CN102001440B - Multi-stage powerful fan and vertical takeoff and landing aircraft - Google Patents
Multi-stage powerful fan and vertical takeoff and landing aircraft Download PDFInfo
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- CN102001440B CN102001440B CN 201010535803 CN201010535803A CN102001440B CN 102001440 B CN102001440 B CN 102001440B CN 201010535803 CN201010535803 CN 201010535803 CN 201010535803 A CN201010535803 A CN 201010535803A CN 102001440 B CN102001440 B CN 102001440B
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Abstract
The invention relates to a multi-stage powerful fan and a vertical takeoff and landing aircraft. The multi-stage powerful fan provided by the invention is composed of multiple stages of concentric fan rings which extend from the center to the outside, wherein a gear ring is arranged on the outer rack ring of each stage of fan ring in a rotating manner, a plurality of fan blades use the common extension center as the center of rotation and are arranged on the gear ring uniformly and radially; and the gear ring is a follower which is in mesh transmission with a jugged part which transmits the same rotation power. The technical scheme of the invention realizes the technical aim of increasing the wind power conversion efficiency of the entire fan and has wide range of application. The vertical takeoff and landing aircraft provided by the invention utilizes the powerful lifting force generated by the multi-stage powerful fan for driving, thus the vertical takeoff and landing of the aircraft can be realized; and the multi-stage powerful fan has simple structure and light weight, can be used as a part of the airfoil surface and can not affect the normal flight of the aircraft.
Description
Technical field
What patent application of the present invention related to is the aircraft of the fan realization vertical takeoff and landing after fan technological improvement and the application enhancements.
Background technology
Make can only horizontal running take off aircraft possess desirable vertical takeoff and landing function, be the maximum dreams of people after having helicopter and aircraft.But the aircraft of the previous vertical takeoff and landing that occurs comparatively typically has Harrier and Muscovite refined gram 38/41 aircraft model that comes from Britain.Britain's Harrier adopts special-purpose jet engine and turret nozzle structure, and what Muscovite refined gram 38/41 adopted is special-purpose lift jet engine.The jet work of high engine speeds, resisted the gravity of aircraft by jet thrust and realize vertical takeoff and landing, this type of aircraft faces the subject matter that load carrying ability deficiency, combat radius are too short, structure is comparatively complicated, safety performance is low, overcome aircraft deadweight and static inertia thereof and make that aircraft is outstanding to fly, need the strong power h type engine h, be great amount of fuel oil consumption thereupon, also be difficult to satisfy the rapidity requirement that takes off vertically in actual applications; Aircraft will be expected the powerful power that oppositely raises, and its driving engine just needs to produce the high speed jet air-flow, produces very noisy therefrom, the high temperature gas flow surrounding environment of seriously ablating of ejection, make the landing environment be subjected to very big restriction, the feedback air-flow also can influence engine operation, and the safety of aircraft is difficult to guarantee; Heavy jet engine becomes one of burden that aircraft can't neglect.So utilize the jet power mode to allow aircraft realize vertical takeoff and landing, this technological means faces the replacement of improvement technology.
With respect to sparrow hawk formula and the Muscovite refined gram of Britain, U.S. F-35B aircraft presents certain progress technically.But its vertical power system comprises the sustainer, main engine of one group of lift fan and a jet pipe vertical duction and constitutes jointly.Lift fan is arranged in the enclosure space of flight cockpit rear, and top, space arranges automatic clamshell doors, in the vertical lift process, the sustainer, main engine spout changes down for 90 °, with the lift fan co-operation, about 16 tons of both comprehensive vertical uplift power can guarantee 14 tons of aircraft vertical lifts of gross weight.Lift fan is exactly the wing of an original place rotation, produces lift with the air interaction in high speed rotating, and when lift surpassed the aircraft own wt, aircraft was just rised sheer from level ground, vertical takeoff and landing.Lift fan and air useful effect face are more big, and lift is also more big.Existing fan drive shaft is positioned at fan center, just more big the closer to fan edge line speed, the dynaflow conversion efficiency is also more high, more close to fan center, linear velocity is just more little, the dynaflow conversion efficiency is also more low, is subjected to the influence of factors such as product processing and flabellum quantity again, and the real work efficient of fan can be lower.Because the ascending fluid under power that lift fan produces, just must adopt other additional technological means, be the vertical takeoff and landing that the technical scheme of the jet common combination of tail pipe is finished aircraft, this just in the U.S. F-35B aircraft by the major cause of replenishing of jet power as vertical takeoff and landing power.There is ineffective technical matters in existing fan self just, and the vertical takeoff and landing effect that causes arranging the aircraft of this lift fan can't compare favourably with rolling start.
