CN107269583B - A kind of super or transonic speed axial fan designs method based on high-order moment - Google Patents
A kind of super or transonic speed axial fan designs method based on high-order moment Download PDFInfo
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- CN107269583B CN107269583B CN201710602403.7A CN201710602403A CN107269583B CN 107269583 B CN107269583 B CN 107269583B CN 201710602403 A CN201710602403 A CN 201710602403A CN 107269583 B CN107269583 B CN 107269583B
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- 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
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- 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
Abstract
Super/transonic speed axial fan designs method based on high-order moment that the invention discloses a kind of, the method carries out one-dimensional design, quasi three-dimensional design, full three dimensional design mainly for super/transonic fan stage, while matching different flow angle and the further three-dimensional optimized design of middle camber line regularity of distribution progress；Finally, obtain camber line characteristic parameter and the geometry angular dimensions regularity of distribution in the more blade of universality, these parameter distribution rules with universality are expressed as relevant high-order moment mathematical model, personnel use in actual engineering design convenient for Aeroengine Design.Research practice shows that the very harsh technical needs such as high load capacity, high throughflow, high efficiency, the wide stable operation range of aero-engine compressibility can be better meet using super/transonic speed aerofoil fan designed by design method of the present invention.
Description
Technical field
The invention belongs to aero-gas turbine fan/compressor design fields, are related to a kind of super or transonic speed axis stream
The design method of fan.
Background technique
Aero-engine is referred to as modern industry " jewel on imperial crown ", is both that the heart of aircraft and the strategy of country fill
It is standby, but be measure a National Industrial basis, scientific and technological industrial might, military equipment level and overall national strength important symbol.Its
Development applies the most advanced technology of modern industry and state-of-the-art industry efforts to a certain extent.Therefore, high performance turbine
The development of engine countries in the world are military or the development plan of civilian propulsion system in occupy space of top prominence always.Implement in China
Aviation Propulsion Technology Verification (APTD) plan, for develop thrust ratio provide technological reserve for the engine of 10~15 ranks, with
Western developed country half to two generation technique periods of expansion of a poor generation.Country arranges the development of aero-engine and gas turbine
For key special subjects, and increased capital is put within a very long time from now on, and the advanced technology of each industrial circle is concentrated to carry out weight
Point tackling key problem, final target are to realize the independent research and development and manufacture of aero-engine complete product.
Fan/compressor as one of aero-engine core Pneumatic component is by high-speed rotating blade to air-flow
Acting, meets the technical indicator demand of combustion chamber to improve stream pressure.A large amount of research data and actual engineering design are real
It tramples and shows the interaction flowed under the premise of structural strength, material technology allow by parts match, expands compression system
The potentiality for critical performance parameters of uniting, and then the contradiction between concordant flow, pressure ratio, efficiency and stall margin are modern Aviation hairs
The target that the development of motivation key aerodynamic component fan/compressor aeroperformance is pursued.15~20 magnitude of thrust ratio higher is had an high regard for
One of fanjet key technology of ratio is exactly to improve the grade airload level and efficiency of compressibility, to reach reduction
Fan/compressor series improves engine thrust-weight ratio and reduces the purpose of oil consumption.Therefore, the core design skill of fan/compressor
The research and development of art are the important link of modern aeroengine technology development always.
Super or transonic fan stage channel interior is with shockwave boundary layer interaction, strong inverse pressure flowing, boundary-layer corner region flow
The secondary flow of separation and SHOCK WAVE INDUCED is main feature.How to be controlled in the limited flowing space and utilizes shock wave itself
Supercharging effect, farthest reduce inverse pressure flow induced separation flowing scale and intensity with reduce all kinds of flow losses,
Expected from guidance boundary-layer fluid or even mainstream fluid are realized to required direction flowing plus function amount designs, undoubtedly such wind
Fan is designed with successful core technology route.
