive elastic deformation can cause a lower structural fatigue life and poorer rigidity. Patent CN209196034U provides an adaptive vibration-damping sandwich panel composite material, in which vibration is damped by filling a shear thickening fluid in the sandwich wall, but the obvious disadvantage of this structure is that it needs to be tightly sealed, the sealing device will increase the weight of the whole system, and once leakage of the shear thickening fluid occurs, it is difficult to ensure the vibration damping effect. The patent CN 110065273A discloses a sandwich corrugated cylindrical shell structure filled with a magnetorheological damping composite material, which is provided with an outer cylindrical shell and an inner cylindrical shell, wherein a composite corrugated sandwich is arranged between the outer cylindrical shell and the inner cylindrical shell, the sandwich is annular formed by a plurality of trapezoid folding lines, the upper bottom or the lower bottom of each trapezoid folding line is provided with a magnetorheological damping material unit along the axial direction of the inner cylindrical shell, and the magnetorheological damping material unit plays a role in buffering, so that the stepless active control of damping performance can be realized. But the structure can not well radiate heat generated by the magneto-rheological, thereby affecting the damping performance and the overall rigidity of the structure of the magneto-rheological material. Patent CN 110077046A discloses a self-powered and vibration-perceived magnetorheological interlayer corrugated cylindrical shell structure, a composite material corrugated interlayer is arranged between an outer cylindrical shell and an inner cylindrical shell, magnetorheological damping material units are arranged in the interlayer, and a plurality of self-powered units are embedded in the circumference of the inner cylindrical shell; a MEMS vibration sensor and integrated logic circuitry are embedded in the outer cylindrical shell. The structure supplies energy to the magneto-rheological core layer through the electric energy collected by the inner shell so as to play a damping buffering role, but the structure cannot wind a plurality of coils due to the small size of the magneto-rheological core, so that the damping effect of the structure can be exerted like that of the magneto-rheological core wound by the plurality of coils, and the structure also does not solve the heat dissipation problem of the magneto-rheological copper coil and influences the damping performance.
Disclosure of Invention
The invention provides a composite hyperbolic corrugated sandwich structure for inhibiting vibration of an aircraft engine lubricating oil tank and application thereof, and the vibration inhibition effect of the lubricating oil tank mounting structure is realized by actively controlling the damping performance of a magnetorheological interlayer.
The technical scheme of the invention is as follows:
the composite hyperbolic corrugated sandwich structure for inhibiting vibration of an aircraft engine lubricating oil tank comprises two panels, two corrugated plates and a plurality of magnetorheological cores, wherein the panels and the corrugated plates are made of composite materials; the two corrugated plates are bonded together in a buckling way, a plurality of mounting holes are formed between the two corrugated plates, and the magnetorheological core is placed in the mounting holes; the two panels are respectively arranged at the outer sides of the two corrugated plates, and the panels are bonded with the corrugated plates through filled polyester foam; the magnetorheological core comprises a core rod, a metal cap, copper coils and a heat dissipation film, wherein magnetorheological fluid is filled in the core rod, the metal caps are respectively arranged at two ends of the core rod, and a plurality of groups of copper coils are arranged outside the core rod in a mode of winding a group of copper coils and then covering a layer of heat dissipation film.
Further, the composite hyperbolic corrugated sandwich structure for inhibiting vibration of an aircraft engine lubricating oil tank, the corrugated plate is a trapezoid corrugated plate, semicircular opening clamping plates are arranged at trapezoid corrugated positions of the mounting holes, and two semicircular opening clamping plates which are oppositely arranged form a clamp for clamping the magnetorheological core.
Further, the composite hyperbolic corrugated sandwich structure for inhibiting vibration of the lubricating oil tank of the aeroengine is characterized in that the heat dissipation film is a nano carbon heat dissipation film or a graphite heat dissipation film.
Further, the composite hyperbolic corrugated sandwich structure for inhibiting vibration of an aircraft engine lubricating oil tank is prepared by the following steps: and adding the magnetic particles into a non-magnetic carrier liquid, adding a surfactant, and performing ball milling or high-speed stirring.
Further, the composite hyperbolic corrugated sandwich structure for inhibiting vibration of an aircraft engine lubricating oil tank is characterized in that the magnetic particles are carbonyl iron powder, and the non-magnetic carrier liquid is mineral oil and silicone oil.
