CN110173459A - Blade and its formative method and turbine - Google Patents
Blade and its formative method and turbine Download PDFInfo
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- CN110173459A CN110173459A CN201910435055.8A CN201910435055A CN110173459A CN 110173459 A CN110173459 A CN 110173459A CN 201910435055 A CN201910435055 A CN 201910435055A CN 110173459 A CN110173459 A CN 110173459A
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- 238000005452 bending Methods 0.000 claims abstract description 127
- 230000005484 gravity Effects 0.000 claims abstract description 6
- 238000010276 construction Methods 0.000 claims abstract description 5
- 238000006243 chemical reaction Methods 0.000 claims description 4
- 238000005516 engineering process Methods 0.000 abstract description 8
- 239000011888 foil Substances 0.000 abstract description 6
- 239000000047 product Substances 0.000 description 52
- 239000007789 gas Substances 0.000 description 7
- 238000010586 diagram Methods 0.000 description 5
- 239000006227 byproduct Substances 0.000 description 3
- 239000012530 fluid Substances 0.000 description 3
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- 230000000149 penetrating effect Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor
- F03D1/06—Rotors
- F03D1/065—Rotors characterised by their construction elements
- F03D1/0675—Rotors characterised by their construction elements of the blades
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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
- F04D29/386—Skewed blades
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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
- F04D29/388—Blades characterised by construction
-
- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to blade shape construction technical field more particularly to blades and its formative method and turbine.Blade includes the blade profile section of different radii position, and for all blade profile sections by radial location along product superimposing thread series connection, product superimposing thread passes through the center of gravity of all blade profile sections；Product superimposing thread includes n concatenated bending segments；Bending segment includes concatenated first bending and the second bending, and first bends the overbending direction with the second bending on the contrary, n >=1；The overbending direction of two bendings connected between two neighboring bending segment is opposite.Product superimposing thread is designed as multiple bending segment series connection in the present invention, and each bending segment series connection forms the structure of fluctuating, and entire product superimposing thread forms multiple fluctuatings, and blade profile section constructs concaveconvex structure along the blade inlet edge that product superimposing thread heap poststack obtains naturally.This technology is constructed the concaveconvex structure of blade inlet edge using the fluctuating of product superimposing thread, improves blade good hydrodynamic performance under the big angle of attack under the premise of not changing vane foil.
Description
Technical field
The present invention relates to blade shape construction technical field more particularly to blades and its formative method and turbine.
Background technique
Gas turbine is the major technologies and equipment realized high efficiency of energy clean conversion and ensure national energy security, including boat
Empty engine, naval vessel with or the gas turbine of power generation etc..Gas turbine is made of compressor, combustion chamber and turbine three parts.
In gas-turbine unit, compressor (compressor) improves air pressure to air work done using high-speed rotating blade
Power.The energy being accumulated in fluid media (medium) is converted into the machine of mechanical work, also known as turbine by turbine (turbine).From inlet duct
After the air of entrance is compressed in compressor, it is mixed and burned into combustion chamber and with the fuel oil of penetrating, generates high temperature and pressure combustion
Gas.Combustion gas drives high speed rotation in expansion process, and energy is changed into turbine function.Turbine drives compressor inspiration air to go forward side by side
Thus row compression, engine carry out continuous sex work.Wherein, compressor and turbine are made of blade, under the big angle of attack,
All there are problems that stall causes efficiency quickly to reduce.Especially for compressor, in the case where the big angle of attack, stall is also easy to
Lead to surge phenomenon, damage compressor or even gas turbine in a short time, gas turbine must in design and operational process
It must prevent compressor stall surge.Therefore, the big angle of attack of blade is paid much attention in the design of impeller rotating machinery especially compressor
Performance.
Have good hydrodynamic characters under the big angle of attack to improve blade, as shown in figure 3, in the leading edge of blade
Install convex block additional, but this blade is difficult to apply in compressor, blade profile employed in compressor actual design, is all by big
Amount experiment is formed by mature specification.If installing convex block additional, Compressor airfoil shape will be changed, to generate it is difficult to predict after
Fruit.