Summary of the invention
The super or transonic speed axial fan designs method that the present invention provides a kind of based on high-order moment, for it is super or across
Velocity of sound aerofoil fan carries out three-dimensional optimized design, reaches raising wind by camber line, matching blade air angle in optimization blade profile
Fan the purpose of whole aeroperformance.Meanwhile obtaining point of camber line characteristic parameter and geometry angular dimensions in the more blade of universality
These parameter distribution rules with universality are expressed as corresponding high-order moment mathematical model by cloth rule, are convenient for aviation
Engine designer uses in actual engineering design.
The key of the used method of the present invention is to use under fan grade flowing environment based on quasi- three-dimensional design data
Three-dimensional optimal design method (Genetic algorithms~+ gradient algorithm) carries out complete three to camber line scheme in different blade profiles and geometry angle scheme
Dimension value emulation, obtains and analyzes corresponding aeroperformance data and Field Characteristics parameter.Meeting mechanical structure, processing work
Under the limiting factors such as skill, impeller intensity, the pneumatic new construction of least disadvantage fan for meeting total demand is extracted.Therefore, this will
Relatively reasonable swirl distribution feature should be given by asking in quasi three-dimensional design, not only flow angle can match under the conditions of Three-dimensional Flow
Flow boundary condition between blade row, and the variation characteristic of middle camber line should be able to control to the maximum extent and utilize shock wave, suppression
Exhibition after corner region flow separation processed and shock wave improves the pneumatic efficiency of fan to secondary flow, and guarantees that original stall is abundant
Degree demand.
The purpose of the present invention is what is be achieved through the following technical solutions:
A kind of super or transonic speed axial fan designs method based on high-order moment, includes the following steps:
One, one-dimensional design
Based on original fan aerodynamic parameter and runner geometry, each column blade at fan mean radius is calculated
Leading edge and trailing edge position speed triangle, while obtaining fan overall performance data and main geometric parameter；
Two, quasi three-dimensional design
To S in one-dimensional design basis2Stream interface and S1Stream interface carries out refinement, wherein in S2Stream interface design when, by
Movable vane trailing edge position gives the regularity of distribution of circular rector radially to complete the three-dimensional indirect problem design of the standard of fan；
On the basis of quasi three-dimensional design, the analysis result and blade three-dimensional modeling to S1 and S2 stream interface design data are relied on
The initial three dimendional blade geometry passages structure of module construction fan；
Three, full three dimensional design
Using the obtained initial three dimendional blade geometry passages of quasi three-dimensional design, the blade three-dimensional gas of high-order moment is relied on
Dynamic forming method, by based on Three Dimensional Viscous CFD technology under grade environmental condition further implement the optimization design of blade path with
Complete design task.
In the present invention, used Optimal Design Strategies are as follows: using fan grade adiabatic efficiency as objective function, with fan blade
Feature geometries parameter (camber line characteristic parameter and geometry angular dimensions in blade) is optimization design variable, and using Genetic algorithms~+ ladder
It spends algorithm and carries out optimizing, it is final to obtain camber line characteristic parameter and the geometry angular dimensions regularity of distribution in the more blade of universality.This
Outside, the parameter distribution rule by these with universality is expressed as relevant high-order moment mathematical model, is convenient for aeroplane engine
Machine designer uses in actual engineering design.
In the present invention, the fan flowing control mechanism that three-dimensional optimized designs under grade environmental condition are as follows: in three-dimensional viscous flow
Under environment, the adjustment of camber line geometric parameter in blade path higher derivative can reasonably be controlled in blade inlet edge or even channel
The N-S equations in portion and the high entropy flow body three-dimensional migration characteristic of the boundary-layer on channel surface, so that fan blade channel exists
Guarantee that original stall is spent in advance and realized accordingly plus under conditions of function amount, is effectively reduced shock loss, inhibits blade suction surface attached
The secondary flow of surface layer migration and induction.It is required pneumatic negative that the optimizing and revising of blade geometry angle is that fan blade channel can be realized
Lotus is horizontal and obtains the important guarantee of corresponding through-current capability.Meanwhile the flow boundary condition between Auto-matching upstream and downstream blade row, it
It is that interstage flow moves one of the key technique that matching technique is achieved during fan design.
