CN108518348B - Model plane axis stream ducted fan design method - Google Patents

Model plane axis stream ducted fan design method Download PDF

Info

Publication number
CN108518348B
CN108518348B CN201810245288.7A CN201810245288A CN108518348B CN 108518348 B CN108518348 B CN 108518348B CN 201810245288 A CN201810245288 A CN 201810245288A CN 108518348 B CN108518348 B CN 108518348B
Authority
CN
China
Prior art keywords
fan
indicate
rotor
design
velocity triangle
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.)
Active
Application number
CN201810245288.7A
Other languages
Chinese (zh)
Other versions
CN108518348A (en
Inventor
李秋实
潘天宇
刘仕杰
鹿哈男
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Chengdu Feiqing Aviation Technology Co.,Ltd.
Original Assignee
Beihang University
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Beihang University filed Critical Beihang University
Priority to CN201810245288.7A priority Critical patent/CN108518348B/en
Publication of CN108518348A publication Critical patent/CN108518348A/en
Application granted granted Critical
Publication of CN108518348B publication Critical patent/CN108518348B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/002—Axial flow fans
    • 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
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • 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
    • 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
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps

Abstract

Present disclose provides a kind of model plane axis stream ducted fan design methods, the following steps are included: flow and stagnation pressure liter of the S1 according to fan, design the inlet velocity triangle of fan propeller and the inlet velocity triangle and discharge velocity triangle of discharge velocity triangle and fan stator；And S2 designs the geometric parameter of rotor and stator according to the inlet velocity triangle and discharge velocity triangle of rotor and the inlet velocity triangle and discharge velocity triangle of stator.

