CN205819560U - A kind of low noise blade for rotor craft - Google Patents
A kind of low noise blade for rotor craft Download PDFInfo
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- CN205819560U CN205819560U CN201620556517.3U CN201620556517U CN205819560U CN 205819560 U CN205819560 U CN 205819560U CN 201620556517 U CN201620556517 U CN 201620556517U CN 205819560 U CN205819560 U CN 205819560U
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- 239000000203 mixture Substances 0.000 claims description 5
- 241000208340 Araliaceae Species 0.000 claims 1
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 claims 1
- 235000003140 Panax quinquefolius Nutrition 0.000 claims 1
- 235000008434 ginseng Nutrition 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 abstract description 7
- 238000005516 engineering process Methods 0.000 abstract description 4
- 238000000034 method Methods 0.000 description 6
- 230000035939 shock Effects 0.000 description 3
- 238000004088 simulation Methods 0.000 description 2
- 108010069407 BERP Proteins 0.000 description 1
- 102100038798 Tripartite motif-containing protein 3 Human genes 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000009499 grossing Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000003786 synthesis reaction Methods 0.000 description 1
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Abstract
This utility model embodiment discloses a kind of low noise blade for rotor craft, relates to aeromechanics technology field, it is possible to while ensureing blade production cost and structural strength, improves pneumatic efficiency and reduces noise.This utility model includes: anti-section under smooth extension, sweepforward section, sweepback section and sweepback, and under sweepforward section, sweepback section and sweepback, anti-section is positioned at outside blade, and blade outboard structure presents first sweepforward sweepback again；Smooth extension is to smooth laterally from starting point to extend to specify connection sweepforward section in place of radius, and starting point is blade and propeller hub junction；Sweepforward section connects smooth extension, and sweepback section connects sweepforward section, and under sweepback, anti-section connects sweepback section.This utility model is applicable to the rotor craft of low noise.
Description
Technical field
This utility model relates to aeromechanics technology field, particularly relates to a kind of low noise oar for rotor craft
Leaf.
Background technology
The lift producing method of rotor uniqueness makes rotor craft and other Flight Vehicle Design schemes there is marked difference.
Such as: rotor craft is interacted to produce lift with air by blade rotary motion, therefore blade at different radii
The speed of incoming flow that section is corresponding all has difference.
When carrying out more complicated flare maneuver at rotor craft, the air force state of rotor then can more be answered
Miscellaneous, such as: when flying before rotor craft, flow field can there is rotor blade tip distalmost end Transonic Flows simultaneously and rotor
Root low speed/reverse flow, and and the adjoint Various Complex aerodynamic phenomenon such as dynamic stall, oar-vortex interaction, these flowings
Have a strong impact on the noise characteristic of rotor so that the flight noise of rotor craft becomes bigger problem always.
In order to overcome noise problem, countries in the world all to design and apply a lot of novel oar while meeting aeroperformance
Point configuration design.Such as: the BERP series blade tip that the method using test to combine with numerical simulation technology of Britain is designed
Design uses on up-to-date EH101 series multimission helicopter, although have more excellent aeroperformance and noise
Performance, but its " short quant " configuration design changes in distribution is changeable, structure is complicated, production difficulty and production cost are high, mainly should
It is used in military field, it is difficult to apply in the higher commercial market of cost control requirement.
Therefore, the most still lack and can meet pneumatic efficiency and noiseproof feature simultaneously, and the relatively low blade of cost performance sets
Meter.
Utility model content
Embodiment of the present utility model provides a kind of low noise blade for rotor craft, it is possible to ensureing that blade is raw
While producing cost and structural strength, improve pneumatic efficiency and reduce aerodynamic noise.
For reaching above-mentioned purpose, embodiment of the present utility model adopts the following technical scheme that
Paddle blade structure composition includes: anti-section under smooth extension, sweepforward section, sweepback section and sweepback, described sweepforward section, sweepback
Under section and sweepback, anti-section is positioned at outside described blade, and described blade outboard structure presents first sweepforward sweepback again；Described smooth extension
Duan Weicong starting point smooths laterally in place of extending to specify radius and connects described sweepforward section, and described starting point is that blade is connected with propeller hub
Place；Described sweepforward section connects described smooth extension, and described sweepback section connects described sweepforward section, and under described sweepback, anti-section connects institute
State sweepback section.