The present invention is advised in traditional one-dimensional design basis by giving the distribution of circular rector radially in movable vane trailing edge position
It restrains to complete the three-dimensional indirect problem design of the standard of fan.Finally, relying on the blade three-dimensional pneumatic forming method of high-order moment, pass through
Implement the optimization design of blade path further based on Three Dimensional Viscous CFD technology under grade environmental condition with complete design task.
Compared with the prior art, the present invention has the advantage that
1, the present invention is in traditional one-dimensional design basis, by giving the distribution of circular rector radially in movable vane trailing edge position
Rule is led to come the three-dimensional indirect problem design of standard for completing fan finally, relying on the blade three-dimensional pneumatic forming method of high-order moment
It crosses based on Three Dimensional Viscous CFD technology under grade environmental condition and implements the optimization design of blade path further with complete design times
Business.Surpass designed by the present invention or transonic speed aerofoil fan not only remains conventional one-dimensional, quasi- three-dimensional, full three dimensional design successively
Steps propulsion feature, but also by modern advanced CFD technology and design optimizing, it rationally controls and utilizes leaf
Piece channel and up-front shock wave compression effect, guide blades channel boundary-layer fluid and mainstream fluid are flowed to required direction
It is dynamic.Therefore, under the background for abiding by the constraint of aerodynamics macroscopic view, pass through the optimum pneumatic geometry for the completely new fan that design obtains
Structure, while completing to air-flow plus function pressurization mission, additionally it is possible to keep higher pneumatic efficiency, and to maintain to answer
Stall margin.
2, research practice show using designed by design method of the present invention surpass or transonic speed aerofoil fan can be preferably
Meet the very harsh technology need such as high load capacity, high throughflow, high efficiency, the wide stable operation range of aero-engine compressibility
It asks.
Detailed description of the invention
Fig. 1 is fan structure and three dimendional blade construction method of the invention；
Fig. 2 is circular rector and movable vane import relative Mach number along the opposite high distribution of leaf, and (a) movable vane trailing edge circular rector is along opposite
The high distribution of leaf, (b) movable vane import relative Mach number is along the opposite high distribution of leaf；
Fig. 3 is the characteristic line of fan grade adiabatic efficiency and overall pressure tatio and flow, and (a) adiabatic efficiency and discharge characteristic are (b) total
Pressure ratio and discharge characteristic；
Fig. 4 is the middle camber line and the relevant parameter regularity of distribution of movable vane and stator blade root section, (a) movable vane, (b) stator blade；
Fig. 5 is the middle camber line and the relevant parameter regularity of distribution that movable vane and 50% leaf of stator blade open up (central diameter) section, and (a) is dynamic
Leaf, (b) stator blade；
Fig. 6 is the middle camber line and the relevant parameter regularity of distribution of movable vane and stator blade blade tip section, (a) movable vane, (b) stator blade；
Fig. 7 is the long-pending folded stator blade three-dimensional blade profile section of center of gravity product folded movable vane and chord length 50%, (a) movable vane, (b) stator blade；
Fig. 8 is the middle camber line characteristic at movable vane and the high section of stator blade difference leaf, (a) movable vane, (b) stator blade；
Fig. 9 is the distribution high along leaf of the geometry angle of the movable vane stator blade front and rear edge of final design, (a) movable vane, (b) stator blade；
Figure 10 is three-dimensional movable vane, the stator blade 3D solid of final design, (a) fan movable vane, (b) Fan Stator；
Figure 11 is the three-dimensional fan new construction of final design, (a) oblique view, (b) side view, (c) front view, (d) backsight
Figure.
Specific embodiment
Further description of the technical solution of the present invention with reference to the accompanying drawing, and however, it is not limited to this, all to this
Inventive technique scheme is modified or replaced equivalently, and without departing from the spirit and scope of the technical solution of the present invention, should all be covered
Within the protection scope of the present invention.
