CN105197246A - Engine sector-shaped noise-reduction nozzle driven by piezoelectric fiber composite materials - Google Patents
Engine sector-shaped noise-reduction nozzle driven by piezoelectric fiber composite materials Download PDFInfo
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- CN105197246A CN105197246A CN201510583146.8A CN201510583146A CN105197246A CN 105197246 A CN105197246 A CN 105197246A CN 201510583146 A CN201510583146 A CN 201510583146A CN 105197246 A CN105197246 A CN 105197246A
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Abstract
The invention provides an engine sector-shaped noise-reduction nozzle driven by piezoelectric fiber composite materials. The engine sector-shaped noise-reduction nozzle comprises a sector-shaped nozzle, double layers of the piezoelectric fiber composite materials which are fixedly arranged on upper and lower surfaces of a sector section of the nozzle, interdigital electrodes which are arrayed on the upper and lower surfaces of each layer of the piezoelectric fiber composite material, and a control module for controlling a power supply system; an airplane applies opposite voltage to the piezoelectric fiber composite materials through the control module and the interdigital electrodes, and the deformed piezoelectric fiber composite materials accelerate the deformation of the sector section of the nozzle. With the adoption of the engine sector-shaped noise-reduction nozzle, the permeability degree of the sector section of the nozzle can be initiatively and rapidly changed, flow spraying noises are reduced and the smaller thrust loss is guaranteed; the piezoelectric fiber composite materials is rapid in responding speed, small in weight and is abrasion resistant, and can be initiatively adjusted according to a flight state, so that the unification of effective noise reduction and reduction of the thrust loss is realized.
Description
Technical field
What the present invention relates to is a kind of technology of aerospace field, specifically the fan-shaped noise reduction nozzle of driving engine that drives of a kind of piezoelectric fibre composite material.
Background technology
The noise source of aircraft can be divided into power system noise, as the noise that engine blower, air compressor, jet flow etc. produce, and unpowered noise, as high lift device noise, Landing gear noise and ancillary system noise.
Wherein, for driving engine, the high velocity air of engine export mixes with air free stream, forms high velocity turbulent flow shear layer, produces the turbulence noise of high strength.Taking off and landing phases, jet cutting car flow noise can cause serious noise emission to airport and surrounding resident.Based on this, International Civil Aviation Organization has formulated strict noise airworthiness standard; And in aircraft cruising phase, need driving engine to provide high thrust, avoid thrust loss as far as possible thus obtain higher fuel utilization.The design of advanced aero engine, being desirably in the takeoff and landing stage has less noise objective, can reduce engine thrust loss under cruising condition as much as possible simultaneously.
Utilize fan nozzle to substitute traditional round nozzle, be a kind of passive motor noise control technology, the turbulent closure scheme of engine core air-flow and air free stream can be increased, reach the object reducing noise, but extra thrust loss can be produced.Further, conventional fan nozzle is the tradeoff design of noise reduction and thrust loss mostly, is difficult to realize optimum Noise measarement effect.
The penetration degree (fan place, lobe tip tangent plane circle and the difference of fanning place tangent plane radius of a circle bottom lobe) of fan nozzle is the key parameter that motor noise controls, and directly affects Noise measarement effect.Because the fan nozzle structure of routine is fixed, can not active adjustment penetration degree, the optimum limiting noise reduction realizes; And the fan nozzle design of large penetration degree can increase the thrust loss under aircraft cruising condition, be difficult to obtain good cruise performance.
Through finding the retrieval of prior art, Chinese patent literature CN103171757A, date of publication 2013.6.26, disclose a kind of self adaptation trailing edge actuating device using piezoelectric fibre composite material, piezoelectric fibre composite material is that array is pasted onto on the surface of the upper and lower both sides of substrate by epoxy resin, piezoelectric fibre composite material connects an independently high tension supply separately, power supply output area Wei ?500V ~+1500V.But this technology directly applies voltage by additional power supply to piezoelectric fibre composite material, internal electric field skewness when scantling is larger, cannot realize concurrent deformation.