Summary of the invention
Dynaflow conversion efficiency when the goal of the invention of patent application of the present invention is to improve fan work, a kind of multiple stage high-power fan that improves the dynaflow conversion efficiency is provided, but a kind of vertical take-off and landing aircraft (VTOL aircraft) that multiple stage high-power fan of the present invention is realized the good vertical takeoff and landing performance of using also is provided simultaneously.
The multiple stage high-power fan technical scheme that patent application of the present invention provides, its content is: a kind of multiple stage high-power fan, constituted from the abducent concentric fan ring of central authorities by multistage, the outer bobbin of every grade of fan ring rotates and is provided with gear ring, be center of turn, be arranged on the gear ring, be the homogeneous radiation shape and be provided with some electric fans with the common extension center of circle, gear ring is driven member and the tooth components engaged transmission of transmitting same rotational power, and bobbin and tie-beam constitute the fixed frame that supports this high-power fan jointly outside each road.
In above-mentioned overall technical architecture, the flabellum of described fan rings at different levels, its rotation windward side to leeward side is the wedge shape by following flat epirelief and protuberance gradually closing, and according to fluid mechanics principle, this cross section shape flabellum can produce more powerful fluid force.
In above-mentioned overall technical architecture, for realizing hydrokinetic accurate adjustment by the common change to each flabellum corner, each flabellum rotates through the axis of rotation and is arranged on the gear ring, and flabellum corner driving ring endwisely slips and is arranged on the gear ring, and the flabellum eccentric shaft is hinged to be arranged on the flabellum corner driving ring.
The multiple stage high-power fan that technique scheme provides, composite construction by windy fan ring replaces present integrated fan, by the tooth components of same rotational power and the gear ring engaged transmission of fan rings at different levels, namely drive fan rings at different levels, the excircle of fan rings at different levels is all rotated under the driving of same linear velocity or required linear velocity, then each fan ring zone from the inside to the outside produces basic identical or required dynaflow, this is greatly improved with regard to the conversion efficiency that makes whole fan, the conversion efficiency of gentle breeze fan ring can reach 77.8%, and is then higher more than the level Four.The multiple stage high-power fan application of the technical program is very extensive, as eddy current jet engine fan, also can be used as the technical application fan, and especially the technical application fan of technical parameter maximization provides the improved type substitute products.In addition, the external toothing type of drive of this multiple stage high-power fan can directly drive transmission by electrical motor or engine output shaft, has saved the change-speed box composition, and then weight is lighter, integral body is lighter and handier.
Patent application of the present invention also provides but above-mentioned multiple stage high-power fan is applied to aircraft, makes existing aircraft have the technical scheme of the vertical take-off and landing aircraft (VTOL aircraft) of good vertical landing ability.The content of the technical program is: but a kind of vertical take-off and landing aircraft (VTOL aircraft), and install above-mentioned multiple stage high-power fan be set at the assembly opening place at airframe balance center of gravity place.
But in above-mentioned basis vertical take-off and landing aircraft (VTOL aircraft) technical scheme, in the assembly opening of the symmetry position of aircraft both sides wing above-mentioned multiple stage high-power fan is installed all, the contrarotation each other of symmetrical both sides multiple stage high-power fan is so that be easy to adjust the aircraft flight balance.
