CN110513217A - A kind of unmanned plane ducted fan dynamical system - Google Patents
A kind of unmanned plane ducted fan dynamical system Download PDFInfo
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- CN110513217A CN110513217A CN201910838072.6A CN201910838072A CN110513217A CN 110513217 A CN110513217 A CN 110513217A CN 201910838072 A CN201910838072 A CN 201910838072A CN 110513217 A CN110513217 A CN 110513217A
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- 238000005183 dynamical system Methods 0.000 title claims abstract description 34
- 230000035939 shock Effects 0.000 claims description 3
- 230000003068 static effect Effects 0.000 claims description 3
- 230000005611 electricity Effects 0.000 claims description 2
- 238000009434 installation Methods 0.000 claims 1
- 238000005516 engineering process Methods 0.000 description 10
- 238000010586 diagram Methods 0.000 description 7
- 238000005457 optimization Methods 0.000 description 4
- 239000012530 fluid Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/384—Blades characterised by form
- F04D29/386—Skewed blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/528—Casings; Connections of working fluid for axial pumps especially adapted for liquid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/663—Sound attenuation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to a kind of unmanned plane ducted fan dynamical systems, including head-shield, fan propeller, stator, nose cone, gasket, motor and tail cone；Motor drives fan high speed rotation, and fan sucking air simultaneously does work to it, improves the stagnation pressure of air-flow and increases with speed.After air enters stator, the linear velocity of air-flow is cut off.Air-flow obtains thrust from tail portion high speed discharge.By optimizing blade parameter, overall pressure tatio >=1.08 times, isentropic efficiency >=85%.Present system thrust ratio is big, high-efficient and high reliablity.
Description
Technical field
The present invention relates to ducted fan power technologies to belong to duct wind more particularly to a kind of ducted fan dynamical system
Agitate power technical field.
Background technique
Ducted fan dynamical system drives high-power brushless motor, brushless motor band by lithium power supply or DC power supply
Dynamic fan high speed rotation.Fan sucking air simultaneously does work to it, improves the stagnation pressure of air-flow and increases with speed.Air enters
After stator, the linear velocity of air-flow is cut off.Air-flow obtains thrust from tail portion high speed discharge.Ducted fan dynamical system has efficiency
The features such as height, thrust ratio is big and at low cost, the fields such as unmanned plane and helicopter are had been widely used for as dynamical system, to winged
The performance of row device generates important influence.Existing brushless motor ducted fan generallys use stright wing vane design, and efficiency is lower.Contain
Road fan does not carry out noise-reducing design, and noise is very big.Therefore bigger take-off weight and high-quality unmanned aerial vehicle design are unable to satisfy
Demand.
The rotor of ducted fan, the aerodynamic configuration of stator vane and noise-reducing design are the weights of ducted fan dynamical system design
Want key technology.
The optimization design of the parameters such as geometric modeling, blade quantity, duct diameter and the revolving speed of blade, makes its axis with motor
Power matches, and obtains bigger thrust and higher efficiency is the technical difficult points of ducted fan blade aerodynamic design.Point
The noise source and pressure field for analysing fan inlet and outlet carry out the design of noise reduction objective optimization to the shape and material structure of inlet and outlet runner
It is the technical difficult points of the pneumatic noise-reducing design of fan.Therefore the aerodynamic configuration design of ducted fan and pneumatic noise-reducing design are necessary
Numerical value calculating is carried out by mass computing hydrodynamics numerical simulation software platform and high-performance computer, in conjunction with calculating fluid force
Technology, ground experiment measuring technology, material technology and manufacturing technology etc. could obtain the ducted fan dynamical system haveing excellent performance
System.
Summary of the invention
Technology of the invention solves the problems, such as: overcoming the thrust of existing ducted fan dynamical system insufficient, proposes one kind
High-power ducted fan dynamical system, power >=45kw meet the unmanned plane dynamic design demand of 0.0~0.3 range of Mach number.
