CN105092204A - Apparatus used for helicopter rotor blade-vortex interference noise experiment - Google Patents
Apparatus used for helicopter rotor blade-vortex interference noise experiment Download PDFInfo
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Abstract
The invention discloses an apparatus used for a helicopter rotor blade-vortex interference noise experiment. The apparatus comprises a blade wallboard, an ear sheet, a bolt group, sleeves, an angle fixing bolt, a supporting seat, a driving device, a second rotor wing, a first rotor wing and a propeller hub. The first rotor wing and the second rotor wing sleeve a rotating shaft through the sleeves. Through installing the sleeves with different length, a distance between the two rotor wings can be adjusted. Through rotating the sleeve, an included angle of the first rotor wing and the second rotor wing can be adjusted. And the angle fixing bolt is used to screw and fix the three so that the included angle of the first rotor wing and the second rotor wing is fixed. A noise level of the setting rotor wings is always greater than that of a common rotor wing, which can be effectively used in a rotor wing blade-vortex interference noise experiment. By using the apparatus of the invention, cost of the blade-vortex interference noise experiment is greatly saved, which is good for middle-and-small-sized laboratory to carry out research on the helicopter rotor blade-vortex interference noise.
Description
Technical field
The present invention relates to aerodynamic noise experimental technique field, specifically a kind of device for lifting airscrew oar-vortex interaction noise experiment.
Background technology
Rotor-vortex interaction noise is the distinctive a kind of noise of helicopter.Oar-vortex interaction phenomenon is there will be under the state of flights such as oblique decline, zig zag state.When typical oar-vortex interaction noise occurs, noise sound can increase more than 10dB, is detected the steep increasing more than 3 times of distance.This is very serious noise.In order to carry out rotor-vortex interaction noisiness and Research of Noise Reduction, need the experiment carrying out this noise like.Current lifting airscrew oar-vortex interaction noise experiment has acoustic wind tunnel and outfield flight experiment two class.
The experiment of first kind acoustic wind tunnel is a kind of comparatively conventional rotor-vortex interaction noise experiment method, the ultimate principle of experiment is arranged on by model rotor in large-scale wind-tunnel, the generation of flowing, being simulated rotor-vortex interaction phenomenon by the inclination adjusting rotor face sudden before being realized by blasting.In order to carry out noise measurement, need to carry out acoustic treatment to wind tunnel experiment section, hole wall surrounding adopts wedge absorber to surround to avoid pneumatic noise, shear layer and Doppler effect to the interference of microphone.Such as U.S. NASA carried out oar-vortex interaction noise experiment at the opening experimental section (8m × 6m) of DNW wind-tunnel acoustic wind tunnel.Carry out such experiment and necessarily have suitable acoustic wind tunnel.
The flight noise experiment of Equations of The Second Kind outfield is noise when directly measuring prototype flight.In order to can analysis design mothod result quantitatively, need during experiment on helicopter, to install some extra experiment monitoring equipment additional, to obtain the detailed data of rotor control amount, motion state and fuselage attitude.Meanwhile, in order to experimental data is more reliable, pilot must keep state of flight constant for a long time, and this all wants high requirement for experimental facilities and driving technology.
In sum, no matter the oar carried out at present-vortex interaction noise experiment is acoustic wind tunnel experiment or outfield flight experiment, all there is experimental provision complexity, facility requirements is high, preparatory period length, the human and material resources of experiment cost, financial resources cost are also that huge, general middle-size and small-size research institution cannot carry out similar experiment undoubtedly.
Summary of the invention
The present invention is directed to existing oar-vortex interaction noise experiment (acoustic wind tunnel, the full machine outfield) shortcomings such as equipment requirement is many, process is complicated, cost is large, a kind of oar-vortex interaction noise experiment device is proposed, utilize this device can there is no that wind-tunnel etc. is expensive, under the condition of complex experiment facility, simulate lifting airscrew oar-vortex interaction noise, carry out two class oar-vortex interaction noise experiment easily.
