CN105677945B - A kind of multi-state propulsive performance optimum design method of composite propeller - Google Patents
A kind of multi-state propulsive performance optimum design method of composite propeller Download PDFInfo
- Publication number
- CN105677945B CN105677945B CN201511009110.5A CN201511009110A CN105677945B CN 105677945 B CN105677945 B CN 105677945B CN 201511009110 A CN201511009110 A CN 201511009110A CN 105677945 B CN105677945 B CN 105677945B
- Authority
- CN
- China
- Prior art keywords
- propeller
- composite
- angle
- pitch
- blade
- 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.)
- Expired - Fee Related
Links
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Engineering & Computer Science (AREA)
- Theoretical Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Pure & Applied Mathematics (AREA)
- Mathematical Optimization (AREA)
- Mathematical Analysis (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- General Engineering & Computer Science (AREA)
- Computational Mathematics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
A kind of multi-state propulsive performance optimum design method of composite propeller, the present invention relates to the multi-state propulsive performance optimum design methods of composite propeller.The purpose of the present invention is to solve the existing incomplete problems of composite propeller design method.Detailed process are as follows: one, beginning；Two, determine that composite propeller is designed into fast J0Under pitch pi 0；Three, designing into speed is J1When 0.75R at θ0.75R；Four, α is calculated0.75R；Five, determine that metal airscrew is being designed into fast as J1When 0.75R at geometric pitch angle θ1；Six, determine that composite propeller is being designed into fast J1Geometric pitch angle θ1；Seven, composite plys angle and sequence are chosen；Eight, the initial geometry of composite propeller is designed；Nine, composite propeller is calculated into fast J1When geometric pitch angle θ1′；Ten, judge the angle of pitch | θ1′‑θ1|, if | θ1′‑θ1| >=0.1 ° then executes seven；If | θ1′‑θ1| 0.1 ° of < then terminates.The present invention is applied to propeller field.
Description
Technical field
The present invention relates to the multi-state propulsive performance optimum design methods of composite propeller.
Background technique
Traditional metal airscrew in the design process using decision design often with the propulsive performance under operating condition as target, this
Target determines that the basic offset of metal airscrew, the propulsive performance under other operating conditions cannot achieve further optimization design.
And composite propeller can carry out more mesh by the laying of design composite material due to its special Torsion Coupling effect
The design object that metal airscrew cannot achieve is realized in mark optimization.
The design method of composite propeller is different from traditional metal airscrew, and the design method of metal airscrew is not
It is satisfied with composite propeller again.The research of composite propeller is still in infancy at present, composite Materials Design mistake
Journey is mainly based upon conventional metals propeller, based on the offset parameter of metal airscrew, by the paving for designing composite material
Layer realizes that propulsive efficiency is identical as metal paddle under design conditions, or better than the target of metal paddle.However, propeller is in reality
During the navigation of border, there are also other running working conditions, particularly with the naval vessel for having lowsteaming demand, therefore only optimize composite wood
Material propeller is inadequate in the propulsive performance of design conditions.If can be mentioned simultaneously in the propulsive performance under guaranteeing design conditions again
Propulsive performance under other high operating conditions, then can effectively improve the synthesis propulsive performance of composite propeller, improve host
Service efficiency, reach energy-efficient effect, extend the hours underway on naval vessel.
Summary of the invention
The purpose of the present invention is to solve the existing incomplete problems of composite propeller design method, and propose one
The multi-state propulsive performance optimum design method of kind composite propeller.