Summary of the invention
(1) technical problems to be solved
The present invention be solve the problems, such as it is above-mentioned at least one, the present invention provides a kind of blades, and the present invention also provides one kind
Turbine, the present invention also provides a kind of formative methods of blade.
(2) technical solution
In order to solve the above technical problem, the present invention provides a kind of blades comprising the blade profile section of different radii position, institute
There is the blade profile section by radial location along product superimposing thread series connection, the long-pending superimposing thread passes through the center of gravity of all blade profile sections；It is described
Product superimposing thread includes n concatenated bending segments；The bending segment includes concatenated first bending and the second bending, first bending
Overbending direction with second bending is on the contrary, n >=1；The bending side of two bendings connected between two neighboring bending segment
To opposite.
Still retain the blade profile section at blade different radii in the art, product superimposing thread is designed as multiple bending segment strings
Connection, each bending segment are connected by the first bending, the second bending, form the structure of fluctuating, and really long-pending superimposing thread forms multiple fluctuatings, leaf
Type section constructs concaveconvex structure along the blade inlet edge that product superimposing thread heap poststack obtains naturally.To which this technology is not changing blade and blade
Under the premise of type, the concaveconvex structure of blade inlet edge is constructed using the fluctuating of product superimposing thread, it is good under the big angle of attack to improve blade
Hydrodynamic performance.
In some embodiments, preferably, first bending and/or described second broken line or curve are bent to.Broken line
Has bending, curve also has bending, and the line style of bending promotes long-pending superimposing thread in fluctuations, blade profile section heap poststack is facilitated to form leaf
Piece leading edge has concaveconvex structure, improves blade good hydrodynamic performance under the big angle of attack.
In some embodiments, preferably, when first bends and/or second is bent to broken line, in different bending segments, folding
Angle between two sides of line is similar and different.Angle difference then forms the different product superimposing thread of undulating state, can be formed and more be accorded with
Close the blade of good flow power performance under the big angle of attack.Angle is identical, is formed and equally floats or lie prostrate the product superimposing thread fallen, certain
In the case of, it is more suitable for good flow power performance under the big angle of attack.
In some embodiments, preferably, bent in different bending segments when first bends and/or second is bent to curve
Curvature of a curve is identical or different.Curvature is different, and radius of curvature may be the same or different, and forms the different product superimposing thread of fluctuating quantity, can
Form the blade for more meeting good flow power performance under the big angle of attack.Curvature is identical, and radius of curvature is identical, is formed and is equally floated
Or the product superimposing thread that volt is fallen is more suitable for good flow power performance under the big angle of attack in some cases.
In some embodiments, preferably, the long-pending superimposing thread is along blade axial bending, or, along the circumferential skewing of blade.Two
The different curve form of kind forms different blade inlet edge or blade circumferential direction concaveconvex structure to provide blade of different shapes.
In some embodiments, preferably, the line style of the long-pending superimposing thread includes: folding line, wave, sine curve, B-
Spline curve or Nurbs curve.It is linear to provide a variety of long-pending superimposing threads, to obtain the blade of different shapes, forms different blades
Leading edge concaveconvex structure.
In some embodiments, preferably, concave-convex surface at blade inlet edge.The concavo-convex knot of blade inlet edge or blade circumferential direction
Structure promotes blade when significantly rotating, will not stall.Be applied on press machine be not in surge phenomenon.
The present invention also provides a kind of turbines, use above-mentioned blade.Still retain blade different radii in the art
Product superimposing thread is designed as multiple bending segments and connected by the blade profile section at place, and each bending segment is connected by the first bending, the second bending, shape
At the structure of fluctuating, really long-pending superimposing thread forms multiple fluctuatings, the blade inlet edge or blade that blade profile section is obtained along product superimposing thread heap poststack
Circumferential nature constructs concaveconvex structure.To which this technology utilizes the fluctuating structure of product superimposing thread under the premise of not changing vane foil
The concaveconvex structure or blade circumferential nature for producing blade inlet edge construct concaveconvex structure, and it is good under the big angle of attack to improve blade
Hydrodynamic performance.