Summary of the invention
The present invention is directed to prior art above shortcomings, the fan-shaped noise reduction nozzle of driving engine that a kind of piezoelectric fibre composite material drives is proposed, piezoelectric fibre composite material is applied to driving engine fan nozzle, realize nozzle fan lobe homogeneous deformation, the penetration degree of nozzle fan lobe can be changed initiatively, rapidly, while reducing jet noise, ensure less thrust loss.
The present invention is achieved by the following technical solutions:
The present invention includes: fan nozzle and the some actuating devices being fixedly installed on nozzle fan lobe upper and lower surface.
Described actuating device comprises: double-deck piezoelectric fibre composite material, be arranged in every layer of piezoelectric fibre composite material upper and lower surface interdigital electrode and be connected with interdigital electrode and be positioned at the control module that nozzle fans lobe root.
Described double-deck piezoelectric fibre composite material comprises piezoceramic and high-molecular organic material, and wherein the thickness of one deck piezoelectric fibre composite material equals 1/4 ~ 1/3 of the overall maximum ga(u)ge of nozzle fan lobe arbitrarily.
The width of described double-deck piezoelectric fibre composite material equals the tip of nozzle fan lobe to 1/5 ~ 1/4 of root depth.
The entire area of described double-deck piezoelectric fibre composite material is more than or equal to 1/3 of nozzle fan lobe area.
Described double-deck piezoelectric fibre composite material by rivet, fasteningly fan lobe with modes such as bondings with nozzle and be fixedly connected with.
Described piezoceramic and high-molecular organic material meet following combination in any:
1) 1 ?3 structures, namely piezoceramic is one dimension UNICOM, and high-molecular organic material is three-dimensional UNICOM;
2) 2 ?2 structures, namely piezoceramic and high-molecular organic material are two-dimentional UNICOM.
The optional circle in fibre section of described piezoceramic, ellipse, square or irregular shape.
The fibers parallel of described piezoceramic is fanned lobe in nozzle and points to tip from nozzle fan lobe root, fans the lobe deformation result that lower generation is desirable in working order drive the deflection of nozzle fan lobe to make nozzle.
The fibre length of described piezoceramic is consistent with the entire length of double-deck piezoelectric fibre composite material, and fiber spacing is 1/6 ~ 1/5 of fibre length.
Described high-molecular organic material can select high temperature resistant type epoxy resin and relevant suitable poly-mer, and length, the thickness of material are identical with the entirety of piezoelectric fibre composite material with width.
Described interdigital electrode in the upper and lower surface of piezoelectric fibre composite material along both direction symmetry arrangement, comprise a pair different in nature beam electrode and some different in nature branch electrodes, wherein: a pair beam electrode is arranged along the length direction of double-deck piezoelectric fibre composite material, branch electrodes is arranged along the Width of double-deck piezoelectric fibre composite material, and every layer of piezoelectric fibre composite material upper and lower surface correspondence position electrode is homopolarity.
Described control module applies rightabout driving voltage to the double-deck piezoelectric fibre composite material laying respectively at nozzle fan lobe upper and lower surface, forms opposite electric field.
Described drive voltage range Wei ?500V ~+500V.
Described actuating device produces the flexural deformation in the fibre length direction along piezoceramic under voltage control, drive nozzle fan lobe outwards (inwardly) curved deflector, produce the displacement along nozzle cross-section radially outward (inwardly), ACTIVE CONTROL changes the penetration degree of nozzle fan lobe, aggravation fan stream, core flow and the strong blending of freely flowing, reduce air-flow at a high speed ejection time the low-frequency noise that produces, to reduce cruising phase thrust loss at landing stage noise reduction.
Technique effect
Compared with prior art, piezoelectric fibre composite material is applied to the fan nozzle of driving engine by the present invention, can change the penetration degree of nozzle fan lobe initiatively, rapidly, ensure less thrust loss while reducing jet noise; And the piezoelectric fibre composite material speed of response is fast, weight is little, resistance to wear, according to state of flight active adjustment, effective noise reduction and the unification reducing thrust loss can be reached.