Above-mentioned goal of the invention is achieved through the following technical solutions:
Step 1: starting；
Step 2: determining that composite propeller is designed into fast J0Under pitch pi 0, wherein i=1,2......n, n are
The radial radius number of composite propeller, value is positive integer；
Step 3: panel method is used to determine that metal airscrew is being designed into speed as J1When, the incoming flow angle of blade section at 0.75R
Spend θ0.75R；
Step 4: calculating the incoming flow angle of attack of blade section maximum propulsive efficiency at the main blade 0.75R of metal airscrew0.75R；
Step 5: determining that metal airscrew is being designed into fast as J according to step 3 and step 41When, blade section at 0.75R
Reach the geometric pitch angle of maximum propulsive efficiency；
Step 6: determining that composite propeller is being designed into fast J according to step 51, reach and pushed away higher than metal airscrew
Into the geometric pitch angle θ of efficiency1；
Step 7: choosing composite plys angle and sequence according to step 2；
Step 8: designing the initial geometry of composite propeller according to step 7；
Step 9: calculating composite propeller into fast J according to step 81When geometric pitch angle θ1′；
Step 10: judging the angle of pitch according to step 6 and step 9 | θ1′-θ1|, if | θ1′-θ1| >=0.1 °, then execute step
Rapid seven；If | θ1′-θ1| 0.1 ° of <, then terminate.
Invention effect
On the basis of original metal airscrew, using the designability of composite material, combined by design laying angle
The mode of initial geometry designs a kind of composite propeller, and make the propeller under design conditions and it is one or more its
He has higher propulsive efficiency at operating condition, realizes the high efficiency of composite propeller.It is high into fast propulsive performance guaranteeing to design
Effect simultaneously, makes naval vessel still show higher propulsive performance in other regimes.The material that propeller uses is composite material
(carbon fiber or glass fibre).
A kind of multi-state propulsive performance optimum design method of composite propeller, the optimization for being related to a kind of propeller are set
Meter method, multi-state refer to one or more operating condition (into speed) comprising design conditions (designing into speed) and in addition to design conditions,
Propeller uses composite material (carbon fiber or glass fibre).Based on the offset parameter of metal airscrew, determine compound
Geometrical pitch of the material propeller under design conditions is gone out using Design by Surface Panel Method in one or more in addition to design conditions
There is the composite propeller geometrical pitch of higher propulsive performance (propulsive efficiency) under operating condition, it is initial by composite propeller
Geometry designs and material laying angle design make composite propeller realize expected screw pitch point under hydrodynamic(al) load force
Cloth.
It can reach the geometrical pitch of higher propulsive efficiency by being pre-designed multi-state composite propeller, utilization is compound
Material Torsion Coupling characteristic makes it that predetermined torsional deflection occur under corresponding water dynamic load effect, realizes that composite propeller is more
The purpose that operating condition propulsive performance is promoted.
By predefining geometrical pitch value of the composite propeller under design conditions and other operating conditions, make composite wood
Material propeller not only has higher propulsive efficiency under design conditions, has under other running working conditions higher than metal airscrew
Propulsive efficiency, improve the synthesis propulsive performance of composite propeller.
Judge the angle of pitch | θ1′-θ1|, if | θ1′-θ1| >=0.1 °, then choose composite plys angle and sequence；Design
The initial geometry of composite propeller out；Composite propeller is calculated into fast J1When geometric pitch angle θ1′；Change multiple
Condensation material laying angle and sequence recalculate the initial geometry of composite propeller；If | θ1′-θ1| 0.1 ° of <, then terminate.
Detailed description of the invention
Fig. 1 is flow chart of the present invention；
Fig. 2 is angle schematic diagram between blade section and incoming flow at the main blade 0.75R of metal airscrew.
Specific embodiment
Specific embodiment 1: embodiment is described with reference to Fig. 1, a kind of composite propeller of present embodiment
Multi-state propulsive performance optimum design method, is specifically prepared according to the following steps:
Step 1: starting；
Step 2: determining that composite propeller is designed into fast J0Under pitch pi 0, wherein i=1,2......n, n are
The radial radius number of composite propeller, value is positive integer；
Step 3: panel method is used to determine that metal airscrew is being designed into speed as J1When, the incoming flow angle of blade section at 0.75R
Spend θ0.75R；
Step 4: calculating the incoming flow angle of attack of blade section maximum propulsive efficiency at the main blade 0.75R of metal airscrew0.75R；
Step 5: determining that metal airscrew is being designed into fast as J according to step 3 and step 41When, blade section at 0.75R
Reach the geometric pitch angle of maximum propulsive efficiency；
Step 6: determining that composite propeller is being designed into fast J according to step 51, reach and pushed away higher than metal airscrew
Into the geometric pitch angle θ of efficiency1；
Step 7: choosing composite plys angle and sequence according to step 2；
Step 8: designing the initial geometry of composite propeller according to step 7；
Step 9: calculating composite propeller into fast J according to step 81When geometric pitch angle θ1′；
Step 10: judging the angle of pitch according to step 6 and step 9 | θ1′-θ1|, if | θ1′-θ1| >=0.1 °, then execute step
Rapid seven；If | θ1′-θ1| 0.1 ° of <, then terminate；
Multi-state refers to one or more operating condition (into speed) comprising design conditions (designing into speed) and in addition to design conditions,
It is multiple to refer to two or more.