In some embodiments, preferably, the turbine includes: compressor, turbine or wind energy conversion system.The turbine is applied to respectively
In specific equipment, blade good mobilization dynamic performance under the big angle of attack can be improved, it will not stall.
The present invention also provides a kind of formative methods of blade comprising:
Construct product superimposing thread；
Construct the blade profile section of different radii position；
All blade profile sections are connected according to radial location along the long-pending superimposing thread, the long-pending superimposing thread passes through all leaves
The center of gravity of type section, construction obtain the blade, and the leading edge or blade of the blade are circumferentially in concaveconvex structure.
(3) beneficial effect
Still retain the blade profile section at blade different radii in technical solution provided by the invention in the art, product is folded
Line is designed as multiple bending segment series connection, and each bending segment is connected by the first bending, the second bending, forms the structure of fluctuating, entirely
Product superimposing thread forms multiple fluctuatings, and the blade inlet edge or blade circumferential nature that blade profile section is obtained along product superimposing thread heap poststack construct bumps
Structure.To which this technology constructs blade inlet edge or blade under the premise of not changing vane foil, using the fluctuating of product superimposing thread
Circumferential concaveconvex structure, improves blade good hydrodynamic performance under the big angle of attack.It is particularly suitable for compressor blade.
Detailed description of the invention
Fig. 1 is product superimposing thread schematic diagram in some embodiments in the prior art；
Fig. 2 is blade schematic diagram made of stacking in the prior art by product superimposing thread in Fig. 1；
Fig. 3 is to increase the schematic diagram of concaveconvex structure in leading edge in the prior art；
Fig. 4 is that product superimposing thread is wave schematic diagram in the embodiment of the present invention 5；
Fig. 5 is blade schematic diagram made of the present invention is stacked by product superimposing thread in Fig. 4.
In figure: 1, blade inlet edge.
Specific embodiment
With reference to the accompanying drawings and examples, specific embodiments of the present invention will be described in further detail.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can
To be mechanical connection, it is also possible to be electrically connected；It can be directly connected, can also can be indirectly connected through an intermediary
Connection inside two elements." first " " second " " third " " the 4th " does not represent any sequence relation, merely for convenience
The differentiation carried out is described.For the ordinary skill in the art, above-mentioned term can be understood in the present invention with concrete condition
In concrete meaning."upper" "lower" is defined with specific location in product use in text.
Aiming at the problem that current gas compressor in gas turbine, turbine are easy to produce stall under the big angle of attack, the present invention is provided
Blade and its formative method and turbine.
Product, method etc. will be described in detail by basic engineering, extension design and alternative design below.
The present invention is provided in a kind of blade, as shown in Figure 4 and Figure 5 comprising the blade profile section of different radii position, Suo Youye
For type section by radial location along product superimposing thread series connection, product superimposing thread passes through the center of gravity of all blade profile sections；Product superimposing thread includes n concatenated curved
Trisection；Bending segment includes concatenated first bending and the second bending, the overbending direction of the first bending and the second bending on the contrary, n >=
1；It connects in such a way that the first bending is connected with the second bending between two neighboring bending segment, company, institute between two neighboring bending segment
The overbending direction of two bendings connect is opposite.
Bending segment includes the first bending and the second bending, and the first bending, the second overbending direction bent are on the contrary, to each
Bending segment forms undulating state, after the series connection of multiple bending segments, then forms the product superimposing thread for having multiple fluctuatings, different radii position
The blade profile section set forms ups and downs blade along product superimposing thread heap poststack by radial location, and the leading edge of blade has concave-convex knot
Structure.
First bending, the second overbending direction bent are on the contrary, such as: the first bending openings to the left, i.e., are bent to the right,
So concatenated second bending is then bent to the left, and opening is to the right.Based on common knowledge, the second bending part of concatenated first bending is not
It can be oppositely arranged, connect along radial direction or circumferencial direction.
Two neighboring bending segment still defers to the rule successively to rise and fall when connecting, the first bending of next bending segment with it is upper
Second bending series connection of one bending segment, thus formed next bending segment the first bending and a upper bending segment it is second curved
Bending folding is contrary, in undulated.