Motive effect of fluid just because of fan is greatly enhanced, thereby is applied to aircraft, becomes aircraft vertical takeoff and landing engine installation, makes aircraft possess the vertical takeoff and landing ability to have created engineering factor for it.But the vertical take-off and landing aircraft (VTOL aircraft) technical scheme that patent application of the present invention provides, the powerful lift that utilizes the multiple stage high-power fan to produce drives the vertical takeoff and landing that realizes aircraft, its structure constitutes simple, in light weight, and can form complete covering of the fan and constitute the part of aerofoil surface, can the normal flight of aircraft not exerted an influence, and its weight is light, lift conversion efficiency height, is easy to reach the technical requirements of vertical takeoff and landing, be directly or indirect oil consumption all very low.
Description of drawings
Fig. 1 is the unitary construction figure of this multiple stage high-power fan flabellum deployed condition sealing wafter
Fig. 2 is the shaft side figure of this multiple stage high-power fan flabellum deflection state
Fig. 3 is the general assembly shaft side figure of this multiple stage high-power fan
Fig. 4 is flabellum end construction figure
Fig. 5 is the shaft side figure of each grade fan ring
Fig. 6 is that each grade fan ring constitutes block diagram
Fig. 7 is that the actual product of this multiple stage high-power fan is used the general assembly block diagram
Fig. 8 is that Fig. 7 removes the three-dimensional structure diagram that connects crossbeam
But Fig. 9 and Figure 10 are respectively the example structure figure of vertical take-off and landing aircraft (VTOL aircraft).
The specific embodiment
Multiple stage high-power fan of the present invention, its specific implementation structure as shown in drawings, it is by two-stage, three grades or more multistage constituting from the abducent concentric fan ring of central authorities, present embodiment has adopted level Four fan ring 41,42,43,44 structure constitutes, be example with the fan ring 42 of one-level wherein, every grade of gear ring 1 bobbin 3 outside rolling bearing and corresponding fan ring rotates assembling setting, be arranged on the gear ring 1, be that center of turn is the homogeneous radiation shape to circumference and is provided with some electric fans 2 with the common central center of circle, gear ring 1 is as driven member and tooth components 4 engaged transmission of transmitting same rotational power, drive the flabellum rotary work of its fan ring, as shown in Figure 3, bobbin 3 all is fixed on the connection crossbeam 7 on top outside each road, constitutes the fixed mount of whole high-power fan.Fan rings at different levels can also adopt interior bobbin, outer bobbin and in, all flabellums at the corresponding levels are set between the outer bobbin to be constituted, but such structure structure arranges the structure slightly complicated than the single outer bobbin shown in the figure, and be by the single advantage that the structural form of flabellum is set of outer bobbin, when whole fan work, gear ring and outer bobbin only make and bear the centrifugal pressure that brings in the flabellum rotation, so mechanism's functional reliability is higher, and in, outer bobbin arranges the version of flabellum jointly, the powerful pulling force that the flabellum rotating centrifugal that interior bobbin bears brings, therefore mechanism's safety reduces.In this enforcement structure, tooth components 4 is the quadrant gears with gear ring 1 engaged transmission, tooth components 4 equal keys are fixed on axle drive shaft 5 and the corresponding position of gear rings at different levels, it is in place that axle drive shaft 5 is erected at the radius institute of whole fan, drive each grade fan petticoat by the Power Drive Unit output shaft, each grade tooth components 4 on the axle drive shaft 5 can be identical, with identical rotating speed drive fan ring, makes the drive wire speed of each grade fan ring identical; The working speed of fan rings at different levels also can design the transmission amount of tooth components 4 at different levels and corresponding gear ring 1 according to the actual techniques demand, and the alerting ability of its technical design is higher.For the technological improvement type product as universal fan, the fan blade angles of this fan is can stationary structure by technical design, its flabellum cross section is designed by producing the maximum quantity of wind mode, but the fan for special applications, as the following use as the airplane ascensional force fan that will narrate, just need by take off vertically or the vertical landing requirement by to the change of each flabellum corner, accurately adjust the dynaflow that produces by technical requirements.For this reason, flabellum 2 is arranged on the gear ring 1 through the axis of rotation 6, flabellum corner driving ring 9 endwisely slips and is arranged on the gear ring 1, flabellum 2 is corresponding