Description

Model plane axis stream ducted fan design method
Technical field
This disclosure relates to a kind of model plane axis stream ducted fan design method.
Background technique
Model plane ducted fan generally uses direct current generator to drive, under the premise of motor exports equal-wattage, using high revolving speed The motor of (up to ten thousand revs/min, corresponding blade tip tangential velocity is in meter per seconds up to a hundred), low torque can reduce the weight of motor Amount improves flight duration to carry more batteries.For this reason, it may be necessary to which the height of the design speed up-regulation of fan and motor is turned Speed matches, this causes the design of fan beyond the scope of application of conventional method.
The conventional design method communicated with duct power fan principle has two classes: Design of Axial Fan method and calming the anger Machine-fan design method.Design of Axial Fan method is suitable for low blade tip tangential velocity (generally below 80m/s), low stagnation pressure The case where rising；Compressor-fan design method is suitable for high blade tip tangential velocity, the higher situation of single-stage pressure ratio.
In order to adapt to the high revolving speed of motor, the design speed of model plane ducted fan is higher, and air-flow needs plus function amount phase To lower, air-flow deflection angle is accordingly smaller, and therefore, the design requirement of model plane ducted fan deviates from the experience area of conventional design Between.To need based on Design of Axial Fan method, compressor-fan design method and ducted fan design method three's phase Logical principle seeks the selecting party of ducted fan design parameter on the basis of lacking enough experience charts, formula guidance Method, so that ducted fan pneumatic efficiency with higher.
Summary of the invention
In order to solve at least one above-mentioned technical problem, present disclose provides a kind of model plane axis stream ducted fan design sides Method.
According to one aspect of the disclosure, model plane axis stream ducted fan design method, comprising the following steps:
S1 designs the inlet velocity triangle and muzzle velocity triangle of fan propeller according to the flow and stagnation pressure liter of fan The inlet velocity triangle and discharge velocity triangle of shape and fan stator；And
S2 is according to the inlet velocity triangle and discharge velocity triangle and fan stator of the step S1 fan propeller obtained Inlet velocity triangle and discharge velocity triangle, design fan propeller and stator geometric parameter.
According at least one embodiment of the disclosure, in step sl, the inlet velocity triangle of fan propeller is obtained And discharge velocity triangle and fan stator inlet velocity triangle and discharge velocity triangle when, using the circular rectors such as non- Rule.
According at least one embodiment of the disclosure, which is that the model plane axis stream ducted fan of small hub ratio is set Meter method reduces the front face area of wheel hub by using the design of small hub ratio, so that the resistance of engine is reduced, it is non-to wait rings Gauge rule is equal plus function amount design.
According at least one embodiment of the disclosure, in step S1, pass through the radial equilibrium differential equation of rotor The axial velocity profile of rotor outlet, by the radial equilibrium differential equation of Integration Solving rotor,
The radial equilibrium differential equation such as following formula 1:
Integral expression such as following formula 2:
Wherein, LuIndicate wheel rim function, LfIndicate that flow resistance function, r indicate radius, cuIndicate rotor outlet air-flow tangential velocity with The difference of rotor inlet air-flow tangential velocity, caIndicate rotor outlet air-flow axial velocity, d indicates that wheel hub ratio, U indicate that blade is tangential Speed, C indicate integral constant item；It is given to wait cuThe regularity of distribution, and wait LfRadial distribution.
According at least one embodiment of the disclosure, integral constant item C passes through the mean radius r of fanmWith fan Average speed camIt determines, mean radius rmCalculation formula such as formula 3:
Average speed camCalculation formula such as formula 4:
Wherein, R indicates that casing inside radius, D indicate casing interior diameter, qvIndicate volume flow rate, d indicates that wheel hub ratio, π indicate Pi.
According at least one embodiment of the disclosure, pass through the geometric parameter of the step S2 fan propeller obtained and stator Including cascade solidity and the number of blade, wherein the determination of cascade solidity is related to the D factor, the determination of the number of blade and chord of foil Reynolds number It is related.
According at least one embodiment of the disclosure, the pneumatic efficiency of fan is improved by reducing cascade solidity；
Cascade solidity lower limit is controlled by the D factor, the suction surface of fan blade is avoided to separate loss；And
Laminar sublayer separation loss is controlled by chord of foil Reynolds number.
According at least one embodiment of the disclosure, the value of the D factor in fan propeller blade tip section is 0.4 hereinafter, wind The value for fanning the section of the other parts except rotator tip and the D factor in the high corresponding section of each leaf of fan stator is 0.6 or less.
Detailed description of the invention
Attached drawing shows the illustrative embodiments of the disclosure, and it is bright together for explaining the principles of this disclosure, Which includes these attached drawings to provide further understanding of the disclosure, and attached drawing is included in the description and constitutes this Part of specification.
Fig. 1 is the diffusion formula leaf grating rated airflow deflection angle and cascade solidity according at least one embodiment of the disclosure And nominal outlet port flow angle (β2 *) between relation schematic diagram.