Accompanying drawing explanation
Fig. 1 is nozzle fan lobe scheme of installation on the engine;
Fig. 2 is the scheme of installation of actuating device on nozzle fan lobe;
Fig. 3 be piezoelectric fibre composite material fibre length towards schematic diagram;
Fig. 4 is a unit piezoelectric fibre composite material section-drawing;
Fig. 5 is that interdigital electrode installs section-drawing;
Fig. 6 is actuating device at fan lobe to operating diagram during intrinsic deflection;
Fig. 7 be actuating device fan lobe interval inwardly extrinsic deflection time operating diagram;
In figure: 1 is fan lobe, and 2 is actuating device, and 3 is piezoelectric ceramic fibers, and 4 is high-molecular organic material, and 5 is interdigital electrode, and 6 ~ 9 are electrode.
Detailed description of the invention
Elaborate to embodiments of the invention below, the present embodiment is implemented under premised on technical solution of the present invention, give detailed embodiment and concrete operating process, but protection scope of the present invention is not limited to following embodiment.
Embodiment 1
As depicted in figs. 1 and 2, the present invention includes fan nozzle and be fixedly installed on several actuating devices 2 that nozzle fans lobe 1 upper and lower surface.
As shown in Figure 3, described actuating device 2 comprises: double-deck piezoelectric fibre composite material, be arranged in every layer of piezoelectric fibre composite material upper and lower surface interdigital electrode 5 and be connected with interdigital electrode 5 and be positioned at the control module that nozzle fans lobe 1 root.
Described double-deck piezoelectric fibre composite material comprises piezoceramic 3 and high-molecular organic material 4.
Described piezoceramic 3 and high-molecular organic material 4 adopt 1-3 structure, and namely piezoceramic 3 is one dimension UNICOMs, and high-molecular organic material 4 is three-dimensional UNICOMs.
The fibre section of described piezoceramic 3 is square.
The fibers parallel of described piezoceramic 3 is in nozzle fan lobe 1 and from nozzle fan lobe 1 root sensing tip, the fibre length of piezoceramic 3 is consistent with the entire length of double-deck piezoelectric fibre composite material.
Length, the thickness of described high-molecular organic material 4 are identical with the entirety of piezoelectric fibre composite material with width.
As shown in Figure 4 and Figure 5, described interdigital electrode 5 in the upper and lower surface of piezoelectric fibre composite material along both direction symmetry arrangement, comprise a pair different in nature beam electrode 6 and 7 and two different in nature branch electrodes 8 and 9, wherein: beam electrode 6 and 7 is arranged along the length direction of double-deck piezoelectric fibre composite material, branch electrodes 8 and 9 is arranged along the Width of double-deck piezoelectric fibre composite material, and every layer of piezoelectric fibre composite material upper and lower surface correspondence position electrode is homopolarity.
Described control module applies rightabout driving voltage to the double-deck piezoelectric fibre composite material laying respectively at nozzle fan lobe 1 upper and lower surface, forms opposite electric field.
As shown in Figure 6, in the present embodiment, engine nozzle fan lobe penetration degree initial condition is 0.When takeoff and landing, control module controls power-supply system, by the interdigital electrode on each fan lobe, voltage is applied to piezoelectric fibre composite material, form electric field, make piezoelectric fibre composite material flexural deformation, drive driving engine fan lobe to curve inwardly, make fan lobe produce the penetration degree being greater than 0, increase core flow and the blending speed freely flowed, reduce the low-frequency noise that jet flow produces.
When aircraft is in cruising condition, control module controls power-supply system, removes the electric field that interdigital electrode produces, makes piezoelectric fibre composite material not produce adaptability to changes, and nozzle fan lobe restPoses, and ensures the thrust requirements under cruising condition.
Embodiment 2
As depicted in figs. 1 and 2, the present invention includes: fan nozzle and several actuating devices 2 being fixedly installed on nozzle fan lobe 1 upper and lower surface.
As shown in Figure 3, described actuating device 2 comprises: double-deck piezoelectric fibre composite material, be arranged in every layer of piezoelectric fibre composite material upper and lower surface interdigital electrode 5 and be connected with interdigital electrode 5 and be positioned at the control module that nozzle fans lobe 1 root.
Described double-deck piezoelectric fibre composite material comprises piezoceramic 3 and high-molecular organic material 4.