It is that described sweepforward section is opened in place of described appointment radius more than 0.67R and less than 0.71R in place of described appointment radius
Beginning sweepforward, the maximum position that the sweepforward of described sweepforward section reaches is for more than 0.82R and less than 0.86R.Reach in described sweepforward
Maximum position, 1/4 string of a musical instrument of described sweepforward section is relative to the position sweepforward 0.47c with reference to the string of a musical instrument, and from 0.85R to outermost end
For linear sweepback region, blade tip sweepback to maximum and 1/4 chord location relative to reference to string of a musical instrument sweepback 1.1c, wherein, institute
Stating and be positioned at the 1/4 of smooth extension with reference to the string of a musical instrument, c is the length with reference to chord length.
While the sweepforward of described sweepforward section starts, chord length synchronizes to increase, and reaches in the sweepforward of described sweepforward section
Big position chord length increases to maximum, and the maximum increments scope of described chord length is more than 0.1c and less than 0.15c；And from institute
Stating at the maximum position that the sweepforward of sweepforward section reaches, to the distalmost end of described blade, described chord length linearly reduces, wherein, and blade
Tip distalmost end chord length is more than 0.1c and less than 0.5c.Under described sweepback the lower anti-original position of anti-section be more than 0.89R and
Less than 0.93R, inverted diherdral degree scope is more than 8 degree and less than 15 degree.
The low noise blade for rotor craft that this utility model embodiment provides, relative to conventional parabolic leading edge
Blade tip blade, the pneumatic efficiency of the blade in the present embodiment obtains and promotes, under high-speed flight state, relative to conventional blade tip oar
Its aerodynamic noise of leaf reduces substantially.And only by the structure design composition blade of sweepforward, the section of plunderring and the lower low production cost such as instead
Structure, it is ensured that while blade production cost and structural strength, improves pneumatic efficiency and reduces noise.
Accompanying drawing explanation
In order to be illustrated more clearly that the technical scheme in this utility model embodiment, will make required in embodiment below
Accompanying drawing be briefly described, it should be apparent that, below describe in accompanying drawing be only embodiments more of the present utility model,
For those of ordinary skill in the art, on the premise of not paying creative work, it is also possible to obtain according to these accompanying drawings
Other accompanying drawing.
The floor map of the blade that Fig. 1 provides for this utility model embodiment；
Fig. 2, the perspective view of 4 blades provided for this utility model embodiment；
The top view along Y-axis of the blade that Fig. 3 provides for this utility model embodiment.
Detailed description of the invention
For making those skilled in the art be more fully understood that the technical solution of the utility model, real with concrete below in conjunction with the accompanying drawings
This utility model is described in further detail by mode of executing.Of the present utility model embodiment is described in more detail below, described
The example of embodiment is shown in the drawings, the most same or similar label represent same or similar element or
There is the element of same or like function.The embodiment described below with reference to accompanying drawing is exemplary, is only used for explaining
This utility model, and can not be construed to restriction of the present utility model.Those skilled in the art of the present technique are appreciated that unless specially
Statement, singulative used herein " ", " one ", " described " and " being somebody's turn to do " may also comprise plural form.Should manage further
Solving, the wording used in description of the present utility model " includes " referring to there is described feature, integer, step, operation, unit
Part and/or assembly, but it is not excluded that existence or add other features one or more, integer, step, operation, element, assembly
And/or their group.It should be understood that when we claim element to be " connected " or during " coupled " to another element, and it can directly connect
Connect or be couple to other elements, or intermediary element can also be there is.Additionally, " connection " used herein or " coupling " can be wrapped
Include wireless connections or couple.Wording "and/or" used herein includes one or more arbitrary list listing item being associated
Unit and all combination.Those skilled in the art of the present technique are appreciated that unless otherwise defined, and all terms used herein (include
Technical term and scientific terminology) have with the those of ordinary skill in this utility model art be commonly understood by identical meaning
Justice.Should also be understood that those terms defined in such as general dictionary should be understood that have with prior art upper
The meaning that meaning hereinafter is consistent, and unless defined as here, will not come by idealization or the most formal implication
Explain.This utility model embodiment provides a kind of low noise blade for rotor craft, as Figure 1-4, paddle blade structure
Composition includes: anti-section under smooth extension, sweepforward section, sweepback section and sweepback, anti-section under described sweepforward section, sweepback section and sweepback
Outside described blade, described blade outboard structure presents first sweepforward sweepback again, and described smooth extension is from starting point laterally
Smoothing and connect described sweepforward section in place of extending to specify radius, described starting point is blade and propeller hub junction.Described sweepforward Duan Lian
Connecing described smooth extension, described sweepback section connects described sweepforward section, and under described sweepback, anti-section connects described sweepback section.Wherein,
In accompanying drawing 2-4, z represents the z coordinate parameter in x-y-z coordinate system.It should be noted that propeller hub is blade when rotated
Center of rotation.
