CN206704526U - A kind of rotor of high lift-drag ratio - Google Patents
A kind of rotor of high lift-drag ratio Download PDFInfo
- Publication number
- CN206704526U CN206704526U CN201720519929.4U CN201720519929U CN206704526U CN 206704526 U CN206704526 U CN 206704526U CN 201720519929 U CN201720519929 U CN 201720519929U CN 206704526 U CN206704526 U CN 206704526U
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- CN
- China
- Prior art keywords
- rotor
- vortex generator
- radome fairing
- pit type
- drag ratio
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Abstract
It the utility model is related to a kind of rotor of high lift-drag ratio, including rotor matrix and the radome fairing installed in rotor matrix leading edge, radome fairing is provided with pit type vortex generator, pit type vortex generator is on the surface of radome fairing in embedded, and pit type vortex generator is located at the leading edge of radome fairing low regime, fin vortex generator is additionally provided with radome fairing, fin vortex generator is convex on the surface of radome fairing, and fin vortex generator is located at the leading edge of radome fairing low regime.The utility model is on the basis of the leading edge insertion pit type vortex generator of the radome fairing low regime of rotor matrix, fin vortex generator is installed to the leading vertical of the radome fairing low regime of rotor matrix again, when rotor matrix rotating speed from low to high or from high to low when, pit type vortex generator is all located at the low regime of radome fairing with fin vortex generator, and rotor matrix can be made to reach optimal pneumatic effect.
Description
Technical field
Lifting airscrew technical field is the utility model is related to, specifically, refers to a kind of rotor of high lift-drag ratio.
Background technology
Rotor is the important component of helicopter, and in the flight course of helicopter, rotor, which can play, produces lift and drawing
The double action of power, moreover, rotor can also function similarly to the effect of aircraft aileron, elevator, with science and technology
Development, safer, green lifting airscrew is increasingly valued by people.
The rotor of helicopter also has that noise is big, operating efficiency is low and the problem of ring of eddy at present, in big pitch, especially
It is that rotor is front and rear to produce larger pressure drag, makes the lift-drag ratio of lifting airscrew reduce when taking off, hover and landing.It is existing
Have in technology, helicopter, if unfavorable air-flow separation occurs in body surface, will bring many not in its flight envelope
Good consequence, such as increase resistance, reduce lift, cause stall in advance and asymmetric stall etc., therefore the rotation of most of helicopters
The wing prevents the premature disengagement of various air-flows using vortex generator, but is vortexed in the prior art used by the rotor of helicopter
The air-flow of premature disengagement when generator can only prevent the rotor from rotating at a high speed, and premature disengagement when can not prevent rotor low speed rotation
Air-flow.
Utility model content
Technical problem to be solved in the utility model is to provide a kind of rotor of high lift-drag ratio, postpones on lifting airscrew
The premature disengagement of air-flow, improve the lift-drag ratio of lifting airscrew.
The technical scheme that the utility model solves above-mentioned technical problem is as follows：A kind of rotor of high lift-drag ratio, including rotor
Matrix and the radome fairing installed in rotor matrix leading edge, the radome fairing are provided with pit type vortex generator, pit type whirlpool
Flow-generator is in embedded on the surface of radome fairing, and pit type vortex generator is located at the leading edge of radome fairing low regime.
Leading edge of the utility model in the radome fairing low regime of rotor matrix is embedded in pit type vortex generator, can make rotation
Wing matrix produces wingtip vortex in windstream, and difference is produced by rationally designing the recess heights of pit type vortex generator
The vortex of intensity, just can be energy after the wingtip vortex of this high-energy mixes with the low-energy boundary layer air flowing in wingtip vortex downstream
Pass to boundary layer, make the boundary layer flow field in adverse pressure gradient obtain can continue to be attached to after additional-energy body surface without
Cause separation.
This is similar to the pit of golf ball surface, and when golf ball flight, the fluid molecule of near surface is by pit
Caused whirlpool attracts, so that the resistance that pressure difference is formed before and after golf greatly reduces.
The beneficial effects of the utility model are：Air-flow can be reduced using the rotor matrix that embedded in pit type vortex generator
Premature disengagement, reduce pressure drag, so as to improve the lift-drag ratio of rotor matrix.It is demonstrated experimentally that when rotor matrix low speed revolves
When turning, pit type vortex generator can more effectively prevent the air-flow of premature disengagement during the rotation of rotor matrix.
On the basis of above-mentioned technical proposal, the utility model can also do following improvement.