Described piezoceramic 3 and high-molecular organic material 4 adopt 1-3 structure, and namely piezoceramic 3 is one dimension UNICOMs, and high-molecular organic material 4 is three-dimensional UNICOMs.
The fibre section of described piezoceramic 3 is square.
The fibers parallel of described piezoceramic 3 is in nozzle fan lobe 1 and from nozzle fan lobe 1 root sensing tip, the fibre length of piezoceramic 3 is consistent with the entire length of double-deck piezoelectric fibre composite material.
Length, the thickness of described high-molecular organic material 4 are identical with the entirety of piezoelectric fibre composite material with width.
As shown in Figure 4 and Figure 5, described interdigital electrode 5 in the upper and lower surface of piezoelectric fibre composite material along both direction symmetry arrangement, comprise a pair different in nature beam electrode 6 and 7 and two different in nature branch electrodes 8 and 9, wherein: beam electrode 6 and 7 is arranged along the length direction of double-deck piezoelectric fibre composite material, branch electrodes 8 and 9 is arranged along the Width of double-deck piezoelectric fibre composite material, and every layer of piezoelectric fibre composite material upper and lower surface correspondence position electrode is homopolarity.
Described control module applies rightabout driving voltage to the double-deck piezoelectric fibre composite material laying respectively at nozzle fan lobe 1 upper and lower surface, forms opposite electric field.
As shown in Figure 7, in the present embodiment, engine nozzle fan lobe penetration degree initial condition is 0.When takeoff and landing, control module controls power-supply system, by the interdigital electrode on adjacent two fan lobes, opposite voltage is applied to piezoelectric fibre composite material, form opposite electric field, make piezoelectric fibre composite material flexural deformation, drive adjacent driving engine to fan lobe respectively to deflecting outside to inside, thus increase core flow and the blending speed freely flowed, reduce the low-frequency noise that jet flow produces.
When aircraft is in cruising condition, control module controls power-supply system, removes the electric field that interdigital electrode produces, makes piezoelectric fibre composite material not produce adaptability to changes, and nozzle fan lobe restPoses.
Claims (10)
1. the fan-shaped noise reduction nozzle of driving engine of a piezoelectric fibre composite material driving, it is characterized in that, comprise: fan nozzle and be fixedly installed on some actuating devices of nozzle fan lobe upper and lower surface, this actuating device comprises: the double-deck piezoelectric fibre composite material comprising piezoceramic and high-molecular organic material, the interdigital electrode being arranged in every layer of piezoelectric fibre composite material upper and lower surface and be connected with interdigital electrode and be positioned at the control module that described nozzle fans lobe root.
2. the fan-shaped noise reduction nozzle of driving engine of piezoelectric fibre composite material driving according to claim 1, is characterized in that, the thickness in monolayer of described piezoelectric fibre composite material equals 1/4 ~ 1/3 of the overall maximum ga(u)ge of described nozzle fan lobe.
3. the fan-shaped noise reduction nozzle of driving engine of piezoelectric fibre composite material driving according to claim 1, is characterized in that, the width of described piezoelectric fibre composite material equals described nozzle and fans the tip of lobe to 1/5 ~ 1/4 of root depth.
4. the fan-shaped noise reduction nozzle of driving engine of piezoelectric fibre composite material driving according to claim 1, is characterized in that, the entire area of described piezoelectric fibre composite material is more than or equal to 1/3 of described nozzle fan lobe area.
5. the fan-shaped noise reduction nozzle of driving engine of piezoelectric fibre composite material driving according to claim 1, is characterized in that, the fibers parallel of described piezoceramic points in described fan lobe and from fan lobe root and fans lobe tip.
6. the fan-shaped noise reduction nozzle of driving engine of piezoelectric fibre composite material driving according to claim 1, it is characterized in that, the fibre length of described piezoceramic is consistent with the entire length of double-deck piezoelectric fibre composite material, and fiber spacing is 1/6 ~ 1/5 of fibre length.
7. the fan-shaped noise reduction nozzle of driving engine that drives of piezoelectric fibre composite material according to claim 1, is characterized in that, described interdigital electrode in the upper and lower surface of described piezoelectric fibre composite material along both direction symmetry arrangement.