Product superimposing thread molded line, complicated linetype number of cycles and complicated linetype periodic amplitude by (compressor) blade blade profile,
The number of blade and blade angle determine.Molded line is chosen using Fluid Mechanics Computation calculation method or experimental method.
Compared to the blade for accumulating superimposing thread in the prior art and being formed for straight line as illustrated in fig. 1 and 2, in the art still
Retain the blade profile section at blade different radii, product superimposing thread be designed as the series connection of multiple bending segments, each bending segment by the first bending,
Second bending series connection, forms the structure of fluctuating, and really long-pending superimposing thread forms multiple fluctuatings, and blade profile section is obtained along product superimposing thread heap poststack
Blade inlet edge 1 constructs concaveconvex structure naturally.To which this technology utilizes product superimposing thread under the premise of not changing vane foil
It rises and falls and constructs the concaveconvex structure of blade inlet edge 1, improve blade good hydrodynamic performance under the big angle of attack.
In some embodiments, the first bending can be broken line, can also be curve, even if part first in the same long-pending superimposing thread
It is bent to broken line, another part first is bent to curve.Similarly, the second bending can be broken line, can also be curve, even if same
Part second is bent to broken line in product superimposing thread, and another part second is bent to curve.
Moreover, in various embodiments, concatenated first bending and the second bending can connect for broken line and curve,
It can also connect, can also connect with curve for curve with broken line for broken line.
No matter using above-mentioned any series system, mode is bent, only long-pending superimposing thread to be formed is undulated, then belongs to
The product superimposing thread line style of the application protection, belongs within protection scope.
In addition, on the basis of based on the first bending, the second different bending form of bending use is previously mentioned, all uses
In the first bending or the second bending of broken line, first while and second while forms broken line, the angle of broken line can difference, certainly may be used
With identical.
Similarly, on the basis of based on the first bending, the second different bending form of bending use is previously mentioned, all uses
In the first bending or the second bending of curve, the curvature angles of curve, radius of curvature can be identical, can also be different.
It has been previously mentioned the bending segment form of diversified forms, as long as constituting the product superimposing thread of undulating state, has belonged to the application
Protection scope.In practical applications, technical staff can select reasonable, suitable first bending, second curved according to the actual situation
Folding forms bending segment, and then series connection forms product superimposing thread, and best flow dynamics are obtained in the case where the big angle of attack to reach
Energy.
Several long-pending superimposing threads are provided below based on the different shape of the first bending, the second bending:
Embodiment 1:
First bending, the second bending are broken line, in broken line first while, second while angle it is identical, bending segment is along linear string
Connection.
Embodiment 2:
First bending, the second bending are curve, and the first bending and the second bending surround a sinusoidal cycles, product superimposing thread
Line style is sinusoidal line.Along section along axial bending, the leading edge of the blade of formation is concaveconvex structure.
Embodiment 3:
First is bent to broken line, and second is bent to curve, in broken line first while, second while angle it is identical, bending segment is along week
To series connection, product superimposing thread is circumferentially bent, to form circumferential concaveconvex structure
Embodiment 4:
First is bent to broken line, and second is bent to curve, in the broken lines of all first bendings first while, second while angle not
Exactly the same, the radius of curvature of the curve of all second bendings is not all the same.Product superimposing thread is circumferentially bent, to form circumferential bumps
Structure.
Embodiment 5
As shown in Figures 4 and 5, first it is bent to curve, second is bent to curve, and product superimposing thread is wave.The blade of formation
Leading edge be concaveconvex structure.
In other examples, product superimposing thread line style include: folding line, wave, sine curve, B- spline curve or
The combination of Nurbs curve or a variety of line styles.
B- spline curve (B-spline curve) refers to the special table of one kind in the sub- subject numerical analysis of mathematics
Show form.Definition: known n+1 control point Pi (i=0,1,2 ..., n), then the expression formula that can define k B-spline curves is P
(u)=∑ (n, i=0) PiNi, k (u).B-Spline (B-spline): referring to route and construct a curve, at one or more
It is interpolated between more points.
NURBS is the abbreviation of Non-Uniform Rational B-Splines, is the meaning of non-uniform rational B-spline.