to being provided with the drive link 8 that changes the flabellum angle of inclination between gear ring 1 one ends and the flabellum corner driving ring 9, drive link 8 is provided with slideway, flabellum corner driving ring 9 is slidingly arranged in this slideway with the swivel pin of drive link 8, or flabellum 2 is assemblied in the eccentric shaft of flabellum corner driving ring 9 corresponding to gear ring 1 one end settings, this eccentric shaft 10 rotates in the end guiding of flabellum corner driving ring 9 and is arranged in the slideway of flabellum corner driving ring 9, or this eccentric shaft is arranged in the slideway of flabellum end face in the rotation of flabellum 2 one ends guiding, through hydraulic pressure or motorized motions and control flabellum corner driving ring 9 axial internal clearance along gear ring 1, drive each flabellum 2 and produce deflection, obtain required dynaflow by technical requirements, especially in the time of on being applied to aircraft, be used for adjusting required lift value, if each flabellum 2 reverts to original position when becoming sealing covering of the fan shown in Figure 1, be more conducive to that aircraft is flat to fly.In order to make each fan ring can produce balanced lift power, the working area of fan rings at different levels is equated, determine that according to this by the shared entire radius value of fan rings at different levels, the fan ring width at close center is greater than deep fan ring width.According to fluid mechanics principle, if make the interaction force between this multistage high-power fan and the space more powerful, as shown in Figure 4, the rotation windward side M of each sheet flabellum 2 is by the wedge shape that descends flat epirelief and protuberance gradually closing to leeward side N, and the fan that is made of this cross section shape flabellum can produce more powerful fluid force.
But the present patent application also provides above-mentioned multiple stage high-power fan has been installed, made existing aircraft to have the vertical take-off and landing aircraft (VTOL aircraft) of good vertical landing ability, but the fuselage balance center of gravity place in vertical take-off and landing aircraft (VTOL aircraft) arranges multiple stage high-power fan assembly opening, in assembly opening, install described multiple stage high-power fan be set, this multistage high-power fan top set up with each road outside bobbin 3 be fixed as one, constitute some crossbeams 7 that are connected of whole fan frame.As Fig. 9 and shown in Figure 10, multistage high-power fan can also symmetry be arranged at wing position, aircraft both sides, the root position of two wings particularly, the above-mentioned multistage high-power fan of one cover all is installed in the assembly opening of the symmetry position of two wings of aircraft, two cover or the contrarotations each other of the multistage high-power fan of more covers of symmetry both sides are so that keep the aircraft flight balance.A lot of aircraft wings are that fuselage arranges the back partially, after the center of gravity of part aircraft is inclined to one side, for keeping the fuselage balance when the aircraft vertical takeoff and landing, forebody, be preferably in rear cabin or a multistage high-power fan 30,31 is set at the aircraft rear portion, cooperate jointly with rear portion two multiple stage high-power fans and realize the steady vertical takeoff and landing of aircraft.
Claims (8)
1. multiple stage high-power fan, it is characterized in that this fan is made of from the abducent concentric fan ring of central authorities multistage, the outer bobbin of every grade of fan ring rotates and is provided with gear ring, be center of turn, be arranged on the gear ring, be the homogeneous radiation shape and be provided with some electric fans with the common extension center of circle, gear ring is driven member and the tooth components engaged transmission of transmitting same rotational power, and bobbin and tie-beam constitute the fixed frame that supports this high-power fan jointly outside each road.
2. multiple stage high-power fan according to claim 1 is characterized in that the flabellum of fan rings at different levels, and it rotates windward side to leeward side and is by the wedge shape of flat epirelief and protuberance gradually closing down.
3. multiple stage high-power fan according to claim 1 is characterized in that each flabellum is arranged on the gear ring through axis of rotation rotation, and flabellum corner driving ring endwisely slips and is arranged on the gear ring, and the flabellum eccentric shaft is hinged to be arranged on the flabellum corner driving ring.
4. multiple stage high-power fan according to claim 1 is characterized in that the working area of fan rings at different levels equates.
5. multiple stage high-power fan according to claim 1 is characterized in that fan rings at different levels are made of all flabellums of the corresponding levels that arrange between interior bobbin, outer bobbin and the inside and outside bobbin.