8. the fan-shaped noise reduction nozzle of driving engine of piezoelectric fibre composite material driving according to claim 1, it is characterized in that, described interdigital electrode comprises a pair different in nature beam electrode and some different in nature branch electrodes, wherein: a pair beam electrode is arranged along described piezoelectric fibre composite material length direction, some branch electrodes are along the arrangement of described piezoelectric fibre composite material Width, and every layer of piezoelectric fibre composite material upper and lower surface correspondence position electrode is homopolarity.
9. the fan-shaped noise reduction nozzle of driving engine of piezoelectric fibre composite material driving according to claim 1, it is characterized in that, described control module applies rightabout driving voltage to the two-layer piezoelectric fibre composite material laying respectively at described nozzle fan lobe upper and lower surface.
10. the fan-shaped noise reduction nozzle of driving engine that drives of piezoelectric fibre composite material according to claim 9, is characterized in that, described drive voltage range Wei ?500V ~+500V.
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| CN201510583146.8A CN105197246A (en) | 2015-09-15 | 2015-09-15 | Engine sector-shaped noise-reduction nozzle driven by piezoelectric fiber composite materials |
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| CN201510583146.8A CN105197246A (en) | 2015-09-15 | 2015-09-15 | Engine sector-shaped noise-reduction nozzle driven by piezoelectric fiber composite materials |
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Citations (6)
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| US5515444A (en) * | 1992-10-21 | 1996-05-07 | Virginia Polytechnic Institute And State University | Active control of aircraft engine inlet noise using compact sound sources and distributed error sensors |
| US20030231777A1 (en) * | 2002-06-14 | 2003-12-18 | Butler George W. | High frequency jet nozzle actuators for jet noise reduction |
| CN102859582A (en) * | 2010-04-27 | 2013-01-02 | 斯奈克玛 | Method of processing acoustic waves emitted at the outlet of a turbo engine of an aircraft with a dielectric-barrier discharge device and aircraft comprising such a device |
| FR3001324A1 (en) * | 2013-01-24 | 2014-07-25 | Aircelle Sa | ACOUSTICAL ATTENUATION PANEL WITH ALVEOLAR SOUL |
| FR2972710B1 (en) * | 2011-03-15 | 2014-09-26 | Snecma | DEVICE FOR THE ACOUSTICAL ATTENUATION OF THE PROPELLANT NOISE OF A CONTRAROTATIVE DOUBLE PROPELLER AIRCRAFT TURBOPROPULSOR |
| CN104204421A (en) * | 2012-03-20 | 2014-12-10 | 埃尔塞乐公司 | Variable-section jet pipe and aircraft turbojet engine nacelle equipped with such a jet pipe |
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2015
- 2015-09-15 CN CN201510583146.8A patent/CN105197246A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5515444A (en) * | 1992-10-21 | 1996-05-07 | Virginia Polytechnic Institute And State University | Active control of aircraft engine inlet noise using compact sound sources and distributed error sensors |
| US20030231777A1 (en) * | 2002-06-14 | 2003-12-18 | Butler George W. | High frequency jet nozzle actuators for jet noise reduction |
| CN102859582A (en) * | 2010-04-27 | 2013-01-02 | 斯奈克玛 | Method of processing acoustic waves emitted at the outlet of a turbo engine of an aircraft with a dielectric-barrier discharge device and aircraft comprising such a device |
| FR2972710B1 (en) * | 2011-03-15 | 2014-09-26 | Snecma | DEVICE FOR THE ACOUSTICAL ATTENUATION OF THE PROPELLANT NOISE OF A CONTRAROTATIVE DOUBLE PROPELLER AIRCRAFT TURBOPROPULSOR |
| CN104204421A (en) * | 2012-03-20 | 2014-12-10 | 埃尔塞乐公司 | Variable-section jet pipe and aircraft turbojet engine nacelle equipped with such a jet pipe |
| FR3001324A1 (en) * | 2013-01-24 | 2014-07-25 | Aircelle Sa | ACOUSTICAL ATTENUATION PANEL WITH ALVEOLAR SOUL |
Non-Patent Citations (1)
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| 刘为民等: "交叉指形电极压电纤维复合材料的优化设计", 《机械工程材料》 * |
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