Specific embodiment 1: the super or transonic speed aerofoil fan that present embodiments provide for a kind of based on high-order moment
Design method carries out one-dimensional design, quasi three-dimensional design, full three dimensional design mainly for super or transonic fan stage, while matching not
Same flow angle and the middle camber line regularity of distribution carry out further three-dimensional optimized design；Finally, obtaining the blade of more universality
Middle camber line characteristic parameter and the geometry angular dimensions regularity of distribution, these parameter distribution rules with universality are expressed as relevant
High-order moment mathematical model, convenient for Aeroengine Design, personnel use in actual engineering design.Specific technical solution is such as
Under:
One, one-dimensional design
For the one-dimensional design of fan, the present invention is based on original fan aerodynamic parameter and runner geometry, meter
The leading edge of each column blade and the speed triangle of trailing edge position at fan mean radius are calculated, while fan bulking property can be obtained
It can data (adiabatic efficiency, overall pressure tatio, pressure, temperature, the Mach number etc. of middle path position blade front and rear edge) and main geometry
Parameter (number of blade, blade front and rear edge position, fan internal diameter and internal diameter etc.).It is initial stage option screening, overall pneumatic property
It is indispensable in energy prediction and the design of foundation and engine compression system and Performance Prediction of later period quasi three-dimensional design
Important technical links, it is efficient, convenient etc. to have the advantages that.But it is all more important in fan passage due to ignoring or simplifying
Flow characteristics, therefore, precision of prediction especially super or transonic fan stage aeroperformance for fan are relatively low.
Two, quasi three-dimensional design
The quasi three-dimensional design of fan/compressor is further refinement on the basis of one-dimensional design, wherein main packet
Include S2Stream interface (meridional plane) design and S1Stream interface (across the leaf section of blade to blade) design.The input parameter of quasi three-dimensional design
Predominantly one-dimensional design as a result, wherein in S2Control when stream interface designs along the high direction swirl distribution of leaf is particularly critical.According to
Changing rule of the speed triangle of each column blade of fan on different leaf height is calculated along the regularity of distribution of the high circular rector of leaf, and is tied
Relevant loss model is closed, the necessary data of relatively accurate fan performance parameter and later period three dimensional design are obtained.
During quasi three-dimensional design, swirl distribution rule as quasi- three-dimensional indirect problem design key input parameter it
One.That it is not only fan plus function amount, speed triangle and the associated important tie of flow losses, and be also that blade three-dimensional is several
The deciding factor of what feature.For the design method, using change circular rector radially/plus the design method of function amount, specifically
The relational expression of the high relative position of leaf and circular rector is expressed as follows:
H=A+B* (rVθ)+C*(rVθ)2+D*(rVθ)3+E*(rVθ)4+F*(rVθ)5+G*(rVθ)6
A=-5.4878535971996165E+005
B=6.2099455119315367E+006
C=-2.9272064410135999E+007
D=7.3570823036940888E+007
E=-1.0398371911900093E+008
F=7.8362156403807729E+007
G=-2.4598948853334174E+007
Wherein, rVθFor the circular rector value of corresponding leaf exhibition position, H is the relative position from blade root to blade tip, and A~G is respectively phase
The multinomial coefficient answered.
On the basis of quasi three-dimensional design, the analysis result and blade three-dimensional modeling to S1 and S2 stream interface design data are relied on
Module can construct the initial three dimendional blade channel design of fan.After the completion of one peacekeeping quasi three-dimensional design, largely
Fan totality aeroperformance and basic fan grade geometric profile are just determined.
