CN1114944A - Aircraft wing installed impeller at wing end - Google Patents
Aircraft wing installed impeller at wing end Download PDFInfo
- Publication number
- CN1114944A CN1114944A CN 94107374 CN94107374A CN1114944A CN 1114944 A CN1114944 A CN 1114944A CN 94107374 CN94107374 CN 94107374 CN 94107374 A CN94107374 A CN 94107374A CN 1114944 A CN1114944 A CN 1114944A
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- CN
- China
- Prior art keywords
- wing
- impeller
- aircraft
- blade
- tip portion
- 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.)
- Pending
Links
- 238000009434 installation Methods 0.000 claims 1
- 230000002411 adverse Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000007664 blowing Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007115 recruitment Effects 0.000 description 1
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- Hydraulic Turbines (AREA)
Abstract
The aircraft wing installed with impeller at its end can convert part of vortex energy at wing end into dynamic energy of impeller to weaken the vortex strength, reduce drag force, increase lift force and improve the aircraft performance. Said impeller is comprised of blades and axle.
Description
The present invention is a kind of aircraft wing that impeller is installed in wing tip portion.Belong to the aeronautical technology class.
Now aircraft is when flight, because the pressure of wing lower surface is greater than the pressure of upper surface of the airfoil, and forms tip vortex.The existence of this tip vortex can make lifting force of wings reduce, and resistance increases, and 1ift-drag ratio reduces, and the efficient of the primary control surface of aircraft is reduced.
The purpose of this invention is to provide a kind of wing that impeller is installed in wing tip portion.Tip vortex is reduced the adverse effect of aircraft, thereby reduce drag coefficient, increase lift coefficient, improve 1ift-drag ratio; The energy of tip vortex can be changed simultaneously into the kinetic energy of the rotation of impeller, be used to drive electrical generator, Hydraulic Pump, or drive other equipment, improve the economy of aircraft flight.
As shown in Figure 1, impeller is made up of blade 1 and paddle shaft 2.Blade 1 is fixed on the paddle shaft, and paddle shaft 2 is installed on the wing 4 by bearing 3.
As shown in Figure 2, impeller can have loam cake 5 and lower cover 6, or only has loam cake 5, or only has lower cover 6.
As shown in Figure 3, can have block 7 at impeller near leading edge of a wing part.
When aircraft flight, because there is difference of pressure in the wing upper and lower surface, can occur around the mobile of wing tip in the tip of wing is eddy current.This tip vortex will blow wheel rotation.Because the part energy of eddy current has been transformed into the kinetic energy of impeller, and has weakened the intensity of eddy current, has reduced the adverse effect of eddy current to aircraft, and the drag coefficient of wing is reduced, lift coefficient increases, and 1ift-drag ratio improves.Can utilize simultaneously the rotational energy of impeller to drive electrical generator, Hydraulic Pump, or other equipment.Improve the economy of rate of energy and aircraft flight.
Be not have the conventional wing of wing tip impeller and the data comparable situation that the embodiment of the invention is tested in the low speed wind tunnel blowing below.Impeller blade quantity in the embodiment of the invention is 3,120 ° at interval in blade, and blade is not with and is reversed, and impeller is not with upper and lower cover and block.
K0 ° 0.0823 0.1933 2.30 0.0723 0.1833 2.55 10.9%2 ° 0.0823 0.4167 5.05 0.0723 0.4167 5.75 13.9%4 ° 0.0323 0.6500 7.90 0.0733 0.6667 9.10 15.2%6 ° 0.0843 0.9500 10.80 0.0850 0.9667 11.35 5.1%3 ° 0.0953 1.2033 12.65 0.0867 1.1733 13.50 6.7%10 ° 0.1033 1.3667 13.20 0.0967 1.3333 13.75 4.2%12 ° 0.1133 1.3500 11.90 0.1120 1.3733 12.25 3.0%14 ° 0.1233 1.3250 10.70 0.1243 1.3500 10.85 1.4%16 ° 0.1370 1.3250 8.95 0.1320 1.3167 9.95 1.0%18 ° 0.1477 1.3167 8.90 0.1386 1.3083 9.40 5.6%20 ° 0.1583 1.3333 8.40 0.1500 1.3333 8.85 5.3% of conventional wing embodiment of the invention α Cx Cy K Cx Cy K Δs
α-angle of attack
Cx-drag coefficient
Cy-lift coefficient
K-1ift-drag ratio
Δ K-1ift-drag ratio recruitment
Conclusion: the present invention can make the maximum lift coefficient of aircraft improve, and drag coefficient on average reduces by 6%, and 1ift-drag ratio is maximum to improve 15.2%.