Concrete, in the present embodiment, as shown in Figures 2 and 3, it is more than 0.67R and to be less than in place of described appointment radius
0.71R, described sweepforward section starts sweepforward in place of described appointment radius, and the maximum position that the sweepforward of described sweepforward section reaches is big
In 0.82R and less than 0.86R.Wherein, with described propeller hub as starting point, apart from a length of 1R of the distalmost end of described blade.
In the preferred version of the present embodiment, it is 0.69R in place of described appointment radius.The sweepforward of described sweepforward section reaches
Maximum position is 0.85R.
Concrete, in the present embodiment, as shown in Figures 2 and 3, in the maximum position that described sweepforward reaches, described sweepforward section
1/4 string of a musical instrument relative to the position sweepforward 0.47c with reference to the string of a musical instrument, and be linear sweepback region from 0.85R to outermost end, blade
Most advanced and sophisticated sweepback is the most maximum and 1/4 chord location is relative to reference to string of a musical instrument sweepback 1.1c, and wherein, the described reference string of a musical instrument is positioned at smooth prolonging
At the 1/4 of the section of stretching, c is the length with reference to chord length.
Further, while the sweepforward of described sweepforward section starts, chord length synchronizes to increase, and reaches in the sweepforward of described sweepforward section
To maximum position at chord length increase to maximum, the maximum increments scope of described chord length is more than 0.1c and less than 0.15c.
And at the maximum position that the sweepforward of described sweepforward section reaches, to the distalmost end of described blade, described chord length linearly reduces, its
In, blade tip distalmost end chord length is more than 0.1c and less than 0.5c.
In the preferred version of the present embodiment, the maximum increments of described chord length is 0.132c.Described blade tip is farthest
End chord length is 0.2c.
Concrete, in the present embodiment, as shown in Figure 4, under described sweepback, the lower anti-original position of anti-section is more than 0.89
And less than 0.93R, inverted diherdral degree α in the range of more than 8 degree and less than 15 degree.
In the preferred version of the present embodiment, under described sweepback, the lower anti-original position of anti-section is 0.92R, inverted diherdral degree α
It it is 10 degree.
By CFD approach numerical simulation, showing under more high-speed state, blade can weaken table in blade leading edge effectively
The negative pressuren zone intensity in face, reduces the scope of transonic speed critical flow, improves critical Mach number, thus reduces drag due to shock wave.Can
To weaken the comperssibility influences such as the shock wave of advancing blade, improve the stalling angle of retreating blade simultaneously.Now it is pneumatic for synthesis
Performance is substantially better than the parabolic leading edge blade tip blade of routine.Compared with other blade, it is possible to be obviously improved transonic characteristic, weaken
Shock waves etc., also have excellent noise characteristic while obtaining high blade aerodynamic performance.Especially when front flying, relative to often
The parabolic leading edge blade tip blade of rule, the pneumatic efficiency of the blade in the present embodiment obtains the lifting of 2%, in high-speed flight state
Under, reduce 1.5-3dB relative to conventional blade tip blade aerodynamic noise.And it is only low by sweepforward, the section of plunderring and the lower production cost such as instead
Honest and clean structure design composition paddle blade structure, it is ensured that while blade production cost and structural strength, improve pneumatic efficiency and fall
Low noise.
Each embodiment in this specification all uses the mode gone forward one by one to describe, identical similar portion between each embodiment
Dividing and see mutually, what each embodiment stressed is the difference with other embodiments.Real especially for equipment
For executing example, owing to it is substantially similar to embodiment of the method, so describing fairly simple, relevant part sees embodiment of the method
Part illustrate.The above, detailed description of the invention the most of the present utility model, but protection domain of the present utility model is also
Being not limited to this, any those familiar with the art, in the technical scope that this utility model discloses, can think easily
The change arrived or replacement, all should contain within protection domain of the present utility model.Therefore, protection domain of the present utility model should
Should be as the criterion with scope of the claims.