Three, full three dimensional design
Full three dimensional design is to utilize three dimendional blade geometry passages obtained by quasi three-dimensional design on the basis of quasi three-dimensional design
Data carry out full Three Dimensional Viscous Numerical Simulation Analysis, to verify the reliability of preliminary design scheme.Here complete three are mainly used
Victoria C FD technology carries out full three-dimensional computations to fan inside complex flowfield, to the internal flow feature of initial blade design scheme with
Aerodynamic is evaluated, and proposition advanced optimizes improved direction and approach.For super or transonic fan stage inside
It flows complex, is usually often not achieved by one-dimensional+quasi- three-dimensional+three dimensional design preliminary design scheme obtained expected
Design objective problem, it is necessary to carry out the three-dimensional optimized design studies combined based on CFD technology with optimum design method.For
Super or transonic speed aerofoil fan carries out three-dimensional optimized design, is reached by camber line, matching blade air angle in optimization blade profile
Further increase the purpose of fan entirety aeroperformance.Meanwhile obtain more in the blade of universality camber line characteristic parameter with it is several
What angular dimensions regularity of distribution.These parameter distribution rules with universality are expressed as relevant high-order moment mathematical modulo
Type, convenient for Aeroengine Design, personnel use in actual engineering design.
For practical blade path, edge and trailing edge in front of the blade between actual airflow direction and Theoretical airflows direction
Difference is known as being the angle of attack and deviation angle.Although in the development process of fan/compressor designing technique, scholars and engineering
Technical staff has developed many corresponding angles of attack and Deviation Angle Model.But these models are largely dependent upon design
The personal experience of personnel, hardly has universality.Therefore, the present invention is set on the basis of using these models by optimization
Meter means have carried out full three-dimensional optimized to the geometry angle of fan blade and have matched, to reach to shock wave and boundary-layer internal flow
Effectively control, while efficiently solving the pneumatic matching problem between movable vane and stator blade.It finally obtains blade geometry angle and leaf is high
The relational expression of relative position is as follows:
H=A+B* β+C* β2+D*β3+E*β4+F*β5+G*β6
The coefficient at 1 different location geometry angle of table and the high relative position formula of leaf
Wherein, β is corresponding leaf exhibition position blade inlet edge or trailing edge geometry angle, and H is the relative position from blade root to blade tip, A
~F is respectively corresponding multinomial coefficient.
Other a key technology of this method is by optimizing and revising to camber line in each blade profile section, dexterously
Control the shock wave and secondary flow inside blade path.Usually in the technical literature data published, the most common blade profile
Bar none using parabola, circular arc, more circular arcs, Cubic splines and multinomial no more than quadravalence in middle camber line design method
Formula.After the middle camber line of blade profile has been determined, selects the suitable blade profile thickness regularity of distribution to be overlapped and just complete blade profile in benchmark
Construction in plane.But with the continuous improvement of modern fan grade airload level and free stream Mach number, in conventional blade profile
The design method of camber line seems unable to do what one wants very much to do in the control for three-dimension complex flow, often beyond one's ability to help.Base
In the understanding of this basic physical concept, the present invention uses high-order moment (currently used highest number for 6) to design leaf
Camber line in type breaches limitation of the traditional design method to camber line inflection point number in Transonic Blade Profile, increases blade profile and three
Tie up the freedom degree of blade design.Meanwhile mathematically, since high-order moment has continuous, the guidable characteristic of higher order, this
There is more superior control effect for the strong nonlinearities rank such as shock wave in blade path cutout field.The present invention is flat in blade profile benchmark
In face, it is unfolded to introduce the design method of camber line in blade profile with camber line in movable vane blade root, central diameter, the blade profile in blade tip section, specifically
Formula is as follows:
Camber line formula in each section blade profile:
V=A+B*U+C*U2+D*U3+E*U4+F*U5+G*U6
Camber line equation coefficients in the different dynamic and static leaf section blade profiles of table 2
Wherein, U is from leading edge to trailing edge along the relative position in chord length direction, and V is the height of corresponding middle arc positions,
A~G is respectively corresponding multinomial coefficient.
Specific embodiment 2: can be used in super or transonic fan stage/compressor in order to illustrate core of the invention technology
Design, present embodiment designed for certain single-stage transonic fan stage, in which: the import of fan movable vane is in super substantially
Velocity of sound flow regime, as shown in Fig. 2 (b)；The main design parameters of the fan are as shown in table 3.