Device for lifting airscrew oar-vortex interaction noise experiment disclosed by the invention, comprises blade wallboard, auricle, Bolt, sleeve, angle set bolt, bearing, drive unit, the second rotor, the first rotor and propeller hub.First rotor, sleeve and the second rotor are fixed on propeller hub by described angle set bolt; Propeller hub is installed on the drive means, and drive unit is fixed on bearing; Be connected with the upper lower wall panels of blade at the Bolt of auricle up and down of rotor joint, the auricle up and down of joint overlaps mutually with upper lower wall panels respectively.First rotor is socketed on the rotary shaft by sleeve and the second rotor, by loading the sleeve of different length, can regulate the distance between two rotors; And the angle of the first rotor and the second rotor can be regulated by turnbarrel, then turnbarrel, the first rotor and the second rotor three tighten fixing by use angle set bolt, and the angle of the first rotor and the second rotor has also just been fixed.
As the further improvement of technique scheme, described first rotor and the second rotor adopt non-co-planar to arrange.
Another kind as technique scheme improves, and described propeller hub employing is waved, shimmy flexible sheets.
The oar that table 1 adopts this device to carry out-vortex interaction noise experiment effectiveness unit (dBA)
As can be seen from the above table, under the total elongation selected by the example cited by the present invention and rotating speed, the present invention arranges that the noise level of rotor is always greater than common rotor.This is because, non-co-planar arrange under, compared with arranging rotor with plain type, apparatus of the present invention layout the blade tip whirlpool of upper rotor and the blade of lower rotor closer to, there is serious oar-vortex interaction in some cases.And the rotor that plain type is arranged is at floating state, generally there will not be the situation that blade tip whirlpool and succeeding paddle meet above blade.Show thus, this device can effectively for the experiment of rotor-vortex interaction noise.
The cost of oar-vortex interaction noise experiment saved greatly by experimental provision of the present invention, is conducive to medium and small laboratory and studies lifting airscrew oar-vortex interaction noise.
Accompanying drawing explanation
Fig. 1 is the apparatus structure schematic diagram of the present invention for lifting airscrew oar-vortex interaction noise experiment;
Fig. 2 is experimental provision rotor of the present invention assembling schematic diagram;
Fig. 3 is the schematic diagram of experimental provision of the present invention;
When Fig. 4 is Δ ψ=30 °, two rotor interval 3cm arrangenent diagrams
When Fig. 5 is Δ ψ=45 °, two rotor interval 3cm arrangenent diagrams
When Fig. 6 is Δ ψ=60 °, two rotor interval 3cm arrangenent diagrams
When Fig. 7 is Δ ψ=0 °, two rotor interval 3cm arrangenent diagrams
When Fig. 8 is Δ ψ=90 °, two rotor interval 3cm arrangenent diagrams
When Fig. 9 is Δ ψ=30 °, two rotor interval 4cm arrangenent diagrams
When Figure 10 is Δ ψ=30 °, two rotor interval 5cm arrangenent diagrams
Figure 11 is the rough package drawing in anechoic room noise experiment;
Figure 12 is the rough package drawing in outfield noise experiment;
Figure 13 is Δ ψ=30 °, n=1000rpm, the acoustic pressure time history diagram of Hexamermis spp during two rotor interval 3cm;
Figure 14 is Δ ψ=30 °, n=1000rpm, the sound pressure level spectrogram of Hexamermis spp during two rotor interval 3cm.
Embodiment
Below in conjunction with accompanying drawing, a kind of device for lifting airscrew oar-vortex interaction noise experiment that the present invention proposes is described in detail.In embodiment lift concrete numerical value, be only in order to illustrative experiment device and experiment effect, do not limit the scope of the invention.