The composite hyperbolic corrugated sandwich structure for inhibiting vibration of the aeroengine lubricating oil tank is applied, the composite hyperbolic corrugated sandwich structure is arranged on a bracket to form a lubricating oil tank supporting part, the lubricating oil tank supporting part is fixedly connected with a base and a lubricating oil tank body through bolts respectively, and the base is fixedly connected with an aeroengine casing.
Further, the composite hyperbolic corrugated sandwich structure for inhibiting vibration of the lubricating oil tank of the aeroengine is applied, two support plates are arranged at the lower part of the support, and three composite hyperbolic corrugated sandwich structures are respectively arranged between the two support plates and outside each support plate.
Further, the composite hyperbolic corrugated sandwich structure for suppressing vibration of an aircraft engine lubricating oil tank is applied, and the bracket is made of a composite material.
The beneficial effects of the invention are as follows:
1. the invention adopts a sandwich structure design idea, the panel adopts a fiber reinforced composite material, the core layer adopts a magneto-rheological core wound by a plurality of layers of copper coils with a heat dissipation function, and the heat insulation film and the heat dissipation structure are designed in the core, so that the phenomenon that the copper coils are too hot and even fuse due to the magneto-rheological effect is prevented. The fiber reinforced composite material and the sandwich structure are adopted to play a passive vibration reduction role, and the damping performance of the installation structure is actively controlled by utilizing the multi-coil magnetorheological core.
2. Tightly winding the copper coil on the core rod through interference fit between the core rod and the metal cap; and each coil is isolated by using the heat dissipation film, so that the coil is prevented from fusing due to heat accumulation.
3. The corrugated plate and the panel are bonded together by filling the polyester foam, and the polyester foam also plays a certain role in vibration reduction.
Drawings
FIG. 1 is a schematic illustration of a composite hyperbolic corrugated sandwich structure for suppressing vibration of an aircraft engine lubricant tank;
FIG. 2 is a top view of a composite hyperbolic corrugated sandwich structure for suppressing vibration of an aircraft engine lubricant tank;
FIG. 3 is a schematic view of a corrugated plate;
FIG. 4 is a schematic view of a magnetorheological core;
FIG. 5 is a schematic view of a stent;
fig. 6 is a schematic view of a supporting member of the lubricating oil tank.
Detailed Description
Example 1
As shown in fig. 1 to 4, the composite hyperbolic corrugated sandwich structure for suppressing vibration of an aircraft engine lubricating oil tank comprises two panels 1, two corrugated plates 4 and a plurality of magnetorheological cores 2, wherein the panels 1 and the corrugated plates 4 are made of composite materials; the two corrugated plates 4 are bonded together in a buckling way, a plurality of mounting holes are formed between the two corrugated plates 4, and the magnetorheological core 2 is placed in the mounting holes; the corrugated plate 4 is a trapezoid corrugated plate, semicircular opening clamping plates 5 are arranged at trapezoid corrugated positions forming the mounting holes, and two semicircular opening clamping plates 5 which are oppositely arranged form a clamp for clamping the magnetorheological core 2; the two panels 1 are respectively arranged on the outer sides of the two corrugated plates 4, and the panels 1 are bonded with the corrugated plates 4 through filling polyester foam 3; the magneto-rheological core 2 comprises a core rod 6, a metal cap 7, copper coils 8 and a heat dissipation film 9, magneto-rheological fluid is filled in the core rod 6, the metal caps 7 are respectively arranged at two ends of the core rod 6, and a plurality of groups of copper coils 8 are arranged outside the core rod 6 in a mode of winding a group of copper coils 8 and then covering a layer of heat dissipation film 9; the heat dissipation film 9 is a nano carbon heat dissipation film; the preparation method of the magnetorheological fluid comprises the following steps: adding magnetic particles into a non-magnetic carrier liquid, adding a surfactant, and performing ball milling or high-speed stirring; the magnetic particles are carbonyl iron powder, and the non-magnetic carrier liquid is mineral oil and silicone oil.