The technical solution of the invention is as follows:
A kind of unmanned plane ducted fan dynamical system, including head-shield, fan propeller, stator, nose cone, gasket, motor and tail
Cone；
Fan propeller, nose cone and stator are coaxially installed in cylindric head-shield；Fan propeller is connected with stator, and nose cone is solid
It is scheduled on fan propeller and is rotated synchronously with fan propeller, tail cone is connected to stator rear portion, and motor is arranged in stator interior, is used for
The rotation of driving fan rotor, the gasket for bumper and absorbing shock are arranged between motor and stator；
Rotor blade plunders the aerodynamic configuration of type in the wide string of distorted shape, the chord length of rotor blade along rotor blade radial direction gradually
Become larger, the established angle of rotor blade gradually becomes smaller along the radial direction of rotor blade；Stator vane is in the straight wing aerodynamic configuration of sweepback, stator
The chord length of blade is fixed, and the established angle of stator vane gradually becomes smaller along the radial direction of stator vane.
It further, further include L-shaped irdome, short straight-arm is mounted on stator, and long straight-arm is connected on head-shield, and
Irdome is obturator, and the wire guide being arranged from head-shield to the conducting wire that motor is powered sequentially enters long straight-arm and short straight-arm, finally
It is motor power supply into motor.
Further, head-shield includes rotor hood portion and stator hood portion；Fan propeller respective rotor hood portion,
Stator corresponds to stator hood portion；It is evenly arranged with that diameter is identical, the identical blind hole of depth on the inner wall of rotor hood portion；It is fixed
The back edge of sub- hood portion is 60 ° of zigzags；Multiple strip slots are evenly distributed on tail cone surface.
Further, the quantity of the rotor blade is 3~20, and diameter is 200~500mm, the rotor blade section wing
Type thickness and the ratio of chord length are 0.05~0.2, and the ratio of section camber and chord length is 0.03~0.06.
Further, the quantity of the rotor blade is preferably 16, and diameter is preferably 300mm, the rotor blade section wing
Type thickness and the ratio of chord length are preferably 0.15, and the ratio of section camber and chord length is preferably 0.054.
Further, the chord length and established angle of rotor blade axial direction sectional position specifically:
When the distance between shaft of rotor blade axial direction section and fan propeller is 0, the chord length of the axial cross section position
It is respectively 68.3mm and 73.3 ° with established angle；
When the distance between shaft of rotor blade axial direction section and fan propeller is 0.1R, the string of the axial cross section position
Long and established angle is respectively 71.2mm and 70.2 °, and wherein R is the radius of fan propeller；
When the distance between shaft of rotor blade axial direction section and fan propeller is 0.2R, the string of the axial cross section position
Long and established angle is respectively 72.2mm and 67.8 °；
When the distance between shaft of rotor blade axial direction section and fan propeller is 0.3R, the string of the axial cross section position
Long and established angle is respectively 73.1mm and 65.7 °；
When the distance between shaft of rotor blade axial direction section and fan propeller is 0.4R, the string of the axial cross section position
Long and established angle is respectively 73.5mm and 63.7 °；
When the distance between shaft of rotor blade axial direction section and fan propeller is 0.5R, the string of the axial cross section position
Long and established angle is respectively 75.7mm and 61 °；
When the distance between shaft of rotor blade axial direction section and fan propeller is 0.6R, the string of the axial cross section position
Long and established angle is respectively 79.7mm and 59.2 °；
When the distance between shaft of rotor blade axial direction section and fan propeller is 0.7R, the string of the axial cross section position
Long and established angle is respectively 84.7mm and 57.1；
When the distance between shaft of rotor blade axial direction section and fan propeller is 0.8R, the string of the axial cross section position
Long and established angle is respectively 90.8mm and 54.9 °；
When the distance between shaft of rotor blade axial direction section and fan propeller is 0.9R, the string of the axial cross section position
Long and established angle is respectively 98.1mm and 52.6 °；
When the distance between shaft of rotor blade axial direction section and fan propeller is 1.0R, the string of the axial cross section position
Long and established angle is respectively 106.3mm and 50.6 °.