Equipment requirement is many, process is complicated, cost is large for existing rotor-vortex interaction noise experiment (acoustic wind tunnel, full machine outfield), utilize the device for lifting airscrew oar-vortex interaction noise experiment of the present invention, can under the condition not having the expensive Experimental Establishments such as wind-tunnel, carry out two class oar-vortex interaction noise experiment easily: one is carry out by the angle converted between upper and lower two secondary rotors oar-vortex interaction noisiness that Reality simulation rotor produces in different orientations, realizes parameter influence research; Second is change lower rotor aerodynamic configuration, realizes advanced aerodynamic configuration rotor-vortex interaction noise experiment.In addition, when adopting this device to test, both can carry out in the indoor with noise elimination environment, also can carry out in the outdoor that ground unrest is less.
As shown in Figure 1, the device for lifting airscrew oar-vortex interaction noise experiment of the present invention comprises blade wallboard 10, auricle 9, Bolt 8, sleeve 7, angle set bolt 6, bearing 5, drive unit 4, second rotor 3, first rotor 2 and propeller hub 1.First rotor 2, sleeve 7 and the second rotor 3 are fixed on propeller hub 1 by described angle set bolt 6; Propeller hub 1 is arranged on drive unit 4, and drive unit 4 is fixed on bearing 5.The auricle up and down 9 of described rotor joint is connected with the upper lower wall panels 10 of blade with Bolt 8, and the auricle up and down 9 of rotor joint overlaps mutually with upper lower wall panels 10 respectively.First rotor 2 and the second rotor 3 are socketed on the rotary shaft by sleeve 7, by loading the sleeve 7 of different length, can regulate the distance between two rotors; And the angle of the first rotor 2 and the second rotor 3 can be regulated by turnbarrel 7, then three tightens fixing by use angle set bolt 6, and the angle of the first rotor 2 and the second rotor 3 has also just been fixed.Described first rotor 2 and the second rotor 3 adopt non-co-planar to arrange, when namely two blades rotate not in same Plane of rotation.The employing of described propeller hub 1 is waved, shimmy flexible sheets.Described drive unit 4 is the motor that can drive rotor wing rotation.
As shown in Figure 2, experimental provision principle of work of the present invention is: in device, the first and second rotors are respectively upper and lower rotor, upper and lower rotor adopts non-co-planar to arrange, blade tip whirlpool is produced in its blade tips during upper rotor work, the blade tip whirlpool that spiral moves downward and lower rotor blade collide, namely form " oar-vortex interaction ", by the intensity regulating the blade angle of attack of upper rotor can change blade tip whirlpool, realize the controlled of blade tip vortices breakdown; Change angle between upper and lower rotor blade and axial spacing then can realize the change that position occurs oar-vortex interaction.
The example utilizing experimental provision of the present invention to carry out testing is as follows:
One, Plant arrangement
1, Fig. 1 and 2 is a rotor experiment table (frame) for noise experiment of this experiment embodiment design, and the design of this rotor experiment table had both considered the requirement of experiment of acoustical laboratory, have also contemplated that the requirement of outfield experiments simultaneously.Bearing 5 is connected with the existing base of anechoic room, fixed drive motor above it.In order to avoid backflow, and utilize the existing exhaust passage of anechoic room, by rotor shaft horizontal positioned on this rotor stand, the requirement of choosing of the propeller hub centre distance floor level of model rotor mainly ensures that rotor can not encounter ground (in Fig. 1, this device is chosen is highly 1.9 meters).
2, the layout of model rotor
In an experiment, angle and two rotors can be changed between upper and lower rotor respectively between the upper and lower apart from testing, to simulate the interference of upper rotor blade tip whirlpool and lower rotor blade.As shown in figs. 3-9, it is 30 °, 45 °, 60 °, 0 °, 90 ° that the angle in Fig. 3, Fig. 4, Fig. 5, Fig. 6, Fig. 7 between two width rotors is respectively, and two rotor spacing are 3cm; Angle in Fig. 8, Fig. 9 between two width rotors is 30 °, and the spacing of two rotors is respectively 4cm and 5cm.