6. but the application vertical take-off and landing aircraft (VTOL aircraft) of requirement 1 multiple stage high-power fan of having the right, install the multiple stage high-power fan be set at the assembly opening place that it is characterized in that airframe balance center of gravity place.
7. but vertical take-off and landing aircraft (VTOL aircraft) according to claim 6 is characterized in that the multiple stage high-power fan all being installed, the contrarotation each other of symmetrical both sides multiple stage high-power fan in the assembly opening of symmetry position of aircraft both sides wing.
8. but vertical take-off and landing aircraft (VTOL aircraft) according to claim 7 is characterized in that fuselage rear cabin or aircraft rear portion arrange multistage high-power fan.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010535803 CN102001440B (en) | 2010-11-05 | 2010-11-05 | Multi-stage powerful fan and vertical takeoff and landing aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010535803 CN102001440B (en) | 2010-11-05 | 2010-11-05 | Multi-stage powerful fan and vertical takeoff and landing aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN102001440A CN102001440A (en) | 2011-04-06 |
| CN102001440B true CN102001440B (en) | 2013-07-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN 201010535803 Expired - Fee Related CN102001440B (en) | 2010-11-05 | 2010-11-05 | Multi-stage powerful fan and vertical takeoff and landing aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3116511A1 (en) * | 2020-11-25 | 2022-05-27 | Safran | Propulsion unit comprising two contra-rotating propellers |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ES2644667T3 (en) | 2014-09-17 | 2017-11-29 | Airbus Operations S.L. | Multi-fan motor with improved power transmission |
| GB201813671D0 (en) | 2018-08-22 | 2018-10-03 | Rolls Royce Plc | Turbomachine |
| GB201813674D0 (en) | 2018-08-22 | 2018-10-03 | Rolls Royce Plc | Turbomachine |
| GB201813672D0 (en) | 2018-08-22 | 2018-10-03 | Rolls Royce Plc | Turbomachine |
| GB201813675D0 (en) | 2018-08-22 | 2018-10-03 | Rolls Royce Plc | Turbomachine |
| GB201813670D0 (en) | 2018-08-22 | 2018-10-03 | Rolls Royce Plc | Turbomachine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1231977A (en) * | 1998-04-10 | 1999-10-20 | 佟士俊 | Tube wing type helicopter |
| CN1754145A (en) * | 2003-04-23 | 2006-03-29 | 洛德公司 | Aircraft vehicular propulsion system monitoring device and method |
| CN1762763A (en) * | 2004-10-18 | 2006-04-26 | 李荣德 | Radial type screw propeller |
| CN101380881A (en) * | 2007-09-04 | 2009-03-11 | 刘新广 | Deformable flying device |
| CN101437720A (en) * | 2006-03-24 | 2009-05-20 | 国际航空补给I.A.S.有限公司 | Convertible aircraft |
| RU2381956C1 (en) * | 2008-09-25 | 2010-02-20 | Государственное образовательное учреждение высшего профессионального образования "Воронежский государственный технический университет" | Adjustable propeller |
-
2010
- 2010-11-05 CN CN 201010535803 patent/CN102001440B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1231977A (en) * | 1998-04-10 | 1999-10-20 | 佟士俊 | Tube wing type helicopter |
| CN1754145A (en) * | 2003-04-23 | 2006-03-29 | 洛德公司 | Aircraft vehicular propulsion system monitoring device and method |
| CN1762763A (en) * | 2004-10-18 | 2006-04-26 | 李荣德 | Radial type screw propeller |
| CN101437720A (en) * | 2006-03-24 | 2009-05-20 | 国际航空补给I.A.S.有限公司 | Convertible aircraft |
| CN101380881A (en) * | 2007-09-04 | 2009-03-11 | 刘新广 | Deformable flying device |
| RU2381956C1 (en) * | 2008-09-25 | 2010-02-20 | Государственное образовательное учреждение высшего профессионального образования "Воронежский государственный технический университет" | Adjustable propeller |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3116511A1 (en) * | 2020-11-25 | 2022-05-27 | Safran | Propulsion unit comprising two contra-rotating propellers |
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| CN102001440A (en) | 2011-04-06 |
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