Specific embodiment 2: the present embodiment is different from the first embodiment in that: it is determined in the step 2 multiple
Condensation material Design of Propeller is into fast J0Under pitch pi 0, wherein i=1,2......n, n are the radial direction of composite propeller
Radius number；Detailed process are as follows:
It is basic parameter with the geometry offset of metal airscrew, the design of metal airscrew is into fast for J0, radial pitch
For pi 0, wherein i=1,2......n, n are the radial radius number of metal airscrew；By the radial pitch p of metal airscrewi 0
It is determined as composite propeller to design into fast J0Under pitch pi 0(composite propeller is J designing into speed0Shi Fasheng
Pitch after torsional deflection is pi 0)。
Other steps and parameter are same as the specific embodiment one.
Specific embodiment 3: the present embodiment is different from the first and the second embodiment in that: it is adopted in the step 3
Determine that metal airscrew designing into speed is J with panel method1When, at 0.75R blade section guide margin it is up-front come flow angle；Specific mistake
Journey are as follows:
Based on green theorem, metal airscrew panel method program is write using Fortran language, according to metal spiral
The solving model of paddle velocity field
4 π V (p) of metal airscrew velocity field is solved, basin where solving metal airscrew according to 4 π V (p) of metal airscrew velocity field
Disturbance velocity V (p)；
Wherein, p is flow field arbitrary point, and V (p) is the disturbance velocity in basin where metal airscrew, and Q is on propeller surface
Point,For perturbation potential,For velocity potential jump, V0For speed of incoming flow, nQFor Q point normal vector, RpQBetween point p and point Q
Distance, ssFor propeller blade face, swFor propeller tailwater system, S is integral face, Q1For the point on tailwater system,For point Q1
Normal vector,For for point p and point Q1The distance between；
Using the solving model of metal airscrew velocity field, solves and be different from designing into fast J0Into fast J1Lower metal spiral
The speed of incoming flow of the main blade of paddle
Wherein, P0.75RFor blade section guide margin leading edge at the main blade 0.75R of metal airscrew, R is radius, whereinVxTo be J into speed1When metal airscrew main blade 0.75R at x-axis speed of incoming flow, VyTo be J into speed1
When metal airscrew main blade 0.75R at y-axis speed of incoming flow, VzTo be J into speed1When metal airscrew main blade 0.75R at z
The speed of incoming flow of axis；Coordinate system where metal airscrew is cartesian coordinate system, and rotary shaft is defined as x-axis, and x-axis forward direction is next
Directional velocity is flowed, the axis where the main blade of propeller is y-axis, and coordinate system abides by right-hand rule；
It is J according to solving into speed1The speed of incoming flow of the lower main blade of metal airscrewUtilize formulaIt is J that metal airscrew, which is calculated, designing into speed1When, at 0.75R blade section guide margin it is up-front come flow angle
θ0.75R。
Other steps and parameter are identical as one of specific embodiment one to two.