Further, the stator vane quantity is 20~40, and the ratio of stator vane section profile thickness and chord length is
0.05~0.2, the ratio of section camber and chord length is 0.03~0.06；Stator diameter is 100~200mm.
Further, the stator vane quantity is preferably 30, and the ratio of stator vane section profile thickness and chord length is excellent
It is selected as 0.1, the ratio of section camber and chord length is preferably 0.05；Stator diameter is preferably 171mm.
Further, the chord length and established angle of stator vane axial cross section position specifically:
When the distance between stator vane axial cross section and stator central axis are 0, the chord length and peace of the axial cross section position
Filling angle is respectively 50mm and 110 °；
The distance between stator vane axial cross section and stator central axis be 0.1r when, the chord length of the axial cross section position and
Established angle is respectively 50mm and 109 °, and wherein r is the radius of stator；
The distance between stator vane axial cross section and stator central axis be 0.2r when, the chord length of the axial cross section position and
Established angle is respectively 50mm and 108 °；
The distance between stator vane axial cross section and stator central axis be 0.3r when, the chord length of the axial cross section position and
Established angle is respectively 50mm and 107 °；
The distance between stator vane axial cross section and stator central axis be 0.4r when, the chord length of the axial cross section position and
Established angle is respectively 50mm and 106 °；
The distance between stator vane axial cross section and stator central axis be 0.5r when, the chord length of the axial cross section position and
Established angle is respectively 50mm and 106 °；
The distance between stator vane axial cross section and stator central axis be 0.6r when, the chord length of the axial cross section position and
Established angle is respectively 50mm and 105 °；
The distance between stator vane axial cross section and stator central axis be 0.7r when, the chord length of the axial cross section position and
Established angle is respectively 50mm and 104 °；
The distance between stator vane axial cross section and stator central axis be 0.8r when, the chord length of the axial cross section position and
Established angle is respectively 50mm and 103 °；
The distance between stator vane axial cross section and stator central axis be 0.9r when, the chord length of the axial cross section position and
Established angle is respectively 50mm and 102 °；
The distance between stator vane axial cross section and stator central axis be 1.0r when, the chord length of the axial cross section position and
Established angle is respectively 50mm and 101 °.
Further, the leading-edge sweep angle of stator vane is 15 °~50 °, preferably 45 °.
Further, overall pressure tatio >=1.08 times of unmanned plane ducted fan dynamical system, total temperature ratio >=1.02, isentropic efficiency
>=85%, air flow rate >=6.0kg/s；In fan propeller maximum (top) speed 9000rpm, ground maximum static thrust >=60kg；Electricity
The shaft power of machine is greater than 45kw.
The present invention compared with prior art the advantages of:
(1) present invention by using wide string plunder type fan, high-lift airfoil and inclination stator vane design, using CFD into
Row calculates and the aerodynamic configuration of optimization geometric parameter acquisition blade.It has devised in brushless motor shaft power >=45kw condition
Under, fan grade overall pressure tatio and isentropic efficiency reach maximum, acquisition >=60kg thrust ducted fan dynamical system, isentropic efficiency
>=85%.The thrust of the invention compared to existing electric ducted fan dynamical system has greatly improved.
(2) ducted fan dynamical system of the present invention is applicable in range of Mach numbers 0.0~0.3, can satisfy most low speed
Unmanned plane during flying velocity interval, the propulsion system as unmanned plane have apparent compared with shaft power source airscrew thrust
Advantage.
(3) ducted fan dynamical system of the present invention uses unique honeycomb and broached-tooth design noise reduction, relatively original
Ducted fan can reduce noise 10dB.