Fig. 2 is the low speed leaf grating data according to the fan blade of at least one embodiment of the disclosure in benchmark fluid inlet angle The tail momentum thickness of lower calculating is than the variation schematic diagram with the local diffusion factor.
Fig. 3 is between zero camber fluid inlet angle and cascade solidity and flow inlet angle according at least one embodiment of the disclosure Relation schematic diagram.
Fig. 4 is thick according to the least disadvantage fluid inlet angle camber correction factor and leaf grating of at least one embodiment of the disclosure Relation schematic diagram between degree and flow inlet angle.
Fig. 5 is the relationship between deflecting angle and cascade solidity and flow inlet angle according at least one embodiment of the disclosure Schematic diagram.
Fig. 6 is the deflecting angle camber correction factor and cascade solidity and air inlet according at least one embodiment of the disclosure Relation schematic diagram between angle.
Fig. 7 is the maximum blade thickness according to zero camber least disadvantage fluid inlet angle of at least one embodiment of the disclosure Correction factor change curve.
Fig. 8 is the geometrical model according to the ducted fan of at least one embodiment of the disclosure.
Fig. 9 is the variation according to the stagnation pressure liter of the rotor of at least one embodiment of the disclosure and fan with air flow rate Curve.
Figure 10 is according to the rotor of at least one embodiment of the disclosure and the torque efficiency of fan with air flow rate Change curve.
Specific embodiment
The disclosure is described in further detail with embodiment with reference to the accompanying drawing.It is understood that this place The specific embodiment of description is only used for explaining related content, rather than the restriction to the disclosure.It also should be noted that being Convenient for description, part relevant to the disclosure is illustrated only in attached drawing.
It should be noted that in the absence of conflict, the feature in embodiment and embodiment in the disclosure can To be combined with each other.The disclosure is described in detail below with reference to the accompanying drawings and in conjunction with embodiment.
The design cycle that underload, high-revolving high-efficient duct fan design can not follow conventional lines, by design abundant Empirical value.This makes the selection of high-efficient duct fan design parameter lack foundation.
Cascade solidity is an important parameter in fan design, as shown in Figure 1, can borrow in conventional design cycle Fig. 1 is helped to carry out the selection of cascade solidity τ.But because the design speed of high-efficient duct fan is higher, processing capacity needed for air-flow It is small, therefore lead to the air-flow deflection angle △ β of fan*It is smaller, conventional parameter selection range is deviated from, so cascade solidity is difficult to It is determined by experience chart.
If the design parameter selection of fan is improper, it would be possible to which the pneumatic efficiency for further resulting in design fan reduces.This public affairs It opens in the TWO-DIMENSIONAL CASCADE experimental result and Design of Axial Fan method in integrated use compressor-fan design method Become circular rector design, the design method that can not be followed conventional lines when for high-efficient duct fan design lacks relevant design experience or public affairs Formula instructs and more difficult determining design parameter, the situation for causing the efficiency for designing fan to reduce, and proposes a kind of suitable for small hub The model plane axis stream ducted fan design method of ratio.
Model plane axis stream ducted fan design method, comprising the following steps:
S1 designs the inlet velocity triangle and muzzle velocity triangle of fan propeller according to the flow and stagnation pressure liter of fan The inlet velocity triangle and discharge velocity triangle of shape and fan stator；And
S2 is according to the inlet velocity triangle and discharge velocity triangle and fan stator of the step S1 fan propeller obtained Inlet velocity triangle and discharge velocity triangle, design fan propeller and stator geometric parameter.
In an optional embodiment of the disclosure, can use conventional method, according to the thrust requirements of aircraft with Power consumption limit obtains the flow and stagnation pressure liter of fan.In order to reduce the front face area of wheel hub, reduces engine drag, can use The design form of small hub ratio.For small hub than fan, in the axial velocity for the exit flow for determining botanical origin rotor blade When, add function regular according to the circular rectors such as conventional, the problem for being easy to cause blade root load excessively high.If but to rotor blade using non- Etc. circular rectors rule, specifically, can using etc. add function amount design, then can be to avoid this excessively high problem of blade root load.Therefore, it obtains Take the inlet velocity triangle of fan propeller and the inlet velocity triangle and outlet of discharge velocity triangle and fan stator When speed triangle, can using etc. add function amount design.
In an optional embodiment of the disclosure, in step sl, wait plus function amount design when, will lead to fan propeller The radial distribution of exit flow axial velocity is uneven, so that the inlet velocity triangle of downstream stator is influenced, so needing logical Integration Solving rotor radial balance differential equation is crossed to obtain the axial velocity profile of rotor outlet, is designed for stator.
The radial equilibrium differential equation such as following formula 1:
Integral expression such as following formula 2:
Wherein, LuIndicate wheel rim function, LfIndicate that flow resistance function, r indicate radius, cuIndicate rotor outlet air-flow tangential velocity with The difference of rotor inlet air-flow tangential velocity, caIndicate rotor outlet air-flow axial velocity, d indicates that wheel hub ratio, U indicate that blade is tangential Speed, C indicate integral constant item；It is given to wait cuThe regularity of distribution, and wait LfRadial distribution.
In an optional embodiment of the disclosure, above-mentioned integral constant item C passes through the mean radius r of fanmWith wind The average speed c of fanamIt determines, mean radius rmCalculation formula such as following formula 3:
Average speed camCalculation formula such as following formula 4:
Wherein, R indicates that casing inside radius, D indicate casing interior diameter, qvIndicate volume flow rate, d indicates that wheel hub ratio, π indicate Pi.
Geometric parameter by the step S2 fan propeller obtained and stator includes cascade solidity and the number of blade, wherein leaf The determination of grid consistency is related to the D factor, and the determination of the number of blade is related to chord of foil Reynolds number.
In an optional embodiment of the disclosure, under the higher background of fan design revolving speed, fan integral load Lower, needed for air-flow plus function amount is small.Therefore, the design point (flow and stagnation pressure liter) of fan is fallen in except the section of experience chart, The important design parameter of blade, i.e. cascade solidity, it is difficult to be confirmed by experience chart, and then influence the choosing of subsequent design parameter It selects.The disclosure determines that cascade solidity, chord of foil Reynolds number determine the Strategy for Parameter Selecting of the number of blade using the D factor.Below with reference to The specific embodiment of the strategy is described in detail in attached drawing.
It, can be by experience number when determining the design parameter of Elementary Cascade in an optional embodiment of the disclosure According to (such as NACA65 series), the air-flow angle of associated fan import and the experimental data of blade profile angle, to plan that air-flow deflects. By angle of attack configuration near least disadvantage fluid inlet angle, the pitot loss in TWO-DIMENSIONAL CASCADE flowing can be reduced, to obtain higher Pneumatic efficiency.Chord of foil Reynolds number and the D factor are the key factor of determining fan geometric parameter, at the same be also possible to except the angle of attack it An important factor for outer influence pneumatic efficiency.
The pneumatic efficiency of fan is improved by reducing cascade solidity.Cascade solidity lower limit is controlled by the D factor, avoids fan The suction surface of blade separates loss.Laminar sublayer separation loss is controlled by chord of foil Reynolds number.
In an optional embodiment of the disclosure, aerodynamic loss with chord of foil Reynolds number variation, with blade surface Laminar sublayer local detachment is totally separated related.Ducted fan design when, by chord of foil Reynolds number be selected in a certain lower limit with Upper (such as 1.5e5 or more), can evade aerodynamic loss caused by laminar sublayer separation effect.
The calculation formula of the D factor such as following formula 5:
Wherein, V1Indicating opposite is the air velocity that inferior lobe is discharged into mouth, V2Indicating opposite is the gas velocity of inferior lobe outlet Degree, Δ cuIndicate that leaf outlet and leaf are discharged into the variable quantity of the air-flow tangential velocity of mouth, τ indicates cascade solidity.
The value of the D factor in fan propeller blade tip section is for 0.4 hereinafter, the section of the other parts except fan propeller blade tip And the value of the D factor in the high corresponding section of each leaf of fan stator is 0.6 or less.
In an optional embodiment of the disclosure, in general, from avoiding causing aerodynamic loss to increase because suction surface separates For big angle, the numerical value of the D factor is small, can reduce the risk of suction surface separation, can also reduce aerodynamic loss.Cause And although lesser cascade solidity is selected to can be improved the pneumatic efficiency of fan, too small cascade solidity can cause D because Son increases, and then increases the risk of suction surface separation, this is unfavorable to the whole design of fan.So in the disclosure, turning The D factor in cotyledon point section is not preferably greater than 0.4, the D factor in section corresponding to other sections of rotor and each leaf height of stator It is not preferably greater than 0.6.
In an optional embodiment of the disclosure, usually in a certain range, suitably increase cascade solidity, to D The influence of the factor and chord of foil Reynolds number is advantageous.Big cascade solidity facilitates rotor and stator caused by preventing load excessively high It is lost caused by the suction surface separation loss of blade and laminar flow separation.But cascade solidity is excessive, is not to pneumatic efficiency Benefit.As shown in Fig. 2, leaf grating aerodynamic loss data can use momentum loss thickness ratio (θ*/ c) it measures.Cascade solidity and chord length It is directly proportional.In momentum loss thickness than a timing, the ratio of chord length and momentum loss thickness be it is certain, i.e., chord length is longer, moves Amount loss thickness is bigger, so that aerodynamic loss is more serious.So losing not serious situation caused by separating in blade suction surface Under, cascade solidity as small as possible can be selected, it will help improve the pneumatic efficiency of fan.
The D factor, chord of foil Reynolds number and rotor blade chord length and stator blade chord length correspond to different flow losses machines System needs to comprehensively consider influencing each other for they when designing cascade solidity, need to use in range, choose lesser cascade solidity, To obtain higher pneumatic efficiency.