Specific embodiment 4: unlike one of present embodiment and specific embodiment one to three: the step 4
The middle incoming flow angle of attack for calculating blade section maximum propulsive efficiency at the main blade 0.75R of metal airscrew；Detailed process are as follows:
Up-front geometrical model (the machine of blade section guide margin at the main blade 0.75R of metal airscrew is established using commercial CFD code
Aerofoil profile, two bubble faces) and fluid computational domain grid is divided, solve blade section guide margin leading edge at the main blade 0.75R of metal airscrew
Lift coefficient CL and resistance coefficient CD under different incoming flow angle of attack, are depicted as lift resistance ratio curve CL/CD- α, lift resistance ratio CL/CD
Bigger, the propulsive efficiency of blade section is higher at the main blade 0.75R of metal airscrew, lift resistance ratio curve CL/CDThe highest point-α is corresponding
The incoming flow angle of attack of blade section guide margin leading edge maximum propulsive efficiency at the main blade 0.75R of incoming flow angle of attack, that is, metal airscrew0.75R。
Other steps and parameter are identical as one of specific embodiment one to three.
Specific embodiment 5: unlike one of present embodiment and specific embodiment one to four: the step 5
It is middle to determine that metal airscrew is being designed into fast as J according to step 3 and step 41When, blade section reaches maximum propulsion at 0.75R
The geometric pitch angle of efficiency；Detailed process are as follows:
Metal airscrew is J designing into speed1When, at the main blade 0.75R of metal airscrew between blade section and incoming flow
There is angle α0.75RWhen, blade section reaches maximum propulsive efficiency at 0.75R, then blade section reaches maximum propulsion effect at 0.75R
The geometric pitch angle of rate are as follows: θ0.75R+α0.75R, such as Fig. 2.
Specific embodiment 6: unlike one of present embodiment and specific embodiment one to five: the step 6
It is middle to determine that composite propeller is being designed into fast J according to step 51, reach the geometry spiral shell for being higher than metal airscrew propulsive efficiency
Elongation θ1；Detailed process are as follows:
It is being J into speed1When, the geometric pitch angle and metal of blade section at the deformed 0.75R of composite propeller
Paddle reach maximum propulsive efficiency geometric pitch angle it is identical when, composite propeller reaches the propulsion higher than virgin metal propeller
Efficiency, i.e. composite propeller are being J into speed1When the target angle of pitch be θ1。
Other steps and parameter are identical as one of specific embodiment one to five.
Specific embodiment 7: unlike one of present embodiment and specific embodiment one to six: the step 7
It is middle that composite plys angle and sequence are chosen according to step 2；Detailed process are as follows:
It chooses composite plys angle and sequence is For composite material paving
Layer angle is 0 °,It is 45 ° for composite plys angle,It is 90 ° for composite plys angle, []sSymmetrically to spread
Layer.
Other steps and parameter are identical as one of specific embodiment one to six.
Specific embodiment 8: unlike one of present embodiment and specific embodiment one to seven: the step 8
The middle initial geometry that composite propeller is designed according to step 7；Detailed process are as follows:
The geometry for choosing metal airscrew first is the model 1 of composite propeller, according to the wing flapping in step 7
Degree and sequence solve composite propeller fluid and structural simulation equation calculation and go out composite propeller model 1 in J0Under paddle
Phyllomorphosis amount 1 obtains new composite material on the negative value maps of blade deflection 1 to 1 blade of composite propeller model
Model propeller 2 calculates composite propeller spiral shell model 2 in J again0Under blade deflection 2, extract composite material at this time
Propeller deform after pitch, whether the pitch compared at this time be equal to radial pitch pi 0If be equal to, will answer
Condensation material model propeller 2 is determined as the initial geometry of composite propeller, if it is not, then again by blade deflection
New composite propeller model 3 is obtained on 2 negative value maps to composite propeller model 2, calculates composite wood again
Expect model propeller 3 in J0Under blade deflection 3, extract the pitch after composite propeller deforms at this time, than
Whether pitch more at this time is equal to radial pitch pi 0If be equal to, composite propeller model 3 is determined as compound
The initial geometry of material propeller, if it is not, then again by the negative value maps of blade deflection 3 to composite propeller
New composite propeller model 4 is obtained on model 3, is repeated new composite propeller model 3 and is arrived new composite material
The process of model propeller 4 is until in J0Pitch and p after lower composite propeller model n deformationi 0It is identical, at this time by model
N is determined as the initial geometry of composite propeller；
Composite propeller fluid and structural simulation equation is
Wherein, [M] is mass matrix, and [C] is damping matrix, and [K] is stiffness matrix,For vector acceleration,For
Velocity vector, { u } are motion vector, FceFor centrifugal force, FcoFor Coriolis force, FhFor external force.