Detailed description of the invention
Fig. 1 is one of the scale diagrams of ducted fan dynamical system in the embodiment of the present invention；
Fig. 2 is two of the scale diagrams of ducted fan dynamical system in the embodiment of the present invention；
Fig. 3 is one of ducted fan power system architecture schematic diagram in the embodiment of the present invention；
Fig. 4 is two of ducted fan power system architecture schematic diagram in the embodiment of the present invention；
Fig. 5 is three of ducted fan power system architecture schematic diagram in the embodiment of the present invention；
Fig. 6 is four of ducted fan power system architecture schematic diagram in the embodiment of the present invention；
Fig. 7 is one of the schematic cross-section of fan blade of the present invention；
Fig. 8 is the two of the schematic cross-section of fan blade of the present invention；
Fig. 9 is one of the schematic cross-section of stator vane of the present invention；
Figure 10 is the two of the schematic cross-section of stator vane of the present invention；
Figure 11 is the three of the schematic cross-section of stator vane of the present invention；
Figure 12 is for system of the invention and with power propeller contrast schematic diagram.
Specific embodiment
The present invention proposes efficient one kind, low noise and high thrust unmanned plane ducted fan dynamical system.Utilize calculating fluid
Mechanical technology optimizes the aerodynamic configuration of the blade of ducted fan, obtains thrust >=60kg, isentropic efficiency >=85%
Ducted fan blade.And also the structure of fan inlet and outlet is optimized, propose a kind of honeycomb air intake duct and
The jet pipe and trough of belt tail cone scheme of broached-tooth design noise reduction.Aerodynamic noise of the invention can be reduced compared to the product of same type
10dB。
As shown in figs. 1 to 6, the present invention proposes a kind of unmanned plane ducted fan dynamical system, including head-shield 1, fan propeller
2, stator 3, nose cone 4, gasket 6, motor 7 and tail cone 10；
Fan propeller 2, nose cone 4 and stator 3 are coaxially installed in cylindric head-shield 1；Fan propeller 2 and stator 3 connect,
Nose cone 4 is fixed on fan propeller 2 and rotates synchronously with fan propeller 2, and tail cone 10 is connected to 3 rear portion of stator, and the setting of motor 7 exists
It inside stator 3, is rotated for driving fan rotor 2, the gasket 6 for bumper and absorbing shock is arranged between motor 7 and stator 3；
Rotor blade 8 plunders the aerodynamic configuration of type in the wide string of distorted shape, the radial direction of the chord length of rotor blade 8 along rotor blade 8
It becomes larger, the established angle of rotor blade 8 gradually becomes smaller along the radial direction of rotor blade 8；Stator vane 5 is pneumatically outer in the straight wing of sweepback
The chord length of shape, stator vane 5 is fixed, and the established angle of stator vane 5 gradually becomes smaller along the radial direction of stator vane 5.
Further, dynamical system of the present invention further includes L-shaped irdome 9, and short straight-arm is mounted on stator 3, long straight
Arm is connected on head-shield 1, and irdome 9 is obturator, the wire guide that is arranged from head-shield 1 of conducting wire powered to motor 7 successively into
Enter long straight-arm and short straight-arm, eventually enters into motor 7 as motor power supply.
Further, above-mentioned head-shield 1 includes rotor hood portion and stator hood portion；2 respective rotor head of fan propeller
Cover portion point, the corresponding stator hood portion of stator 3；It is evenly arranged with that diameter is identical, depth is identical on the inner wall of rotor hood portion
Blind hole, honeycomb hole can reduce the low-frequency vibration of noise, from the noise for reducing air intake duct；The back edge of stator hood portion is
Zigzag is crushed the big vortex shedding in jet pipe tail portion by saw tooth profile and is become broken whirlpool, to reduce jet pipe
Noise；Tail cone is evenly distributed with multiple strip slots on 10 surface, and the strip slot by optimization can pneumatically rectify jet pipe
Effect, can also cool down to motor, heat is diffused into air-flow by strip slot, while the gas of the jet pipe also reduced
Flow separation causes thrust.