Heterogeneity refers to that the range of the influence power of a control vertex can change.Rational (reasonable): refer to each NURBS object
Body can be defined with rational polynominal primitive formula.It is a kind of formative method for specially doing curved face object.
Sine curve or sine wave (Sinusoid/Sine wave) are a kind of sine ratios in mathematics trigonometric function
The curve of example.Sine curve is represented by y=Asin (ω x+ φ)+k, is defined as function y=Asin (ω x+ φ)+k at right angle
Image on coordinate system, wherein sin is sinusoidal symbol, and x is the numerical value in rectangular coordinate system x-axis, and y is in same rectangular coordinate system
The corresponding y value of superior function, k, ω and φ are constant (k, ω, φ ∈ R and ω ≠ 0).Sine curve is a wave.
Concave-convex surface at the blade inlet edge 1 obtained in above-mentioned various embodiments, to improve fluid of the blade under the big angle of attack
Power performance.
The present invention also provides a kind of turbines, use any of the above-described kind of blade.The present invention is suitable for all folded by product
The blade of line series connection blade profile, such as compressor, turbine, pneumatic equipment bladess, are particularly suitable for compressor blade.
Still retain the blade profile section at blade different radii in the art, product superimposing thread is designed as multiple bending segment strings
Connection, each bending segment are connected by the first bending, the second bending, form the structure of fluctuating, and really long-pending superimposing thread forms multiple fluctuatings, leaf
Type section constructs concaveconvex structure or circumferential concaveconvex structure along the blade inlet edge 1 that product superimposing thread heap poststack obtains naturally.To this technology
Under the premise of not changing vane foil, the concaveconvex structure or blade circumferential direction of blade inlet edge 1 are constructed using the fluctuating of product superimposing thread
Concaveconvex structure improves blade good hydrodynamic performance under the big angle of attack.
The turbine includes: compressor, turbine or wind energy conversion system etc., in other embodiments, as long as using blade, and face
The turbine of stall problem, can use the blade under big situations of attack.
The present invention also provides a kind of formative methods of blade comprising:
Step 110, product superimposing thread is constructed；
The product superimposing thread is connected in series in undulated by n bending segment；Bending segment includes that concatenated first bending and second are curved
The overbending direction of folding, the first bending and the second bending is on the contrary, n >=1；It is curved with the first bending and second between two neighboring bending segment
The connected mode of folding is connected.After the series connection of multiple bending segments, then the product superimposing thread that line style there are multiple fluctuatings, different radii position are formed
Blade profile section form ups and downs blade along product superimposing thread heap poststack by radial location, the leading edge or blade of blade circumferentially exist
Concaveconvex structure.
Step 120, the blade profile section of different radii position is constructed；
Step 130, all blade profile sections are connected according to radial location along product superimposing thread, product superimposing thread passes through the weight of all blade profile sections
The heart, construction obtain blade, and the leading edge or blade of blade are circumferentially in concaveconvex structure.
Still retain the blade profile section at blade different radii in the art, product superimposing thread is designed as multiple bending segment strings
Connection, each bending segment are connected by the first bending, the second bending, form the structure of fluctuating, and entire product superimposing thread forms multiple fluctuatings, leaf
Type section constructs concaveconvex structure along the obtained blade inlet edge 1 of product superimposing thread heap poststack or blade circumferential nature.To which this technology is not
Under the premise of changing vane foil, the concaveconvex structure of blade inlet edge 1 or blade circumferential direction is constructed using the fluctuating of product superimposing thread, is improved
Blade good hydrodynamic performance under the big angle of attack.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Within mind and principle, any modification, equivalent replacement, improvement and so on be should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of blade, which is characterized in that the blade profile section including different radii position, all blade profile sections press radial location edge
Product superimposing thread series connection, the long-pending superimposing thread pass through the center of gravity of all blade profile sections；
The long-pending superimposing thread includes n concatenated bending segments；The bending segment includes that concatenated first bending and second bend, described
The overbending direction of first bending and second bending is on the contrary, n >=1；
The overbending direction of two bendings connected between two neighboring bending segment is opposite.
2. blade as described in claim 1, which is characterized in that it is described first bending and/or described second be bent to broken line or
Curve.