3, the layout of experiment measuring point
As shown in FIG. 10 and 11, be respectively the rough package drawing of anechoic room noise experiment and the rough package drawing of outfield noise experiment, measurement point below rotor disk is positioned at on the line of rotor hub center and the measurement point circle that is radius, and different measuring point radius is different; And respectively between Plane of rotation on different angle, in this example, angle selects 30 °, 45 °, 60 ° and 90 °, on the direction that other angles also can be selected to carry out testing.Measure apart from multiple location points of rotor hub center different distance different directions in rotor disk plane and under oar dish plane respectively in anechoic room noise experiment and outfield noise experiment, concrete measurement point is arranged and is respectively:
Being arranged in on propeller hub center and the measurement point circle that is radius of anechoic chamber's measurement point, measurement point 16 and 17 is arranged in propeller hub center for the center of circle, and radius is on the circle of 1.55 meters, and angle is respectively 45 ° and 0 °; Measurement point 11,12,13,14 and 15 is arranged in propeller hub center for the center of circle, and radius is on the circle of 1.8 meters, and angle is respectively 0 °, 30 °, 45 °, 60 ° and 90 °.
The layout of outfield measurement point is equally on the circle being radius with propeller hub center and measurement point, and measurement point 17 is arranged in propeller hub center for the center of circle, and radius is on the circle of 1.55 meters, and angle is 0 °; Measurement point 13 is arranged in propeller hub center for the center of circle, and radius is on the circle of 1.8 meters, and angle is 45 °; Measurement point 11,12,14 and 16 is arranged in propeller hub center for the center of circle, and radius is on the circle of 4.0 meters, and angle is respectively 0 °, 30 °, 60 ° and 45 °; Measurement point 15 is arranged in propeller hub center for the center of circle, and radius is on the circle of 7.0 meters, and angle is 45 °.
4, model rotor
Bladepiston is rectangle, shown in the table 2 that design parameter is following.
Table 2 rotor parameter
| Rotor diameter: | 2.0m |
| Blade chord length: | 0.06m |
| Paddle blade number: | 4 |
| Blade twist: | 0 |
5, number is adopted and surveying instrument
Test the surveying instrument used to comprise microphone, acoustical signal conditioning instrument, count and adopt and analytic system etc.The microphone used in anechoic room noise experiment with outfield noise experiment is identical, and microphone model is HS14417 type, carries out signal amplification by each channel sound signal condition instrument, and the sound pressure level of output is A sound level.
Two, experimental situation
This experimental provision without particular restriction to experimental site, can carry out at anechoic room, also can test in outfield.
1, anechoic room
The wall of anechoic room, ceiling and ground have been covered with " wedge ", and " wedge " is made primarily of glass wool, has good acoustically effective.As shown in Figure 10, being arranged in on propeller hub center and the measurement point circle that is radius of anechoic chamber's measurement point, measurement point 16 and 17 is arranged in propeller hub center for the center of circle, and radius is on the circle of 1.55 meters, and angle is respectively 45 ° and 0 °; Measurement point 11,12,13,14 and 15 is arranged in propeller hub center for the center of circle, and radius is on the circle of 1.8 meters, and angle is respectively 0 °, 30 °, 45 °, 60 ° and 90 °.
2, outfield noise experiment
This programme also can be tested in outfield.The advantage of outfield experiments is the impact do not refluxed, and avoids the additional noise that pneumatic noise is brought; Shortcoming is that ground unrest is very high.In order to overcome the unfavorable factors such as ground unrest is large in experiment, can select to test at night.The ground unrest at night is very little.Adopt the rotor identical with anechoic room in outfield experiments, and rotor is arranged also identical.In order to prevent ground return, fix the location arrangements of microphone part " wedge " on the ground, the glass wool of remaining some location arrangements bulk is in order to preventing acoustic reflection.Meanwhile, as shown in figure 11, relative to the experiment of anechoic room, carried out adjustment again to measuring point, the line at measurement point and propeller hub center and the angle of rotor shaft do not change, and measurement point 17 is arranged in propeller hub center as the center of circle, radius is on the circle of 1.55 meters, and angle is 0 °; Measurement point 13 is arranged in propeller hub center for the center of circle, and radius is on the circle of 1.8 meters, and angle is 45 °; Measurement point 11,12,14 and 16 is arranged in propeller hub center for the center of circle, and radius is on the circle of 4.0 meters, and angle is respectively 0 °, 30 °, 60 ° and 45 °; Measurement point 15 is arranged in propeller hub center for the center of circle, and radius is on the circle of 7.0 meters, and angle is 45 °.
