CN102745328A - Bypass with tip eddy-current confinement effect - Google Patents
Bypass with tip eddy-current confinement effect Download PDFInfo
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- CN102745328A CN102745328A CN201210243146XA CN201210243146A CN102745328A CN 102745328 A CN102745328 A CN 102745328A CN 201210243146X A CN201210243146X A CN 201210243146XA CN 201210243146 A CN201210243146 A CN 201210243146A CN 102745328 A CN102745328 A CN 102745328A
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- bypass
- duct
- blade
- current confinement
- confinement effect
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Abstract
The invention belongs to the technical field of an aircraft mechanism, and particularly relates to a bypass with a tip eddy-current confinement effect. The bypass with the tip eddy-current confinement effect comprises a propeller (1) and a bypass (4) and is characterized in that an inner wall of the bypass (4) from the lower part of a plane on which blades (2) of the propeller (1) are formed to a lower lip of the bypass (4) is provided with an annular bulge structure (3). The inner wall of the bypass is provided with the bulge structure which surrounds the bypass, has the tip eddy-current confinement effect, and extends from the lower part of the plane of the blade tips of the propeller (fan) to the lower lip of the bypass, so that the problems that the gap between the blade tips of the propeller can not approach to zero and friction and collision between the blade tip and the bypass can appear if the gap is reduced forcedly are solved, blade tip eddy-current resistance is effectively reduced, and the propelling efficiency of a propeller (fan) system of the bypass is improved. The bypass disclosed by the invention is provided with the bulge structure with the tip eddy-current confinement effect, does not need special processing materials and processing technology, has a simple structure and is easy to realize.
Description
Technical field
The invention belongs to aircraft mechanism technical field, be specifically related to a kind of duct with blade tip eddy current confinement effect.
Background technology
Shrouded propeller (fan) is a kind of fluid propulsion means.When the duct radius is not very big; Dynamic efficiency is high, so the power of making models such as the model of an airplane, model flight vehicle and model ship commonly used, the perhaps power of light-small aircraft, flight car and boat; Perhaps need to quicken air-flow, produce device greater than single screw propeller (fan) power as the grade of ventilating.Shrouded propeller (fan) blade tip and duct inwall should keep certain interval; Make and do not produce friction between screw propeller (fan) and duct inwall; But the existence of blade-tip clearance makes screw propeller (fan) produce the blade tip eddy current, and the blade tip eddy current brings resistance, has reduced the efficient of duct.So in order to improve the propulsion coefficient of shrouded propeller (fan) system, should reduce blade-tip clearance as far as possible, the gap is preferably zero in theory.
The restriction of existing duct structure and material, it is very little to make blade-tip clearance not accomplish, approaches zero very for a short time even accomplish; Blade because off-centre or centrifugal forces affect, rocking in various degree must occur when high speed revolution, this will cause the collision friction of screw propeller (fan) blade tip and duct inwall; Blade tip is reamed, and perhaps the duct inwall is isolated, and causes blade-tip clearance to increase; Perhaps shrouded propeller (fan) thrashing, even because accident appears in high speed revolution.
Because unavoidable appearance is rocked in various degree during the blade high speed revolution, let blade-tip clearance near zero, need be on material or structure seeking breakthrough.Because the improvement of material and processing conditions need be considered cost, present in addition processing conditions is limited, so be difficult to break through.
Utility model " ducted fan blade-tip clearance eddy current confinement structure " is to make an issue of from the duct structure aspects in essence; Make every effort to blade-tip clearance near zero; But be subject to the installation and processing precision; Consider the materials processing cost, the factor in many ways such as rock of blade tip cantilever beam structure still can not reach desirable effect during high speed revolution.Problem just is that this utility model do not avoid the gap of screw propeller (fan) blade tip and duct inwall, even structure is exquisite again, technology is meticulous again, still pays no attention to bad clearance issues.
Summary of the invention
The objective of the invention is: a kind of duct with blade tip eddy current confinement effect is provided, and getting around blade-tip clearance cleverly can not infinitesimal technical barrier, effectively reduces blade tip eddy current energy.
Technical scheme of the present invention is: a kind of duct with blade tip eddy current confinement effect; The inside of duct is equipped with screw propeller, on the inwall of the said duct between under to the following lip of said duct that the blade of said screw propeller forms, is provided with the bulge-structure around shape.