Other steps and parameter are identical as one of specific embodiment one to seven.
Specific embodiment 9: unlike one of present embodiment and specific embodiment one to eight: the step 9
It is middle that composite propeller is calculated into fast J according to step 81When geometric pitch angle θ1′；Detailed process are as follows:
The initial geometry of the composite propeller according to obtained in step 8 solves composite propeller fluid structurecoupling meter
The initial geometry of equation calculation composite propeller is calculated into fast J1The change value of the blade angle of pitch after deforming, by the angle of pitch
Change value is mapped to composite propeller, extracts the pitch P of blade section at 0.75R1', calculate pitch angle θ at this time1',
Wherein θ1'=tan-1(P1'/πD)。
Other steps and parameter are identical as one of specific embodiment one to eight.
Specific embodiment 10: unlike one of present embodiment and specific embodiment one to nine: the step 10
The middle judgement angle of pitch | θ1′-θ1|, if | θ1′-θ1| >=0.1 °, then follow the steps seven；If | θ1′-θ1| 0.1 ° of <, then terminate；Specifically
Process are as follows:
Pitch angle θ in comparison step six and step 91' and θ1If | θ1′-θ1| >=0.1 °, then step 7 is repeated to step
Nine work changes composite plys angle and sequence, recalculates the initial geometry of composite propeller；If | θ1′-θ1
| 0.1 ° of <, then terminate.
Other steps and parameter are identical as one of specific embodiment one to nine.
Step 2 to step 6 has determined the angle of pitch under another operating condition in addition to designing into speed, increases it according to demand
He designs and repeats the work of step 7 to step 8 into speed, realizes the propulsive performance optimization design of multiple operating conditions.
Claims (1)
1. a kind of multi-state propulsive performance optimum design method of composite propeller, it is characterised in that a kind of composite material spiral shell
The multi-state propulsive performance optimum design method of rotation paddle is specifically to follow the steps below:
Step 1: starting；
Step 2: determining that composite propeller is designed into fast J0Under pitch pi 0, wherein i=1,2......n, n are compound
The radial radius number of material propeller, value is positive integer；
Step 3: panel method is used to determine that metal airscrew is being designed into speed as J1When, blade section carrys out flow angle at 0.75R
θ0.75R；
Step 4: calculating the incoming flow angle of attack of blade section maximum propulsive efficiency at the main blade 0.75R of metal airscrew0.75R；
Step 5: determining that metal airscrew is being designed into fast as J according to step 3 and step 41When, blade section reaches at 0.75R
The geometric pitch angle of maximum propulsive efficiency；
Step 6: determining that composite propeller is being designed into fast J according to step 51, reach and be higher than the propulsion of metal airscrew maximum
The geometric pitch angle θ of efficiency1；
Step 7: choosing composite plys angle and sequence according to step 2；
Step 8: designing the initial geometry of composite propeller according to step 7；
Step 9: calculating composite propeller into fast J according to step 81When geometric pitch angle θ1′；
Step 10: judging the angle of pitch according to step 6 and step 9 | θ1′-θ1|, if | θ1′-θ1| >=0.1 °, then follow the steps seven to
Step 9；If | θ1′-θ1| 0.1 ° of <, then terminate；
Determine that composite propeller is designed into fast J in the step 20Under pitch pi 0, wherein i=1,2......n, n
For the radial radius number of composite propeller, value is positive integer；Detailed process are as follows:
It is basic parameter with the geometry offset of metal airscrew, the design of metal airscrew is into fast for J0, radial pitch is pi 0,
Wherein i=1,2......n, n are the radial radius number of metal airscrew, and value is positive integer；By the radial spiral shell of metal airscrew
Away from value pi 0It is determined as composite propeller to design into fast J0Under pitch pi 0；
Panel method is used to determine that metal airscrew is being designed into speed as J in the step 31When, blade section guide margin leading edge at 0.75R
Carry out flow angle；Detailed process are as follows:
Based on green theorem, metal airscrew panel method program is write using Fortran language, according to metal airscrew speed
Spend the solving model of field
4 π V (p) of metal airscrew velocity field is solved, basin where solving metal airscrew according to 4 π V (p) of metal airscrew velocity field
Disturbance velocity V (p)；
Wherein, p is flow field arbitrary point, and V (p) is the disturbance velocity in basin where metal airscrew, and Q is on propeller surface
Point,For perturbation potential,For velocity potential jump, V0For speed of incoming flow, nQFor Q point normal vector, RpQBetween point p and point Q
Distance, ssFor propeller blade face, swFor propeller tailwater system, S is integral face, Q1For the point on tailwater system,For point Q1Method
Vector,For for point p and point Q1The distance between；
Using the solving model of metal airscrew velocity field, solves and be different from designing into fast J0Into fast J1Lower metal airscrew master
The speed of incoming flow of blade
Wherein, P0.75RFor blade section guide margin leading edge at the main blade 0.75R of metal airscrew, R is radius, whereinVxTo be J into speed1When metal airscrew main blade 0.75R at x-axis speed of incoming flow, VyFor into speed
For J1When metal airscrew main blade 0.75R at y-axis speed of incoming flow, VzTo be J into speed1When metal airscrew main blade 0.75R
Locate the speed of incoming flow of z-axis；Coordinate system where metal airscrew is cartesian coordinate system, and rotary shaft is defined as x-axis, and x-axis is positive
For speed of incoming flow direction, the axis where the main blade of propeller is y-axis, and coordinate system abides by right-hand rule；
It is J according to solving into speed1The speed of incoming flow of the lower main blade of metal airscrewUtilize formulaIt is J that metal airscrew, which is calculated, designing into speed1When, the up-front incoming flow angle, θ of blade section guide margin at 0.75R0.75R；
The incoming flow angle of attack of blade section maximum propulsive efficiency at the main blade 0.75R of metal airscrew is calculated in the step 4；Specifically
Process are as follows:
The up-front geometrical model of blade section guide margin at the main blade 0.75R of metal airscrew is established using commercial CFD code and is divided
Fluid calculation domain grid solves liter of the blade section guide margin leading edge under different incoming flow angle of attack at the main blade 0.75R of metal airscrew
Force coefficient CLWith resistance coefficient CD, it is depicted as lift resistance ratio curve CL/CD- α, lift resistance ratio CL/CDIt is bigger, the main blade of metal airscrew
The propulsive efficiency of blade section is higher at 0.75R, lift resistance ratio curve CL/CDThe corresponding incoming flow angle of attack, that is, metal airscrew in the highest point-α
The incoming flow angle of attack of blade section guide margin leading edge maximum propulsive efficiency at main blade 0.75R0.75R；
Determine that metal airscrew is being designed into fast as J according to step 3 and step 4 in the step 51When, blade section at 0.75R
Reach the geometric pitch angle of maximum propulsive efficiency；Detailed process are as follows:
Metal airscrew is J designing into speed1When, there is angle between blade section and incoming flow at the main blade 0.75R of metal airscrew
α0.75RWhen, blade section reaches maximum propulsive efficiency at 0.75R, then blade section reaches the several of maximum propulsive efficiency at 0.75R
What angle of pitch are as follows: θ0.75R+α0.75R；
Determine that composite propeller is being designed into fast J according to step 5 in the step 61, reach and be higher than metal airscrew most
The geometric pitch angle θ of big propulsive efficiency1；Detailed process are as follows:
It is being J into speed1When, the geometric pitch angle of blade section reaches with metal paddle at the deformed 0.75R of composite propeller
When the geometric pitch angle of maximum propulsive efficiency is identical, composite propeller reaches the propulsive efficiency higher than virgin metal propeller,
I.e. composite propeller is being J into speed1When the target angle of pitch be θ1；
Composite plys angle and sequence are chosen according to step 2 in the step 7；Detailed process are as follows:
It chooses composite plys angle and sequence is For composite plys angle