Three, experimental result
1, apparatus of the present invention experiment effect test
The rotor (when namely two blades rotate not in same Plane of rotation) that this device adopts two secondary non-co-planar to arrange.The blade tip whirlpool of upper rotor can be collided with lower rotor blade, forms stronger oar-vortex interaction, causes the raising of noise level.Following table 3 is total distances (namely at the established angle of r=0.7R place feature profile) of experiment measuring is θ
7=10 °, rotating speed is the overall noise level of each passage in n=1000rpm situation.
This device of table 3 tests oar-vortex interaction noise testing result unit (dBA) at anechoic room
2, this device is utilized to carry out change oar-vortex interaction type experiment
By converting the angle between upper and lower two secondary rotors, this device can oar-vortex interaction noisiness of producing in different orientations of Reality simulation rotor, realizes the experimental study becoming oar-vortex interaction type.In experiment, this device have employed 5 kinds of rotor angles altogether and arranges, namely Δ ψ=0 °, 30 °, 45 °, 60 ° and 90 °.It is n=1000rpm, total distance θ that following table gives gyroplane rotate speed
7the A weighted sound pressure level (dBA) of rotor overall noise when=10 °.
Test the noise vs unit (dBA) of each measuring point at anechoic room when table 4 different rotor angle is arranged
When Figure 12 shows and tests in anechoic chamber, Δ ψ=30 °, n=1000rpm, the acoustic pressure time history of Hexamermis spp during two rotor interval 3cm, Figure 13 shows Δ ψ=30 °, n=1000rpm, the sound press level spectrum of Hexamermis spp during two rotor interval 3cm.Two acoustic pressure time history diagrams as can be seen from Figure 12, front rotor under arrangement states under, acoustic pressure pulse quantity significantly increases, and pulse amplitude increases, the time history of the acoustic pressure of this state has obvious oar-vortex interaction characteristic, illustrate that rotor there occurs serious BVI at this operation state, cause the sharply rising of rotor noise level thus.
3. utilize this device to carry out change vortex strength oar-vortex interaction noise experiment
By changing the rotating speed of upper rotor, the vortex strength of generation can be changed, thus carry out the quantitative examination of vortex strength to oar-vortex interaction noise experiment.In experiment, this device selects two kinds of rotating speeds to test, i.e. n=1000rpm, n=1200rpm.Following table 5 lists the noise figure of each passage when rotor angle is Δ ψ=45 ° respectively.
Test the noise figure of each passage at anechoic room when table 5 rotor angle is Δ ψ=45 °
Can find out that noise is obviously strengthened when faster rotational speed by table 5.
Under the total elongation selected by the example cited by the present invention and rotating speed, the noise level of Plant arrangement rotor of the present invention is always greater than common rotor.This is because, non-co-planar arrange under, compared with arranging rotor with plain type, apparatus of the present invention layout its blade tip whirlpool of upper rotor and lower rotor blade closer to, there is serious oar-vortex interaction in some cases.And the rotor that plain type is arranged is at floating state, generally there will not be the situation that blade tip whirlpool and succeeding paddle meet above blade.Show thus, this device can effectively for the experiment of rotor-vortex interaction noise.
Embody rule approach of the present invention is a lot, and the above is only the preferred embodiment of the present invention, should be understood that; for those skilled in the art; under the premise without departing from the principles of the invention, can also make some improvement, these improvement also should be considered as protection scope of the present invention.