3 fan grade design parameter of table
According to the design parameter of certain single-stage transonic fan stage, carry out one-dimensional, quasi- three-dimensional, full three-dimensional optimized design studies.Its
During quasi- three-dimensional computations, the distribution core by circular rector along the high relative position of leaf is as shown in Figure 2.Obviously, which adopts
With the change circular rector design method of radially not equal function, this is conducive to the control to shock wave in blade path and secondary flow.
Fig. 3 gives fan grade adiabatic efficiency and overall pressure tatio with the characteristic line of mass-flow change.Result of study shows just
The fan grade scheme for the design that begins cannot reach expected design objective.By using design method proposed by the present invention, not only should
The design point aeroperformance of fan obtains biggish promotion, and its stable operation range is also greatly expanded.Specifically
Are as follows: under design point, overall pressure tatio, mass flow, adiabatic efficiency and stall margin increase separately 2.13%, 0.62%,
1.65%, 3.13%, blocking flow and stall flow increase separately 0.42%, -2.69%, and the whole aeroperformance of the fan obtains
Comprehensive promotion was obtained, as shown in table 4.Its Ananlysis of main cause is as follows: under three-dimensional viscous flow environment, blade path high-order is led
The adjustment of camber line geometric parameter in number can reasonably control N-S equations and the channel of blade inlet edge or even channel interior
The high entropy flow body three-dimensional migration characteristic of the boundary-layer on surface, so that fan blade channel is spent and realized in advance in the original stall of guarantee
Accordingly plus under conditions of function amount, it is effectively reduced shock loss, inhibition blade suction surface boundary-layer migrates and the Secondary Flow of induction
It is dynamic.Optimizing and revising for blade geometry angle is that fan blade channel can be realized required airload level and obtain corresponding through-flow energy
The important guarantee of power.Meanwhile the flow boundary condition between Auto-matching upstream and downstream blade row, it is interstage flow during fan design
One of the key technique that dynamic matching technique is achieved.
4 fan optimization design scheme of table and initial scheme performance comparison
After being designed for further analysis optimization the advantages of the geometrical characteristic and aerodynamic optimization technology in blade profile section, Fig. 4~
Fig. 6 gives each blade root of moving-stator blade, blade tip, the middle camber line in central diameter section and one, second dervative in basic blade profile plane
Changing rule.Result of study shows in blade profile camber line slope and curvature along tangential sufficiently smooth, as incoming flow is with respect to Mach
Several increases, middle camber line maximum defluxion reduces and maximum defluxion position is close to trailing edge, and leading edge nearby there are reverse curvature with
Compression property realizes the purpose of expected control shock wave and secondary mesoscale flow and intensity.Fig. 7 give the folded movable vane of center of gravity product with
The folded stator blade three-dimensional blade profile section of the product of chord length 50%.Result of study shows the maximum defluxion of camber line in the blade profile at movable vane blade root
Position is located at blade profile middle position, and the maximum defluxion position at 50% leaf height and blade tip is successively deviated to trailing edge, is formd pre-
Compress blade profile feature.This with people recognize existing super, transonic speed high load capacity movable vane design core concept, flow mechanism at present
It is sensible consistent.This structure is conducive to postpone the generation of shock wave, and reduces the intensity of leading edge shock, and no matter pressure face or inhales
The air-flow velocity in power face all will not prematurely reach critical Mach number, while reduce negative sequence harmonic, be not susceptible to air-flow
Separation is conducive to the efficiency and overall performance that promote compressor.
Fig. 8 is camber line characteristic in the blade profile in the high section of optimal fan grade difference leaf.Result of study show for movable vane and
Speech, the middle camber line maximum defluxion position at blade root is located in the middle part of blade profile；And along blade open up to, maximum defluxion position gradually to
Trailing edge is mobile, while maximum immunity value is reduced.This is because identical revolving speed, the tangential velocity at movable vane blade tip is greater than leaf
Tangential velocity at root, and free stream Mach number is inherently bigger, by speed triangle it is found that being located at the air-flow phase of blade tip
Mach number is easier to reach critical Mach number state.And once reach critical Mach number, it is super just to will form part on blade profile surface
Sound area.In the area, since the subsequent pressure of the pressure ratio of air-flow is much lower, so that blade profile surface is readily formed shock wave.