In an optional embodiment of the disclosure, the fan that is obtained by model plane axis stream ducted fan design methods Master-plan index and design parameter are as shown in table 1:
1 fan master-plan index of table and parameter
According to above-mentioned design objective and design parameter, along 5 sections of leaf high selection, according to above-mentioned equal plus function amount rotor into The design side of mouth speed triangle and discharge velocity triangle and stator inlet velocity triangle and discharge velocity triangle Method；And the selection strategy of above-mentioned cascade solidity and the number of blade, carry out ducted fan design.The rotor import and export speed of acquisition Type radial distribution is as shown in table 2, consistency, the D factor and chord of foil the Reynolds number distribution such as table 3 along 5 sections of rotor leaf high selection Shown (only by taking the design of rotor as an example, the design method of stator is identical).
2 rotor import and export velocity profile radial distribution of table
Consistency, the D factor and the chord of foil Reynolds number radial distribution in each section of 3 rotor of table
Radius (mm) 60 75 90 105 120
Consistency (-) 0.6 0.45 0.4 0.4 0.4
The D factor (-) 0.32 0.30 0.27 0.23 0.2
Chord of foil Reynolds number (1e5) 1.84 1.97 2.38 3.13 3.98
After above-mentioned major parameter determines, according to the low speed CASCADE EXPERIMENT of 10% thick NACA65 Series Blade thickness distribution Data, as shown in Fig. 3, Fig. 4, Fig. 5 and Fig. 6, by " opposite is inlet air flow angle " in table 2 as abscissa (i.e. in Fig. 3-6 Flow inlet angle β1), it successively tables look-up and determines zero camber (least disadvantage) fluid inlet angle i0, least disadvantage fluid inlet angle camber correction factor n, partially Digression δ0And deflecting angle camber correction factor m.Further, " the least disadvantage fluid inlet angle i of zero camber is obtained by Fig. 30" after, By the comprehensive use of Fig. 3 and Fig. 4, camber amendment is carried out, obtains least disadvantage fluid inlet angle when blade camber is not zero.Similarly, will Fig. 5 and Fig. 6 is comprehensive to be used, in least disadvantage fluid inlet angle after camber is corrected, to deflecting angle δ0Also corresponding camber is carried out to repair Just.
The angle of attack i and deviation angle δ of blade are obtained according to following formula.
(wherein,For blade bent angle)
According to NACA65- (A10) other than thickness, can with reference to Fig. 7 correct fluid inlet angle i0。
By table 2 with respect to the angle for being exit flow and axis and with respect to the angle for being inlet air flow and axis, this two The difference of person acquires flow-deviation angle Δ β.By simple operation, obtain defeated needed for blade modeling, modeling software AutoBlade Enter parameter: half bent angle δ of blade, leaf chord length c and established angle γ.
In an optional embodiment of the disclosure, the radial distribution of above-mentioned parameter is as shown in table 4.
The modeling of table 4, modeling software AutoBlade input parameter radial distribution
Radius (mm) 60 75 90 105 120
Established angle (deg) 45.16 50.51 54.10 56.79 58.19
Chord length (mm) 32.31 30.29 32.31 37.70 43.08
Half bent angle of blade (deg) 4.04 6.74 10.91 13.13 18.17
Parameter each in table 4 is inputted into AutoBlade, obtains the geometrical model of blade, as shown in Figure 8.It is soft with grid drawing Part AutoGrid5 generates the grid calculated for numerical value.Then ducted fan is counted using commercialization numerical value software for calculation CFX Value simulation.It is illustrated in figure 8 geometrical model of the small hub than ducted fan, including rotor (such as 7 blades) and stator (such as 6 blades).
In an optional embodiment of the disclosure, obtained to be verified model plane axis stream ducted fan design method Fan pneumatic efficiency, the flow-pressure for drawing fan propeller and the whole grade of fan rises curve, i.e., the stagnation pressure of rotor and fan rise with The change curve of air flow rate, as shown in Figure 9.Draw flow-torque efficiency curve, i.e. rotor and wind of rotor and the whole grade of fan The torque efficiency of fan with air flow rate change curve, as shown in Figure 10.By Fig. 9 and Figure 10 it is found that the stagnation pressure of rotor rises with stream The changing rule of amount is consistent with fan, and the torque efficiency of rotor is consistent with fan with the changing rule of flow.And in design point Near, rotor and the torque efficiency of the whole grade of fan peak, and the torque efficiency of rotor reaches 95%, the whole grade of fan Torque efficiency nearly 92.5%, this also demonstrates the efficient of the model plane axis stream ducted fan design method of the disclosure.
In the disclosure, the deficiency of ducted fan conventional design process is avoided, TWO-DIMENSIONAL CASCADE experiment is used for reference, plans gas Flow and obtain the design parameter of fan.The ginseng such as cascade solidity, number of blade of fan is determined by chord of foil Reynolds number and the D factor etc. Several layout strategies reduces pitot loss of the air-flow in TWO-DIMENSIONAL CASCADE flowing.The boat obtained by the design method of the disclosure Mold shaft stream ducted fan is also equipped with higher pneumatic efficiency on the basis of keeping underload, high revolving speed feature.
It will be understood by those of skill in the art that above embodiment is used for the purpose of clearly demonstrating the disclosure, and simultaneously Non- be defined to the scope of the present disclosure.For those skilled in the art, may be used also on the basis of disclosed above To make other variations or modification, and these variations or modification are still in the scope of the present disclosure.