The important component of the ducted fan of rotor blade directly determines the thrust, efficiency and pressure ratio of entire ducted fan
Etc. performances.The design of fan blade is extremely complex, needs to utilize calculating auxiliary modeling technique, Computational fluid mechanics numerical simulation skill
Art and high performance parallel computation technology etc. could obtain satisfaction design through a large amount of type selectings and numerical simulation calculation and iterating
The scheme of index.
As illustrated in figures 3-6, the quantity of rotor blade 8 is 3~20, and diameter is 200~500mm, 8 section of rotor blade
Profile thickness and the ratio of chord length are 0.05~0.2, and the ratio of section camber and chord length is 0.03~0.06.
The quantity of rotor blade 8 is preferably 16, and diameter is preferably 300mm, 8 section profile thickness of rotor blade and chord length
Ratio be preferably 0.15, the ratio of section camber and chord length is preferably 0.054.
Specifically, the special-shaped rotor blade of distorted shape is cut along axial, it to be used for clearer description abnormity rotor leaf
The configuration of piece, as shown in Fig. 7~8.
The chord length and established angle of 8 axial cross section position of rotor blade specifically:
When the distance between shaft of 8 axial cross section of rotor blade and fan propeller is 0, the chord length of the axial cross section position
It is respectively 68.3mm and 73.3 ° with established angle；
When the distance between shaft of 8 axial cross section of rotor blade and fan propeller is 0.1R, the axial cross section position
Chord length and established angle are respectively 71.2mm and 70.2 °, and wherein R is the radius of fan propeller 2；
When the distance between shaft of 8 axial cross section of rotor blade and fan propeller is 0.2R, the axial cross section position
Chord length and established angle are respectively 72.2mm and 67.8 °；
When the distance between shaft of 8 axial cross section of rotor blade and fan propeller is 0.3R, the axial cross section position
Chord length and established angle are respectively 73.1mm and 65.7 °；
When the distance between shaft of 8 axial cross section of rotor blade and fan propeller is 0.4R, the axial cross section position
Chord length and established angle are respectively 73.5mm and 63.7 °；
When the distance between shaft of 8 axial cross section of rotor blade and fan propeller is 0.5R, the axial cross section position
Chord length and established angle are respectively 75.7mm and 61 °；
When the distance between shaft of 8 axial cross section of rotor blade and fan propeller is 0.6R, the axial cross section position
Chord length and established angle are respectively 79.7mm and 59.2 °；
When the distance between shaft of 8 axial cross section of rotor blade and fan propeller is 0.7R, the axial cross section position
Chord length and established angle are respectively 84.7mm and 57.1；
When the distance between shaft of 8 axial cross section of rotor blade and fan propeller is 0.8R, the axial cross section position
Chord length and established angle are respectively 90.8mm and 54.9 °；
When the distance between shaft of 8 axial cross section of rotor blade and fan propeller is 0.9R, the axial cross section position
Chord length and established angle are respectively 98.1mm and 52.6 °；
When the distance between shaft of 8 axial cross section of rotor blade and fan propeller is 1.0R, the axial cross section position
Chord length and established angle are respectively 106.3mm and 50.6 °.
It does work after fan suction airflow to it, so that stagnation pressure increases 1.01~1.1 times, air velocity is increased to Ma=0.3
~0.8.Air-flow has to pass through stator and eliminates its linear velocity, and ensures that air-flow does not generate the condition of separation in stator boundary layer
Lower edge level sprays flow angle≤5 °, it is desirable that total pressure recovery coefficient >=0.99.Therefore stator design is the pass of ducted fan design
One of key technology.
As shown in Fig. 9~11,5 quantity of stator vane is 20~40, the ratio of stator vane 5 section profile thickness and chord length
It is 0.05~0.2, the ratio of section camber and chord length is 0.03~0.06；3 diameter of stator is 100~200mm.