Either normal shock wave or oblique shock wave can all cause inevitably after interfering with each other with the boundary-layer that viscous fluid is formed
Aerodynamic loss.Camber line shows flat in the blade profile at blade tip after three-dimensional optimized, has certain precommpression effect, from
And the intensity of movable vane leading edge shock is weakened, be conducive to the promotion of compressor pneumatic efficiency.Tangential speed at movable vane blade root
Spend relatively small, the relative Mach number of air-flow is lower than blade tip place.In addition connecting portion of the movable vane blade root as movable vane and shaft needs
Consider intensity, structure, material property.It is the three-dimensional movable vane of final design shown in Fig. 10, quiet so the thickness at blade root is larger
Leaf 3D solid also illustrates this feature.The above Optimum Design Results and super or transonic fan stage/compressor design core are thought
Want to match.
Claims (5)
1. a kind of super or transonic speed axial fan designs method based on high-order moment, it is characterised in that the method step is such as
Under:
Step 1: one-dimensional design
Based on original fan aerodynamic parameter and runner geometry, calculate at fan mean radius before each column blade
The speed triangle of edge and trailing edge position, while obtaining fan overall performance data and main geometric parameter；
Step 2: quasi three-dimensional design
To S in one-dimensional design basis2Stream interface and S1Stream interface carries out refinement, wherein in S2When stream interface designs, by movable vane
Trailing edge position gives the regularity of distribution of circular rector radially to complete the three-dimensional indirect problem design of the standard of fan；
On the basis of quasi three-dimensional design, rely on to S1And S2The analysis result and blade three-dimensional modeling module of stream interface design data
Construct the initial three dimendional blade geometry passages structure of fan；
Step 3: full three dimensional design
Using the obtained initial three dimendional blade geometry passages of quasi three-dimensional design, rely on the blade three-dimensional pneumatic of high-order moment at
Type method, by implementing the optimization design of blade path further based on Three Dimensional Viscous CFD technology under grade environmental condition to complete
Design objective；Wherein, Optimal Design Strategies are as follows: using fan grade adiabatic efficiency as objective function, with fan blade feature geometries ginseng
Number is optimization design variable, carries out optimizing using genetic algorithm plus gradient algorithm, final to obtain arc in the blade with universality
Line characteristic parameter and the geometry angular dimensions regularity of distribution, and these parameter distribution rules with universality are expressed as relevant height
Order polynomial mathematical model.
2. super or transonic speed axial fan designs method, the feature according to claim 1 based on high-order moment exists
In the step 1, fan overall performance data include adiabatic efficiency, overall pressure tatio, the pressure of middle path position blade front and rear edge,
Temperature, Mach number.
3. super or transonic speed axial fan designs method, the feature according to claim 1 based on high-order moment exists
In the step 1, main geometric parameter includes the number of blade, blade front and rear edge position, fan internal diameter and internal diameter.
4. super or transonic speed axial fan designs method, the feature according to claim 1 based on high-order moment exists
In the fan blade feature geometries parameter be blade in camber line characteristic parameter and geometry angular dimensions.
5. super or transonic speed axial fan designs method, the feature according to claim 1 based on high-order moment exists
In the high-order moment mathematical model are as follows:
Blade geometry angle and the relational expression of the high relative position of leaf are as follows:
H=A + B*β + C*β2 + D*β3 + E*β4 + F*β5+ G*β6,
Wherein, β is corresponding leaf exhibition position blade inlet edge or trailing edge geometry angle, and H is the relative position from blade root to blade tip, and A ~ F divides
It Wei not corresponding multinomial coefficient；
Camber line formula in each section blade profile:
V=A + B*U + C*U2 + D*U3 + E*U4 + F*U5 + G*U6,
Wherein, U is from leading edge to trailing edge along the relative position in chord length direction, and V is the height of corresponding middle arc positions, A ~ G
Respectively corresponding multinomial coefficient.
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