Claims (4)
1, a kind of aircraft wing at wing tip portion installation impeller, impeller is made up of blade 1 and paddle shaft 2, and blade 1 is fixed on the paddle shaft 2, and paddle shaft 2 is installed on the wing 4 by bearing 3.
2, a kind of aircraft wing of impeller being installed in wing tip portion according to claim 1 is characterized in that blade 1 is twist mode or is non-twist mode.
3, a kind of aircraft wing of impeller being installed in wing tip portion of asking according to claim 1 is characterized in that impeller can have loam cake 5 and lower cover 6, or only has loam cake 5, or only has lower cover 6.
4, a kind of aircraft wing of impeller being installed in wing tip portion according to claim 1 is characterized in that can being with block 7 at impeller near leading edge of a wing part.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 94107374 CN1114944A (en) | 1994-07-12 | 1994-07-12 | Aircraft wing installed impeller at wing end |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 94107374 CN1114944A (en) | 1994-07-12 | 1994-07-12 | Aircraft wing installed impeller at wing end |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1114944A true CN1114944A (en) | 1996-01-17 |
Family
ID=5032992
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 94107374 Pending CN1114944A (en) | 1994-07-12 | 1994-07-12 | Aircraft wing installed impeller at wing end |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1114944A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101535125B (en) * | 2006-09-15 | 2013-06-19 | 空中客车德国运营有限责任公司 | Aerodynamic body and carrier wing comprising an aerodynamic body, actuating drive control module, computer, computer program, and method for influencing post-turbulences |
| CN104787305A (en) * | 2015-05-08 | 2015-07-22 | 王志成 | Aircraft with wind ball driven wind wheels at wing leading edges |
| CN104773282B (en) * | 2015-05-08 | 2018-07-13 | 湖南湘晨飞机工业有限公司 | A kind of aircraft of the leading edge of a wing equipped with wind ball driving wind wheel |
| CN113226920A (en) * | 2019-01-31 | 2021-08-06 | 三菱重工业株式会社 | Fluid adjusting device and aircraft |
| RU2758939C1 (en) * | 2021-02-16 | 2021-11-03 | Федеральное государственное казенное военное образовательное учреждение высшего образования "Краснодарское высшее военное авиационное училище летчиков имени Героя Советского Союза А.К. Серова" | Aircraft with wing and horizontal tail |
-
1994
- 1994-07-12 CN CN 94107374 patent/CN1114944A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101535125B (en) * | 2006-09-15 | 2013-06-19 | 空中客车德国运营有限责任公司 | Aerodynamic body and carrier wing comprising an aerodynamic body, actuating drive control module, computer, computer program, and method for influencing post-turbulences |
| CN104787305A (en) * | 2015-05-08 | 2015-07-22 | 王志成 | Aircraft with wind ball driven wind wheels at wing leading edges |
| CN104773282B (en) * | 2015-05-08 | 2018-07-13 | 湖南湘晨飞机工业有限公司 | A kind of aircraft of the leading edge of a wing equipped with wind ball driving wind wheel |
| CN104787305B (en) * | 2015-05-08 | 2018-07-13 | 湖南湘晨飞机工业有限公司 | A kind of aircraft of the leading edge of a wing with wind ball driving wind wheel |
| CN113226920A (en) * | 2019-01-31 | 2021-08-06 | 三菱重工业株式会社 | Fluid adjusting device and aircraft |
| RU2758939C1 (en) * | 2021-02-16 | 2021-11-03 | Федеральное государственное казенное военное образовательное учреждение высшего образования "Краснодарское высшее военное авиационное училище летчиков имени Героя Советского Союза А.К. Серова" | Aircraft with wing and horizontal tail |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C01 | Deemed withdrawal of patent application (patent law 1993) | ||
| WD01 | Invention patent application deemed withdrawn after publication |