The invention has the beneficial effects as follows: have a blade tip eddy current confinement effect bulge-structure around duct through setting at the duct inwall; Lip under lower edge, screw propeller (fan) blade tip plane to the duct; Avoided screw propeller (fan) blade-tip clearance can not be near zero; Reduce to occur problems such as friction, collision between blade tip and the duct by force, and effectively reduce the blade tip eddy resistance, improve the propulsion coefficient of shrouded propeller (fan) system.Bulge-structure with blade tip eddy current confinement effect does not need special work material, processing technology, and is simple in structure, is easy to realize.
Description of drawings
Fig. 1 is a structural perspective of the present invention;
Fig. 2 is a sectional structure scheme drawing of the present invention;
Fig. 3 is the partial enlarged drawing of bulge-structure of the present invention.
Wherein, 1-screw propeller 2-blade 3-bulge-structure 4-duct.
The specific embodiment
Referring to accompanying drawing 1; A kind of duct with blade tip eddy current confinement effect; The inside of duct 4 is equipped with screw propeller 1, on the inwall of the said duct 4 between under to the following lip of said duct 4 that the blade of said screw propeller 12 forms, is provided with the bulge-structure 3 around shape;
Referring to accompanying drawing 2,3, the quantity of said bulge-structure 3 is one or more; Its cross sectional shape is triangle, parallelogram, trapezoidal, oval, round or other are irregular close-shaped; Perhaps be triangle, parallelogram, trapezoidal, oval, round or other irregular close-shaped stacks.
The distance of the said bulge-structure 3 between the quantity of said bulge-structure 3 is when above, is adjacent is not done concrete qualification.
Said bulge-structure 3 is not limited at the height that duct directly makes progress with respect to said duct 4 inwalls.
In l-G simulation test, define said bulge-structure 3 location parameters for being L (mm) to the distance of screw propeller 1 downstream direction along duct 4 inwall buses, bulge-structure 3 cross sectional shapes are semicircle, defining its radius is characteristic dimension a (mm).
To 5 ducts 4 that condition is identical, define, wherein, screw propeller 1 oar dish radius is 275mm, and the blade-tip clearance of duct 4 inwalls and blade 2 is 3mm, and the gap factor is 1.1%.Other condition sees table 1 for details;
Table 1.
Table 2 is depicted as under same-handed oar 2 pulling force operating modes, and duct 4 different parts generations are along the tabulation of axis direction tension coefficient.Wherein the lift-rising effect is the original No. 1 duct 4 duct pulling force factors of contrast.The numerical simulation conclusion shows under the blade-tip clearance of identical duct 4 inwalls and blade 2, and the duct 4 that has a bulge-structure is compared the duct pulling force factor with original duct 4 and all increased, and can reach 11.09% at most.
Table 2
| The duct numbering | The lip pulling force factor | The diffusing opening pulling force factor | The screw propeller pulling force factor | The duct pulling force factor | Lift-rising effect (%) |
| 1 | 0.3277 | -0.00448 | 0.6767 | 0.32322 | 0 |
| 2 | 0.3525 | -0.007 | 0.6544 | 0.3455 | 6.89 |
| 3 | 0.3412 | -0.00541 | 0.6642 | 0.33579 | 3.89 |
| 4 | 0.3457 | -0.00716 | 0.6614 | 0.33854 | 4.74 |
| 5 | 0.3657 | -0.00661 | 0.6409 | 0.35909 | 11.09 |
Claims (3)
1. duct with blade tip eddy current confinement effect; The inside of duct (4) is equipped with screw propeller (1); It is characterized in that, on the inwall of the said duct (4) between under to the following lip of said duct (4) that the blade (2) of said screw propeller (1) forms, be provided with bulge-structure (3) around shape.
2. a kind of duct with blade tip eddy current confinement effect as claimed in claim 1 is characterized in that the quantity of said bulge-structure (3) is one or more.