Claims (7)

1. a kind of model plane axis stream ducted fan design method, which comprises the following steps:
S1 designs the inlet velocity triangle and discharge velocity triangle of fan propeller according to the flow and stagnation pressure liter of fan, and The inlet velocity triangle and discharge velocity triangle of fan stator；And
S2 is according to the inlet velocity triangle and discharge velocity triangle of the rotor and the inlet velocity triangle of the stator And discharge velocity triangle, design the geometric parameter of the rotor and the stator；
In step S1, by the axial velocity profile of the radial equilibrium differential equation rotor outlet of rotor, asked by integral The radial equilibrium differential equation is solved,
The radial equilibrium differential equation such as following formula 1:
Integral expression such as following formula 2:
Wherein, LuIndicate wheel rim function, LfIndicate that flow resistance function, r indicate radius, cuIndicate rotor outlet air-flow tangential velocity and rotor The difference of inlet air flow tangential velocity, caIndicate rotor outlet air-flow axial velocity, d indicates that wheel hub ratio, U indicate that blade is tangentially fast Degree, C indicate integral constant item；It is given to wait cuThe regularity of distribution, and wait LfRadial distribution.
2. design method according to claim 1, which is characterized in that obtain the inlet velocity three of the rotor as described in step S1 When the inlet velocity triangle and discharge velocity triangle of angular and discharge velocity triangle and the stator, using non-etc. Circular rector rule.
3. design method according to claim 2, which is characterized in that the design method is the model plane axis stream of small hub ratio Ducted fan design method reduces the front face area of wheel hub by using the design of small hub ratio, to reduce engine Resistance, the circular rectors rule such as non-are equal plus function amount design.
4. design method according to claim 1, which is characterized in that the integral constant item C passes through average the half of fan Diameter rmWith the average speed c of fanamIt determines, the mean radius rmCalculation formula such as following formula 3:
The average speed camCalculation formula such as following formula 4:
Wherein, R indicates that casing inside radius, D indicate casing interior diameter, qvIndicate volume flow rate, d indicates that wheel hub ratio, π indicate circumference Rate.
5. design method according to any one of claim 1 to 4, which is characterized in that geometric parameter packet described in step S2 Include cascade solidity and the number of blade, wherein the determination of the cascade solidity is related to the D factor, the determination of the number of blade and chord of foil Reynolds number is related.
6. design method according to claim 5, which is characterized in that improve the gas of fan by reducing the cascade solidity Efficiency of movement；
The cascade solidity lower limit is controlled by the D factor, the suction surface of fan blade is avoided to separate loss；And
Laminar sublayer separation loss is controlled by the chord of foil Reynolds number.
7. design method according to claim 5, which is characterized in that the value of the D factor in fan propeller blade tip section For 0.4 hereinafter, the D in the section of the other parts except fan propeller blade tip and the high corresponding section of each leaf of fan stator because The value of son is 0.6 or less.
CN201810245288.7A 2018-03-23 2018-03-23 Model plane axis stream ducted fan design method Active CN108518348B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201810245288.7A CN108518348B (en) 2018-03-23 2018-03-23 Model plane axis stream ducted fan design method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201810245288.7A CN108518348B (en) 2018-03-23 2018-03-23 Model plane axis stream ducted fan design method