Further, fin vortex generator is additionally provided with the radome fairing, fin vortex generator is on the surface of radome fairing
It is convex, and fin vortex generator is located at the leading edge of radome fairing low regime.
It is using the above-mentioned further beneficial effect of scheme：Leading edge in the radome fairing low regime of rotor matrix is embedded in pit
On the basis of formula vortex generator, then fin vortex generator is installed to the leading vertical of the radome fairing low regime of rotor matrix,
When rotor matrix rotates at a high speed, fin vortex generator can more effectively prevent the gas of premature disengagement during the rotation of rotor matrix
Stream, thus when rotor matrix rotating speed from low to high or from high to low when, pit type vortex generator and fin vortex generator
The low regime of radome fairing is all located at, rotor matrix can be made to reach optimal pneumatic effect.
Further, the plane of the pit type vortex generator is in honeycomb network structure, and at each cell edge
Highly higher than the height at each honeycomb center.
It is using the above-mentioned further beneficial effect of scheme：The pit type vortex generator structure of honeycomb network structure is steady
It is fixed, it can ensure that pit type vortex generator is hardly damaged, and the pit type vortex generator of honeycomb network structure, it can make
Air-flow uniformly, it is stable be distributed in each honeycomb, so as to ensure that the symmetry and stability of rotor matrix overdraught.
Further, it is provided with Z-shaped beam in the rotor matrix.
It is using the above-mentioned further beneficial effect of scheme：Z-shaped beam can play a supporting role to rotor matrix, make rotor
Matrix is not susceptible to deform, so as to further ensure the stability of rotor matrix overdraught.
Further, the low regime skins front edges material of the radome fairing is stainless steel.
It is using the above-mentioned further beneficial effect of scheme：Stainless steel good corrosion resistance, intensity are high, plasticity is high, toughness is high,
Using material of the stainless steel material as radome fairing low regime skins front edges, it is easy to process pit type vortex generation on radome fairing
Device and fin vortex generator.
Further, the high velocity skins front edges material of the radome fairing is titanium alloy.
It is using the above-mentioned further beneficial effect of scheme：Titanium alloy has that intensity is high and density is small, good mechanical property, tough
The characteristics of property and corrosion resistance are good, using material of the titanium alloy material as radome fairing high velocity skins front edges, can make rectification
Cover is not susceptible to deform, so as to ensure that the stability of rotor matrix overdraught.
Further, it is embedded with anti-icing equipment in the rotor matrix.
It is using the above-mentioned further beneficial effect of scheme：Defroster can avoid rotor matrix from making rotor due to freezing
The surface of matrix is smooth and the problem of causing air-flow premature disengagement.
Brief description of the drawings
Fig. 1 is the structural representation of radome fairing；
Fig. 2 is the structural representation of rotor matrix；
Fig. 3 is top view of the present utility model；
Fig. 4 is radome fairing and the sectional view of rotor matrix attachment structure；
Fig. 5 is the structural representation of pit type vortex generator.
In accompanying drawing, the list of parts representated by each label is as follows：
1st, radome fairing, 2, fin vortex generator, 3, pit type vortex generator, 4, rotor matrix, 5, Z-shaped beam.
Embodiment
Principle of the present utility model and feature are described below in conjunction with accompanying drawing, example is served only for explaining this practicality
It is new, it is not intended to limit the scope of the utility model.
Embodiment 1：
A kind of rotor of high lift-drag ratio, as shown in Figures 1 to 5, including radome fairing 1 and rotor matrix 4, radome fairing 1 are installed
In the leading edge of rotor matrix 4 to form the rotor of helicopter, the leading edge in the low regime of radome fairing 1 is embedded in pit type vortex generator
3, the plane of pit type vortex generator 3 is in honeycomb network structure, and the arrangement of whole pit type vortex generator 3 is with radome fairing 1
Profile variation and change, the height at each cell edge is higher than the height at each honeycomb center, at cell edge and honeybee
Difference in height and cellular size at nest center determine all in accordance with the flow velocity of each point air on rotor, and each honeybee
The edge of nest and the flush of radome fairing 1, are produced with avoiding pit type vortex generator 3 from protruding the surface of radome fairing 1
Unfavorable resistance.
The utility model can be reduced using the rotor matrix that embedded in pit type vortex generator 3 air-flow premature disengagement,
Reduce pressure drag, so as to improve the lift-drag ratio of rotor matrix 4.It is demonstrated experimentally that when rotor 4 low speed rotation of matrix, pit
Formula vortex generator 3 can more effectively prevent the air-flow of premature disengagement during the rotation of rotor matrix 4.