Degree is 0 °,It is 45 ° for composite plys angle,It is 90 ° for composite plys angle, []sFor symmetric layups；
The initial geometry of composite propeller is designed in the step 8 according to step 7；Detailed process are as follows:
First choose metal airscrew geometry be composite propeller model 1, according in step 7 laying angle and
Sequence solves composite propeller fluid and structural simulation equation calculation and goes out composite propeller model 1 in J0Under blade become
Shape amount 1 obtains new composite material spiral on the negative value maps of blade deflection 1 to 1 blade of composite propeller model
Paddle model 2 calculates composite propeller model 2 in J again0Under blade deflection 2, extract composite propeller at this time
Whether the pitch after deforming, the pitch compared at this time are equal to radial pitch pi 0If be equal to, by composite material
Model propeller 2 is determined as the initial geometry of composite propeller, if it is not, then again by the negative of blade deflection 2
Value, which is mapped to, obtains new composite propeller model 3 on composite propeller model 2, calculate composite material spiral again
Paddle spiral shell model 3 is in J0Under blade deflection 3, extract the pitch after composite propeller deforms at this time, compare this
When pitch whether be equal to radial pitch pi 0If be equal to, composite propeller model 3 is determined as composite material
The initial geometry of propeller, if it is not, then again by the negative value maps of blade deflection 3 to composite propeller model
New composite propeller model 4 is obtained on 3, is repeated new composite propeller model 3 and is arrived new composite material spiral
The process of paddle model 4 is until in J0Pitch and p after lower composite propeller model n deformationi 0It is identical, at this time by composite material
Model propeller n is determined as the initial geometry of composite propeller；
Composite propeller fluid and structural simulation equation is
Wherein, [M] is mass matrix, and [C] is damping matrix, and [K] is stiffness matrix,For vector acceleration,For speed
Vector, { u } are motion vector, FceFor centrifugal force, FcoFor Coriolis force, FhFor external force；
Composite propeller is calculated into fast J according to step 8 in the step 91When geometric pitch angle θ1′；Detailed process
Are as follows:
The initial geometry of the composite propeller according to obtained in step 8 solves composite propeller fluid and structural simulation side
Journey calculates the initial geometry of composite propeller into fast J1The change value of the blade angle of pitch, the angle of pitch is changed after deforming
Value is mapped to composite propeller, extracts the pitch P of blade section at 0.75R1', calculate pitch angle θ at this time1', wherein
θ1'=tan-1(P1'/πD)；
The angle of pitch is judged in the step 10 | θ1′-θ1|, if | θ1′-θ1| >=0.1 °, then follow the steps seven；If | θ1′-θ1| <
0.1 °, then terminate；Detailed process are as follows:
Pitch angle θ in comparison step six and step 91' and θ1If | θ1′-θ1| >=0.1 °, then repeat the work of step 7 to step 9
Make, changes composite plys angle and sequence, recalculate the initial geometry of composite propeller；If | θ1′-θ1| <
0.1 °, then terminate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201511009110.5A CN105677945B (en) | 2015-12-28 | 2015-12-28 | A kind of multi-state propulsive performance optimum design method of composite propeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201511009110.5A CN105677945B (en) | 2015-12-28 | 2015-12-28 | A kind of multi-state propulsive performance optimum design method of composite propeller |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105677945A CN105677945A (en) | 2016-06-15 |
| CN105677945B true CN105677945B (en) | 2019-10-22 |
Family
ID=56297765
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201511009110.5A Expired - Fee Related CN105677945B (en) | 2015-12-28 | 2015-12-28 | A kind of multi-state propulsive performance optimum design method of composite propeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105677945B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20180016810A (en) * | 2016-08-08 | 2018-02-20 | 월드콥터코리아 주식회사 | Automatic control device for controllable pitch airboat propeller |