Publications (2)

Publication Number Publication Date
CN108518348A CN108518348A (en) 2018-09-11
CN108518348B true CN108518348B (en) 2019-07-30

Family

ID=63434146

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201810245288.7A Active CN108518348B (en) 2018-03-23 2018-03-23 Model plane axis stream ducted fan design method

Country Status (1)

Country Link
CN (1) CN108518348B (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110162863B (en) * 2019-05-15 2021-07-13 北京玮航科技有限公司 Thermal coupling design method of electric ducted fan

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101092970A (en) * 2007-07-23 2007-12-26 北京航空航天大学 New type single stage transonic axial fan
CN103195757B (en) * 2013-04-25 2015-07-22 哈尔滨工业大学 Pneumatic designing method of counter rotating compressor combining pumping of boundary layer
CN107269583B (en) * 2017-07-21 2019-04-12 哈尔滨工业大学 A kind of super or transonic speed axial fan designs method based on high-order moment

Also Published As

Publication number Publication date
CN108518348A (en) 2018-09-11

Similar Documents

Publication Publication Date Title
CA1233146A (en) Multi stage centrifugal impeller
US4653976A (en) Method of compressing a fluid flow in a multi stage centrifugal impeller
US20080038114A1 (en) Airfoil diffuser for a centrifugal compressor
CN106640757B (en) A kind of multi-wing centrifugal fan and its packet design method
CN105358836B (en) Tube-axial fan
CN107061321B (en) Using the compressor of the variable asymmetric vaned diffuser of established angle and consistency coupling
CN103195757B (en) Pneumatic designing method of counter rotating compressor combining pumping of boundary layer
CN104895841B (en) Rectifier, flow passage structure, combined compressor, aero gas turbine engine
CN111859651A (en) Method for optimizing power generation performance of wind turbine generator set under low air density
CN108644152A (en) Diffuser twisted blade and design method, diffuser and centrifugation/inclined flow air compressor
CN108829970A (en) Axial fan blade optimum design method and optimization system based on vortex dynamics
CN103244459A (en) Aerodynamic design method of subsonic adsorption type axial compressor
CN106762747A (en) Using the centrifugal compressor of the highly asymmetric vaned diffuser of circumferential variable-vane
CN107061368A (en) Using the centrifugal compressor of the circumferential asymmetric vaned diffuser of variable-vane denseness
CN103925244B (en) A kind of big flow high load axial compressor and fan for 300MW F level heavy duty gas turbines
CN107061329A (en) A kind of axial flow blower
CN109695590A (en) Impeller and the fan for using the impeller
CN105298548B (en) A kind of method for designing of micro fuel engine turbine wheel
CN108518348B (en) Model plane axis stream ducted fan design method
CN107100893A (en) The adjustable centrifugal pump of blade and draught fan impeller
CN109505790B (en) High-load high-through-flow-capacity axial flow fan
CN101363450A (en) Blade wheel structure of multiple wing type centrifugal blower fan
CN112943686A (en) Centrifugal compressor impeller and design method thereof
CN110939601A (en) Turbocharger compressor impeller with high-performance blades
CN104165156B (en) A kind of axial-flow pump impeller method for designing not waiting outlet circulation distribution

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant
TR01 Transfer of patent right
TR01 Transfer of patent right

Effective date of registration: 20201203

Address after: No. 917, floor 9, building 1, No. 666, middle section of Tianfu Avenue, hi tech Zone, Chengdu, Sichuan 610000

Patentee after: Chengdu Feiqing Aviation Technology Co.,Ltd.

Address before: 100191 Haidian District, Xueyuan Road, No. 37,

Patentee before: BEIHANG University