Claims (11)
1. the low noise blade for rotor craft, it is characterised in that paddle blade structure composition includes: smooth extension,
Anti-section under sweepforward section, sweepback section and sweepback, under described sweepforward section, sweepback section and sweepback, anti-section is positioned at outside described blade, described
Blade outboard structure presents first sweepforward sweepback again；
Described smooth extension for from starting point laterally smooth extend to specify radius in place of connect described sweepforward section, described starting point
For blade and propeller hub junction；
Described sweepforward section connects described smooth extension, and described sweepback section connects described sweepforward section, and under described sweepback, anti-section connects
Described sweepback section.
Low noise blade for rotor craft the most according to claim 1, it is characterised in that described appointment radius it
Place is for more than 0.67R and less than 0.71R, and described sweepforward section starts sweepforward in place of described appointment radius, before described sweepforward section
Plunder the maximum position reached for more than 0.82R and less than 0.86R.
Low noise blade for rotor craft the most according to claim 2, it is characterised in that described appointment radius it
Place is 0.69R.
Low noise blade for rotor craft the most according to claim 2, it is characterised in that before described sweepforward section
Plunderring the maximum position reached is 0.85R.
Low noise blade for rotor craft the most according to claim 4, it is characterised in that
At the maximum position that described sweepforward reaches, 1/4 string of a musical instrument of described sweepforward section is relative to the position sweepforward with reference to the string of a musical instrument
0.47c, and be linear sweepback region from 0.85R to outermost end, blade tip sweepback to maximum and 1/4 chord location are relative to ginseng
Examining string of a musical instrument sweepback 1.1c, wherein, the described reference string of a musical instrument is positioned at the 1/4 of smooth extension, and c is the length with reference to chord length.
Blade for low noise rotor craft the most according to claim 5, it is characterised in that in described sweepforward section
While sweepforward starts, chord length synchronizes to increase, and chord length increases to maximum at the maximum position that the sweepforward of described sweepforward section reaches
Value, the maximum increments scope of described chord length is more than 0.1c and less than 0.15c；
And at the maximum position that the sweepforward of described sweepforward section reaches, to the distalmost end of described blade, described chord length linearly reduces,
Wherein, distalmost end chord length in blade tip is more than 0.1c and less than 0.5c.
Low noise blade for rotor craft the most according to claim 6, it is characterised in that the maximum of described chord length
Increments is 0.132c.
Low noise blade for rotor craft the most according to claim 6, it is characterised in that described blade tip is
Far-end chord length is 0.2c.
Low noise blade for rotor craft the most according to claim 1, it is characterised in that anti-section under described sweepback
Lower anti-original position be more than 0.89 and less than 0.93R, inverted diherdral degree scope be more than 10 degree and to be less than 15 degree.
Low noise blade for rotor craft the most according to claim 9, it is characterised in that anti-under described sweepback
The lower anti-original position of section is 0.92R, and inverted diherdral degree is 10 degree.
11. according to the blade for low noise rotor craft described in any one in claim 1-10, it is characterised in that
With the described place that links with propeller hub as starting point, apart from a length of 1R of the distalmost end of described blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620556517.3U CN205819560U (en) | 2016-06-08 | 2016-06-08 | A kind of low noise blade for rotor craft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620556517.3U CN205819560U (en) | 2016-06-08 | 2016-06-08 | A kind of low noise blade for rotor craft |
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| Publication Number | Publication Date |
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| CN205819560U true CN205819560U (en) | 2016-12-21 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201620556517.3U Active CN205819560U (en) | 2016-06-08 | 2016-06-08 | A kind of low noise blade for rotor craft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105923155A (en) * | 2016-06-08 | 2016-09-07 | 南京航空航天大学 | Low-noise paddle for rotor craft |
| CN114560082A (en) * | 2022-02-16 | 2022-05-31 | 西南科技大学 | Combined modification type propeller tip structure capable of effectively controlling propeller tip vortex and design method |
-
2016
- 2016-06-08 CN CN201620556517.3U patent/CN205819560U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105923155A (en) * | 2016-06-08 | 2016-09-07 | 南京航空航天大学 | Low-noise paddle for rotor craft |
| CN114560082A (en) * | 2022-02-16 | 2022-05-31 | 西南科技大学 | Combined modification type propeller tip structure capable of effectively controlling propeller tip vortex and design method |
| CN114560082B (en) * | 2022-02-16 | 2023-07-04 | 西南科技大学 | Combined shape-modifying blade tip structure capable of effectively controlling blade tip vortex and design method |
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| GR01 | Patent grant |