5 quantity of stator vane is preferably 30, and the ratio of 5 section profile thickness of stator vane and chord length is preferably 0.1,
The ratio of section camber and chord length is preferably 0.05；3 diameter of stator is preferably 171mm.
Specifically, stator vane is cut along axial, for the clearer configuration for describing the stator vane, as Fig. 9~
Shown in 11.
The chord length and established angle of 5 axial cross section position of stator vane specifically:
When the distance between 5 axial cross section of stator vane and stator central axis are 0, the chord length and peace of the axial cross section position
Filling angle is respectively 50mm and 110 °；
When the distance between 5 axial cross section of stator vane and stator central axis are 0.1r, the chord length of the axial cross section position
It is respectively 50mm and 109 ° with established angle, wherein r is the radius of stator 3；
When the distance between 5 axial cross section of stator vane and stator central axis are 0.2r, the chord length of the axial cross section position
It is respectively 50mm and 108 ° with established angle；
When the distance between 5 axial cross section of stator vane and stator central axis are 0.3r, the chord length of the axial cross section position
It is respectively 50mm and 107 ° with established angle；
When the distance between 5 axial cross section of stator vane and stator central axis are 0.4r, the chord length of the axial cross section position
It is respectively 50mm and 106 ° with established angle；
When the distance between 5 axial cross section of stator vane and stator central axis are 0.5r, the chord length of the axial cross section position
It is respectively 50mm and 106 ° with established angle；
When the distance between 5 axial cross section of stator vane and stator central axis are 0.6r, the chord length of the axial cross section position
It is respectively 50mm and 105 ° with established angle；
When the distance between 5 axial cross section of stator vane and stator central axis are 0.7r, the chord length of the axial cross section position
It is respectively 50mm and 104 ° with established angle；
When the distance between 5 axial cross section of stator vane and stator central axis are 0.8r, the chord length of the axial cross section position
It is respectively 50mm and 103 ° with established angle；
When the distance between 5 axial cross section of stator vane and stator central axis are 0.9r, the chord length of the axial cross section position
It is respectively 50mm and 102 ° with established angle；
When the distance between 5 axial cross section of stator vane and stator central axis are 1.0r, the chord length of the axial cross section position
It is respectively 50mm and 101 ° with established angle.
The leading-edge sweep angle of stator vane 5 is 15 °~50 °, preferably 45 °.
Flow angle≤5 ° of the invention, air-flow do not separate in stator boundary layer, total pressure recovery coefficient >=0.99.
Overall pressure tatio >=1.08 times of unmanned plane ducted fan dynamical system of the present invention, total temperature ratio >=1.02, isentropic efficiency >=
85%, air flow rate >=6.0kg/s；In 2 maximum (top) speed 9000rpm of fan propeller, ground maximum static thrust >=60kg；Motor
7 shaft power is greater than 45kw.The present invention is compared with the propeller of equal-wattage, and in Ma >=0.1, thrust has apparent excellent
Gesture, as shown in Figure 12.
Unspecified part of the present invention belongs to common sense well known to those skilled in the art.
Claims (11)
1. a kind of unmanned plane ducted fan dynamical system, it is characterised in that: including head-shield (1), fan propeller (2), stator (3),
Nose cone (4), gasket (6), motor (7) and tail cone (10)；
Fan propeller (2), nose cone (4) and stator (3) are coaxially installed in cylindric head-shield (1)；Fan propeller (2) and stator
(3) it connects, nose cone (4) is fixed on fan propeller (2) and rotates synchronously with fan propeller (2), and tail cone (10) is connected to stator
(3) rear portion, motor (7) setting is internal in stator (3), rotates for driving fan rotor (2), the gasket for bumper and absorbing shock
(6) it is arranged between motor (7) and stator (3)；
Rotor blade (8) plunders the aerodynamic configuration of type in the wide string of distorted shape, the diameter of the chord length of rotor blade (8) along rotor blade (8)
To becoming larger, the established angle of rotor blade (8) gradually becomes smaller along the radial direction of rotor blade (8)；Stator vane (5) is straight in sweepback
The chord length of wing aerodynamic configuration, stator vane (5) is fixed, and the established angle of stator vane (5) gradually becomes along the radial direction of stator vane (5)
It is small.