Claims (5)
1., for a device for lifting airscrew oar-vortex interaction noise experiment, comprise blade wallboard (10), auricle (9), sleeve (7), bearing (5), drive unit (4), the second rotor (3), the first rotor (2) and propeller hub (1); Described first rotor (2), sleeve (7) and the second rotor (3) are fixed on propeller hub (1); Propeller hub (1) is arranged on drive unit (4), and drive unit (4) is fixed on bearing (5); Mutually overlap with upper lower wall panels (10) respectively at the auricle up and down (9) of rotor joint; First rotor (2) and the second rotor (3) are socketed on the rotary shaft by sleeve (7), by loading the sleeve (7) of different length, regulate the distance between two rotors; The angle of the first rotor (2) and the second rotor (3) is regulated by turnbarrel (7).
2. the device for lifting airscrew oar-vortex interaction noise experiment according to claim 1, is characterized in that: when described first rotor (2) and the second rotor (3) adopt non-co-planar to arrange that namely two blades rotate not in same Plane of rotation.
3. the device for lifting airscrew oar-vortex interaction noise experiment according to claim 1, it is characterized in that: also comprise angle set bolt (6), first rotor (2), sleeve (7) and the second rotor (3) are fixed on propeller hub (1) by described angle set bolt (6), for fixing the angle of the first rotor (2) and the second rotor (3).
4. the device for lifting airscrew oar-vortex interaction noise experiment according to claim 1, is characterized in that: also comprise Bolt (8), and the auricle up and down (9) of described rotor joint is connected with the upper lower wall panels (10) of blade with Bolt (8).
5. the device for lifting airscrew oar-vortex interaction noise experiment according to claim 1, is characterized in that: described propeller hub (1) employing is waved, shimmy flexible sheets.
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| CN107444673A (en) * | 2017-07-12 | 2017-12-08 | 南京航空航天大学 | The control noise reduction test platform that is synchronised based on small propeller fixed-wing unmanned plane |
| CN108100300A (en) * | 2017-12-03 | 2018-06-01 | 中国直升机设计研究所 | A kind of whirlpool generating means for whole elimination room paddle-vortex interaction experiment |
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| CN110844115B (en) * | 2019-10-18 | 2022-04-12 | 中国直升机设计研究所 | Method for judging effectiveness of data of propeller vortex interference noise and blade flapping load |
| CN112414667A (en) * | 2020-10-30 | 2021-02-26 | 中国航空工业集团公司西安飞机设计研究所 | Wind tunnel test method for aerodynamic noise of turboprop aircraft |
| CN112407321A (en) * | 2020-10-30 | 2021-02-26 | 中国直升机设计研究所 | Method for generating azimuth angle signal based on helicopter rotor rotation speed |
| CN112414667B (en) * | 2020-10-30 | 2023-03-14 | 中国航空工业集团公司西安飞机设计研究所 | Wind tunnel test method for aerodynamic noise of turboprop aircraft |
| CN112278265B (en) * | 2020-11-05 | 2023-09-12 | 南京航空航天大学 | Phase angle processing logic in propeller synchronous control |
| CN112278265A (en) * | 2020-11-05 | 2021-01-29 | 南京航空航天大学 | Phase angle processing logic in propeller phase synchronization control |
| CN112373723A (en) * | 2020-11-20 | 2021-02-19 | 中国直升机设计研究所 | Rotor noise microphone array |
| CN112556968A (en) * | 2021-02-23 | 2021-03-26 | 中国空气动力研究与发展中心低速空气动力研究所 | Three-quarter opening test section for acoustic wind tunnel test |
| CN112556968B (en) * | 2021-02-23 | 2021-05-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Three-quarter opening test section for acoustic wind tunnel test |
| CN113705116A (en) * | 2021-04-20 | 2021-11-26 | 中国直升机设计研究所 | Guidance method for low-noise flight of helicopter |
| CN113705116B (en) * | 2021-04-20 | 2023-05-23 | 中国直升机设计研究所 | Helicopter low-noise flight guiding method |
| CN113670559A (en) * | 2021-10-19 | 2021-11-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Helicopter rotor noise active control wind tunnel test method based on trailing edge winglet |
| CN113670559B (en) * | 2021-10-19 | 2022-01-25 | 中国空气动力研究与发展中心低速空气动力研究所 | Helicopter rotor noise active control wind tunnel test method based on trailing edge winglet |
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