As shown in Figures 1 to 5, the low regime skins front edges of radome fairing 1 are made using stainless steel, the height of radome fairing 1
Fast area's skins front edges are made using titanium alloy, to ensure that radome fairing 1 is not susceptible to deform.It is provided with rotor matrix 4 Z-shaped
Beam 5, to ensure that rotor matrix 4 is not susceptible to deform.Be embedded with anti-icing equipment in rotor matrix 4, with avoid rotor matrix 4 due to
The problem of icing makes the surface of rotor matrix 4 smooth and causes air-flow premature disengagement.
Embodiment 2：
The present embodiment does further optimization on the basis of above-described embodiment, as shown in Figures 1 to 5, not only in radome fairing 1
Upper embedded pit type vortex generator 3, also the leading vertical installation fin vortex generator 2 in the low regime of radome fairing 1, fin whirlpool
Flow-generator 2 is laminated structure, and fin vortex generator 2 is convex on the surface of radome fairing 1.
Leading edge while right angle setting fin vortex generator 2 of the utility model in the low regime of radome fairing 1 of rotor matrix 4
With embedded pit type vortex generator 3, when 4 body low speed rotation of rotor base, pit type vortex generator 3 can be prevented effectively
The air-flow of premature disengagement when rotor matrix 4 rotates, when the body of rotor base 4 rotates at a high speed, fin vortex generator 2 can be effective
The air-flow of premature disengagement when preventing the rotation of rotor matrix, thus whole rotor matrix 4 rotating speed from low to high or by up to
When low, pit type vortex generator 3 is used cooperatively with fin vortex generator 2, and rotor matrix 4 can be made to reach optimal pneumatic
Effect.Further, since pit type vortex generator 3 is all located on radome fairing 1 with fin vortex generator 2, rotation is not interfered with also
In the case of big pitch when especially taking off, hover and landing, air-flow easily occurs for the overall structure of wing matrix 4, lifting airscrew
Separation, the problem of efficiency is low, are effectively improved, and also improve the lift-drag ratio of lifting airscrew.
Preferred embodiment of the present utility model is the foregoing is only, it is all in this practicality not to limit the utility model
Within new spirit and principle, any modification, equivalent substitution and improvements made etc., guarantor of the present utility model should be included in
Within the scope of shield.
Claims (7)
1. a kind of rotor of high lift-drag ratio, including rotor matrix（4）And installed in rotor matrix（4）The radome fairing of leading edge（1）,
It is characterized in that：The radome fairing（1）It is provided with pit type vortex generator（3）, pit type vortex generator（3）In radome fairing
（1）Surface in embedded, and pit type vortex generator（3）Positioned at radome fairing（1）The leading edge of low regime.
2. the rotor of high lift-drag ratio according to claim 1, it is characterised in that：The radome fairing（1）On be additionally provided with fin
Vortex generator（2）, fin vortex generator（2）In radome fairing（1）Surface it is convex, and fin vortex generator
（2）Positioned at radome fairing（1）The leading edge of low regime.
3. the rotor of high lift-drag ratio according to claim 2, it is characterised in that：The pit type vortex generator（3）'s
Plane is in honeycomb network structure, and the height at each cell edge is higher than the height at each honeycomb center.
4. the rotor of high lift-drag ratio according to claim 3, it is characterised in that：The rotor matrix（4）It is interior to be provided with Z-shaped beam
（5）.
5. the rotor of the high lift-drag ratio according to any one of Claims 1-4, it is characterised in that：The radome fairing（1）It is low
Fast area's skins front edges material is stainless steel.
6. the rotor of high lift-drag ratio according to claim 5, it is characterised in that：The radome fairing（1）High velocity leading edge
Covering material is titanium alloy.
7. the rotor of the high lift-drag ratio according to any one of Claims 1-4, it is characterised in that：The rotor matrix（4）In
It is embedded with anti-icing equipment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720519929.4U CN206704526U (en) | 2017-05-11 | 2017-05-11 | A kind of rotor of high lift-drag ratio |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720519929.4U CN206704526U (en) | 2017-05-11 | 2017-05-11 | A kind of rotor of high lift-drag ratio |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206704526U true CN206704526U (en) | 2017-12-05 |
Family
ID=60466923
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720519929.4U Expired - Fee Related CN206704526U (en) | 2017-05-11 | 2017-05-11 | A kind of rotor of high lift-drag ratio |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206704526U (en) |
-
2017
- 2017-05-11 CN CN201720519929.4U patent/CN206704526U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171205 Termination date: 20190511 |