2. a kind of unmanned plane ducted fan dynamical system according to claim 1, it is characterised in that: further include L-shaped
Irdome (9), short straight-arm are mounted on stator (3), and long straight-arm is connected on head-shield (1), and irdome (9) is obturator, to electricity
The wire guide that the conducting wire of machine (7) power supply is arranged from head-shield (1) sequentially enters long straight-arm and short straight-arm, eventually enters into motor (7)
For motor power supply.
3. a kind of unmanned plane ducted fan dynamical system according to claim 1 or 2, it is characterised in that: head-shield (1) includes
Rotor hood portion and stator hood portion；Fan propeller (2) respective rotor hood portion, the corresponding stator head cover portion of stator (3)
Point；It is evenly arranged with that diameter is identical, the identical blind hole of depth on the inner wall of rotor hood portion；The back edge of stator hood portion
For 60 ° of zigzags；Multiple strip slots are evenly distributed on tail cone (10) surface.
4. a kind of unmanned plane ducted fan dynamical system according to claim 2, it is characterised in that: the rotor blade
(8) quantity is 3~20, and diameter is 200~500mm, and the ratio of rotor blade (8) section profile thickness and chord length is 0.05
~0.2, the ratio of section camber and chord length is 0.03~0.06.
5. a kind of unmanned plane ducted fan dynamical system according to claim 4, it is characterised in that: the rotor blade
(8) quantity is preferably 16, and diameter is preferably 300mm, and the ratio of rotor blade (8) section profile thickness and chord length is preferably
0.15, the ratio of section camber and chord length is preferably 0.054.
6. a kind of unmanned plane ducted fan dynamical system according to claim 4 or 5, it is characterised in that: rotor blade (8)
The chord length and established angle of axial cross section position specifically:
The distance between shaft of rotor blade (8) axial cross section and fan propeller be 0 when, the chord length of the axial cross section position and
Established angle is respectively 68.3mm and 73.3 °；
When the distance between shaft of rotor blade (8) axial cross section and fan propeller is 0.1R, the string of the axial cross section position
Long and established angle is respectively 71.2mm and 70.2 °, and wherein R is the radius of fan propeller (2)；
When the distance between shaft of rotor blade (8) axial cross section and fan propeller is 0.2R, the string of the axial cross section position
Long and established angle is respectively 72.2mm and 67.8 °；
When the distance between shaft of rotor blade (8) axial cross section and fan propeller is 0.3R, the string of the axial cross section position
Long and established angle is respectively 73.1mm and 65.7 °；
When the distance between shaft of rotor blade (8) axial cross section and fan propeller is 0.4R, the string of the axial cross section position
Long and established angle is respectively 73.5mm and 63.7 °；
When the distance between shaft of rotor blade (8) axial cross section and fan propeller is 0.5R, the string of the axial cross section position
Long and established angle is respectively 75.7mm and 61 °；
When the distance between shaft of rotor blade (8) axial cross section and fan propeller is 0.6R, the string of the axial cross section position
Long and established angle is respectively 79.7mm and 59.2 °；
When the distance between shaft of rotor blade (8) axial cross section and fan propeller is 0.7R, the string of the axial cross section position
Long and established angle is respectively 84.7mm and 57.1；
When the distance between shaft of rotor blade (8) axial cross section and fan propeller is 0.8R, the string of the axial cross section position
Long and established angle is respectively 90.8mm and 54.9 °；
When the distance between shaft of rotor blade (8) axial cross section and fan propeller is 0.9R, the string of the axial cross section position
Long and established angle is respectively 98.1mm and 52.6 °；
When the distance between shaft of rotor blade (8) axial cross section and fan propeller is 1.0R, the string of the axial cross section position
Long and established angle is respectively 106.3mm and 50.6 °.