| CN108357630B (en) * | 2018-03-07 | 2023-11-14 | 中国人民解放军海军工程大学 | Large-side-inclined propeller blade made of marine carbon fiber composite material and design method thereof |
| CN109711093B (en) * | 2019-01-17 | 2020-09-15 | 北京理工大学 | Pre-deformation optimization method for marine composite propeller |
| CN111444642B (en) * | 2020-03-02 | 2022-04-19 | 北京理工大学 | Composite propeller layering optimization method based on multi-objective genetic algorithm |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101706832A (en) * | 2009-11-25 | 2010-05-12 | 哈尔滨工业大学 | Optimization design method of fibre enhanced composite material marine propeller blade |
| CN102930118A (en) * | 2012-11-20 | 2013-02-13 | 哈尔滨工业大学 | Optimization design method for blade root of compound propeller blade |
| CN102930116A (en) * | 2012-11-20 | 2013-02-13 | 哈尔滨工业大学 | Design method for large-size detachable compound propeller |
| CN104809320A (en) * | 2015-05-27 | 2015-07-29 | 厦门大学 | Method for designing air pusher propeller of rotary wing type aircraft |
-
2015
- 2015-12-28 CN CN201511009110.5A patent/CN105677945B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101706832A (en) * | 2009-11-25 | 2010-05-12 | 哈尔滨工业大学 | Optimization design method of fibre enhanced composite material marine propeller blade |
| CN102930118A (en) * | 2012-11-20 | 2013-02-13 | 哈尔滨工业大学 | Optimization design method for blade root of compound propeller blade |
| CN102930116A (en) * | 2012-11-20 | 2013-02-13 | 哈尔滨工业大学 | Design method for large-size detachable compound propeller |
| CN104809320A (en) * | 2015-05-27 | 2015-07-29 | 厦门大学 | Method for designing air pusher propeller of rotary wing type aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105677945A (en) | 2016-06-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105677945B (en) | A kind of multi-state propulsive performance optimum design method of composite propeller | |
| CN105653781B (en) | A kind of computational methods of composite propeller vacuole performance | |
| CN109625226B (en) | Design method of axial-flow type high-power-density water jet propulsion pump | |
| CN113821996B (en) | Novel rapid calculation method for high-speed entry trajectory of projectile | |
| CN109711093B (en) | Pre-deformation optimization method for marine composite propeller | |
| CN111444642B (en) | Composite propeller layering optimization method based on multi-objective genetic algorithm | |
| Firdaus et al. | Numerical and experimental studies of a small vertical-axis wind turbine with variable-pitch straight blades | |
| CN105653783A (en) | Method for improving fluid-solid coupling calculation precision of composite material propeller | |
| CN106043688A (en) | Helicopter rotor airfoil | |
| Sánchez-Caja et al. | Study of end-plate shape variations for tip loaded propellers using a RANSE solver | |
| Xing-Kaeding et al. | ESD design and analysis for a validation bulk carrier | |
| Truong et al. | The EFD and CFD study of rudder-bulb-fin system in ship and propeller wake field of KVLCC2 tanker in calm water | |
| CN202953169U (en) | Novel spoon-shaped blended winglet for civil airplane | |
| CN205819561U (en) | A kind of lifting airscrew aerofoil profile | |
| CN108757568B (en) | Axial flow fan blade | |
| CN105302983A (en) | Wind turbine wing type asymmetrical blunt trailing-edge design method based on relative curvature degrees | |
| CN101968821B (en) | Airfoil profile design method and structure applicable for multi-speed domain | |
| CN114896722A (en) | Method for accurately predicting multi-scale cavitation flow around hydrofoil | |
| Truong et al. | Improvement of rudder-bulb-fin system in ship and propeller wake field of KVLCC2 tanker in calm water | |
| Hu | Two dimensional numerical simulation of cycloidal propellers with flat plate airfoil in hovering status | |
| CN106050730B (en) | A kind of vane pump and the impeller blade for vane pump | |
| CN114036660B (en) | Velocity moment distribution for inhibiting secondary flow of suction surface of impeller blade of water pump | |
| Liu et al. | A potential based panel method for prediction of steady performance of ducted propeller | |
| CN1621682A (en) | Rotor blade of diagonal flow water turbine | |
| Sánchez-Caja et al. | Evaluation of endplate impact on tip loaded propeller performance using a RANSE solver |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20191022 Termination date: 20211228 |