Example 2
As shown in fig. 5 and 6, in the application of the composite hyperbolic corrugated sandwich structure for suppressing vibration of an aircraft engine lubricating oil tank in embodiment 1, the composite hyperbolic corrugated sandwich structure 10 is arranged on a metal bracket 11 to form a lubricating oil tank supporting part, and the lubricating oil tank supporting part is fixedly connected with a base and a lubricating oil tank body through bolts respectively, and the base is fixedly connected with an aircraft engine case. Two support plates 12 are arranged at the lower part of the metal support 11, and three composite material hyperbolic corrugated sandwich structures 10 are respectively arranged between the two support plates 12 and outside each support plate 12.
The working principle is as follows: when the lubricating oil tank supporting component is vibrated, the piezoelectric ceramic film in the composite material converts kinetic energy of mechanical vibration into electric energy; firstly, storing most electric energy in a carbon nano film tube film layer, when the stored electric energy is enough, firstly, enabling the electric energy to enter from an input port of an integrated logic circuit, and if the average peak-peak value Save= (S1+S … +S12)/12 of time domain signals detected by 12 MEMS sensors is higher than a certain set value S0, namely Save > S0, connecting an output port of the integrated logic circuit to a filling damping-variable unit in a corrugated sandwich structure for supplying power to form an electromagnetic field, thereby achieving the effects of actively controlling and increasing damping of the magneto-rheological sandwich, and stopping supplying power until Save is less than or equal to S0. The steps are repeated, and the purpose of actively controlling vibration of the lubricating oil tank supporting component is achieved.
Claims (4)
1. The composite hyperbolic corrugated sandwich structure for inhibiting vibration of an aircraft engine lubricating oil tank is characterized by comprising two panels, two corrugated plates and a plurality of magnetorheological cores, wherein the panels and the corrugated plates are made of composite materials; the two corrugated plates are bonded together in a buckling way, a plurality of mounting holes are formed between the two corrugated plates, and the magnetorheological core is placed in the mounting holes; the two panels are respectively arranged at the outer sides of the two corrugated plates, and the panels are bonded with the corrugated plates through filled polyester foam; the magnetorheological core comprises a core rod, a metal cap, copper coils and a heat dissipation film, wherein magnetorheological fluid is filled in the core rod, the metal caps are respectively arranged at two ends of the core rod, and a plurality of groups of copper coils are arranged outside the core rod in a mode of winding a group of copper coils and then covering a layer of heat dissipation film; the corrugated plate is a trapezoid corrugated plate, semicircular opening clamping plates are arranged at trapezoid corrugated positions forming the mounting holes, and two semicircular opening clamping plates which are oppositely arranged form a clamp for clamping the magnetorheological core; the heat dissipation film is a nano carbon heat dissipation film or a graphite heat dissipation film; the preparation method of the magnetorheological fluid comprises the following steps: adding magnetic particles into a non-magnetic carrier liquid, adding a surfactant, and performing ball milling or high-speed stirring; the magnetic particles are carbonyl iron powder, and the non-magnetic carrier liquid is mineral oil and silicone oil.
2. The use of a composite doubly curved corrugated sandwich structure for suppressing vibrations of an aircraft engine lubricant tank as defined in claim 1, wherein said composite doubly curved corrugated sandwich structure is arranged on a support frame to form a lubricant tank support member fixedly connected to a base and a lubricant tank body, respectively, by bolts, said base being fixedly connected to an aircraft engine case.
3. The use of a composite double-curved corrugated sandwich structure for suppressing vibration of an aircraft engine lubricating oil tank according to claim 2, wherein the lower part of the bracket is provided with two support plates, and three composite double-curved corrugated sandwich structures are respectively arranged between the two support plates and outside each support plate.
4. Use of a composite doubly curved corrugated sandwich structure for suppressing vibrations of an aircraft engine lubricant tank as claimed in claim 2 wherein said brackets are made of composite material.
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|---|---|---|---|
| CN202210250456.8A CN114776747B (en) | 2022-03-15 | 2022-03-15 | Composite hyperbolic corrugated sandwich structure for inhibiting vibration of lubricating oil tank of aero-engine and application thereof |
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| CN202210250456.8A CN114776747B (en) | 2022-03-15 | 2022-03-15 | Composite hyperbolic corrugated sandwich structure for inhibiting vibration of lubricating oil tank of aero-engine and application thereof |
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| CN114776747B true CN114776747B (en) | 2023-09-22 |
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