7. a kind of unmanned plane ducted fan dynamical system according to claim 2, it is characterised in that: the stator vane
(5) quantity is 20~40, and the ratio of stator vane (5) section profile thickness and chord length is 0.05~0.2, section camber with
The ratio of chord length is 0.03~0.06；Stator (3) diameter is 100~200mm.
8. a kind of unmanned plane ducted fan dynamical system according to claim 7, it is characterised in that: the stator vane
(5) quantity is preferably 30, and the ratio of stator vane (5) section profile thickness and chord length is preferably 0.1, section camber and string
Long ratio is preferably 0.05；Stator (3) diameter is preferably 171mm.
9. a kind of unmanned plane ducted fan dynamical system according to claim 7 or 8, it is characterised in that: stator vane (5)
The chord length and established angle of axial cross section position specifically:
When stator vane (5) the distance between axial cross section and stator central axis are 0, the chord length and installation of the axial cross section position
Angle is respectively 50mm and 110 °；
Stator vane (5) the distance between axial cross section and stator central axis be 0.1r when, the chord length of the axial cross section position and
Established angle is respectively 50mm and 109 °, and wherein r is the radius of stator (3)；
Stator vane (5) the distance between axial cross section and stator central axis be 0.2r when, the chord length of the axial cross section position and
Established angle is respectively 50mm and 108 °；
Stator vane (5) the distance between axial cross section and stator central axis be 0.3r when, the chord length of the axial cross section position and
Established angle is respectively 50mm and 107 °；
Stator vane (5) the distance between axial cross section and stator central axis be 0.4r when, the chord length of the axial cross section position and
Established angle is respectively 50mm and 106 °；
Stator vane (5) the distance between axial cross section and stator central axis be 0.5r when, the chord length of the axial cross section position and
Established angle is respectively 50mm and 106 °；
Stator vane (5) the distance between axial cross section and stator central axis be 0.6r when, the chord length of the axial cross section position and
Established angle is respectively 50mm and 105 °；
Stator vane (5) the distance between axial cross section and stator central axis be 0.7r when, the chord length of the axial cross section position and
Established angle is respectively 50mm and 104 °；
Stator vane (5) the distance between axial cross section and stator central axis be 0.8r when, the chord length of the axial cross section position and
Established angle is respectively 50mm and 103 °；
Stator vane (5) the distance between axial cross section and stator central axis be 0.9r when, the chord length of the axial cross section position and
Established angle is respectively 50mm and 102 °；
Stator vane (5) the distance between axial cross section and stator central axis be 1.0r when, the chord length of the axial cross section position and
Established angle is respectively 50mm and 101 °.
10. a kind of unmanned plane ducted fan dynamical system according to claim 7 or 8, it is characterised in that: stator vane
(5) leading-edge sweep angle is 15 °~50 °, preferably 45 °.
11. a kind of unmanned plane ducted fan dynamical system according to claim 1 or 2, it is characterised in that: unmanned plane duct
Overall pressure tatio >=1.08 times of fan powering systems, total temperature ratio >=1.02, isentropic efficiency >=85%, air flow rate >=6.0kg/s；In
When fan propeller (2) maximum (top) speed 9000rpm, ground maximum static thrust >=60kg；The shaft power of motor (7) is greater than 45kw.
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| CN201910838072.6A CN110513217B (en) | 2019-09-05 | 2019-09-05 | Unmanned aerial vehicle duct fan driving system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114962326A (en) * | 2021-02-26 | 2022-08-30 | 利尤姆埃飞行器有限责任公司 | Ducted fan engine, arrangement structure and aircraft |
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