3. according to claim 1 or claim 2 a kind of duct with blade tip eddy current confinement effect is characterized in that, the cross sectional shape of said bulge-structure (3) is triangle, parallelogram, trapezoidal, oval, round or other are irregular close-shaped; Perhaps be triangle, parallelogram, trapezoidal, oval, round or other irregular close-shaped stacks.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210243146XA CN102745328A (en) | 2012-07-13 | 2012-07-13 | Bypass with tip eddy-current confinement effect |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210243146XA CN102745328A (en) | 2012-07-13 | 2012-07-13 | Bypass with tip eddy-current confinement effect |
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| CN102745328A true CN102745328A (en) | 2012-10-24 |
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| CN201210243146XA Pending CN102745328A (en) | 2012-07-13 | 2012-07-13 | Bypass with tip eddy-current confinement effect |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106286011A (en) * | 2016-08-11 | 2017-01-04 | 南昌航空大学 | A kind of duct wall and the adjustable ducted fan in blade tip gap |
| CN106477025A (en) * | 2015-09-02 | 2017-03-08 | 中国航空工业第六八研究所 | A kind of small-sized electrically driven (operated) aircraft power propulsion system |
| CN106628120A (en) * | 2016-12-06 | 2017-05-10 | 湖南星思科技有限公司 | Efficient pneumatic duct body |
| CN107249811A (en) * | 2015-02-19 | 2017-10-13 | 三菱日立电力系统株式会社 | Welder, welding method and turbo blade |
| CN107826235A (en) * | 2017-11-30 | 2018-03-23 | 肖华清 | Culvert type thrust turbofan |
| CN108128442A (en) * | 2017-12-22 | 2018-06-08 | 北京正兴弘业科技有限公司 | For the pneumatic rudder ducted fan of vector and control method of vertical take-off and landing drone |
| CN108190020A (en) * | 2018-01-04 | 2018-06-22 | 酷黑科技（北京）有限公司 | Shrouded propeller system and unmanned plane |
| WO2019019161A1 (en) * | 2017-07-28 | 2019-01-31 | 深圳市大疆创新科技有限公司 | Airscrew, power assembly and air vehicle |
| CN109533311A (en) * | 2018-11-16 | 2019-03-29 | 中国直升机设计研究所 | A kind of high-performance ducted fan |
| CN109611208A (en) * | 2018-11-06 | 2019-04-12 | 武汉卓尔无人机制造有限公司 | A method of reducing ducted fan noise |
| CN109630313A (en) * | 2018-11-06 | 2019-04-16 | 武汉卓尔无人机制造有限公司 | A method of improving ducted fan engine pulling force |
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| US20030167741A1 (en) * | 1999-05-21 | 2003-09-11 | Lewis Illingworth | Combined toroidal and cylindrical vortex dust separator |
| CN2646045Y (en) * | 2003-10-24 | 2004-10-06 | 尚光辉 | Culvert fan type screw propeller |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107249811A (en) * | 2015-02-19 | 2017-10-13 | 三菱日立电力系统株式会社 | Welder, welding method and turbo blade |
| CN106477025A (en) * | 2015-09-02 | 2017-03-08 | 中国航空工业第六八研究所 | A kind of small-sized electrically driven (operated) aircraft power propulsion system |
| CN106286011A (en) * | 2016-08-11 | 2017-01-04 | 南昌航空大学 | A kind of duct wall and the adjustable ducted fan in blade tip gap |
| CN106628120B (en) * | 2016-12-06 | 2019-08-27 | 湖南星思科技有限公司 | A kind of efficient aerodynamic duct body |
| CN106628120A (en) * | 2016-12-06 | 2017-05-10 | 湖南星思科技有限公司 | Efficient pneumatic duct body |
| WO2019019161A1 (en) * | 2017-07-28 | 2019-01-31 | 深圳市大疆创新科技有限公司 | Airscrew, power assembly and air vehicle |
| US11364999B2 (en) | 2017-07-28 | 2022-06-21 | SZ DJI Technology Co., Ltd. | Rotor, power assembly and air vehicle |
| CN107826235A (en) * | 2017-11-30 | 2018-03-23 | 肖华清 | Culvert type thrust turbofan |
| CN108128442A (en) * | 2017-12-22 | 2018-06-08 | 北京正兴弘业科技有限公司 | For the pneumatic rudder ducted fan of vector and control method of vertical take-off and landing drone |
| CN108190020A (en) * | 2018-01-04 | 2018-06-22 | 酷黑科技（北京）有限公司 | Shrouded propeller system and unmanned plane |
| CN109630313A (en) * | 2018-11-06 | 2019-04-16 | 武汉卓尔无人机制造有限公司 | A method of improving ducted fan engine pulling force |
| CN109611208A (en) * | 2018-11-06 | 2019-04-12 | 武汉卓尔无人机制造有限公司 | A method of reducing ducted fan noise |
| CN109533311A (en) * | 2018-11-16 | 2019-03-29 | 中国直升机设计研究所 | A kind of high-performance ducted fan |
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Application publication date: 20121024 |