3. blade as claimed in claim 2, which is characterized in that different curved when first bends and/or second is bent to broken line
In trisection, the angle between two sides of broken line is similar and different.
4. blade as claimed in claim 2, which is characterized in that different curved when first bends and/or second is bent to curve
Bent curvature of a curve is identical or different in trisection.
5. blade as described in claim 1, which is characterized in that the long-pending superimposing thread is along blade axial bending, or, along the week of blade
To bending.
6. blade as described in claim 1, which is characterized in that the line style of the long-pending superimposing thread includes: folding line, wave, just
Chord curve, B- spline curve or Nurbs curve.
7. blade as claimed in any one of claims 1 to 6, which is characterized in that concave-convex surface or blade are circumferential at blade inlet edge
Concave-convex surface.
8. a kind of turbine, which is characterized in that it uses any one of claim 1-7 blade.
9. turbine as claimed in claim 8, which is characterized in that the turbine includes: compressor, turbine or wind energy conversion system.
10. a kind of formative method of any one of claim 1-7 blade characterized by comprising
Construct product superimposing thread；
Construct the blade profile section of different radii position；
All blade profile sections are connected according to radial location along the long-pending superimposing thread, the long-pending superimposing thread passes through all blade profile sections
Center of gravity, construction obtain the blade, the leading edge or blade of the blade are circumferentially in concaveconvex structure.
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| CN201910435055.8A CN110173459A (en) | 2019-05-23 | 2019-05-23 | Blade and its formative method and turbine |
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| CN201910435055.8A CN110173459A (en) | 2019-05-23 | 2019-05-23 | Blade and its formative method and turbine |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110497036A (en) * | 2019-08-28 | 2019-11-26 | 西安陕鼓动力股份有限公司 | The formative method and its processing method of movable vane flute profile abnormity chamfering |
| CN110985410A (en) * | 2019-12-19 | 2020-04-10 | 中国航空发动机研究院 | Transonic compressor plane cascade with bionic wavy structure leading edge |
| CN112610513A (en) * | 2020-12-04 | 2021-04-06 | 北京航空航天大学 | Non-uniform wave-shaped front edge stationary blade and modeling method thereof |
| CN112855284A (en) * | 2021-01-18 | 2021-05-28 | 西北工业大学 | Construction method of low-pressure turbine stator blade wave front edge |
| CN113048007A (en) * | 2019-12-26 | 2021-06-29 | 江苏金风科技有限公司 | Blade, wind generating set and method for reducing blade breathing effect |
| CN113323796A (en) * | 2021-06-29 | 2021-08-31 | 中国科学院工程热物理研究所 | Bionic leading edge wind power blade and optimal design method |
| CN113669194A (en) * | 2021-08-09 | 2021-11-19 | 中国科学院工程热物理研究所 | Flow separation control method based on bionic concave-convex front edge structure |
| CN114688083A (en) * | 2022-04-28 | 2022-07-01 | 宁波方太厨具有限公司 | Blade, impeller with blade, fan system and range hood |
| CN114962329A (en) * | 2022-05-27 | 2022-08-30 | 哈尔滨工程大学 | Novel compressor rotor clearance structure and application |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1564374A1 (en) * | 2004-02-12 | 2005-08-17 | Siemens Aktiengesellschaft | Turbine blade for a turbomachine |
| WO2009103528A2 (en) * | 2008-02-19 | 2009-08-27 | Paolo Pietricola | Parametric blades with either sinusoidal lean or airfoils with arcs of ellipses |
| CN103452904A (en) * | 2012-06-01 | 2013-12-18 | 航空技术空间股份有限公司 | S-shaped profile blade of axial turbomachine compressor, corresponding compressor and turbomachine |
| GB2507493A (en) * | 2012-10-30 | 2014-05-07 | Solyvent Flakt Ab | Air movement fan with protrusions on the leading and trailing edges of the blades |
| CN204828043U (en) * | 2015-08-03 | 2015-12-02 | 江森自控楼宇设备科技(无锡)有限公司 | Blade |
| CN105275854A (en) * | 2015-10-26 | 2016-01-27 | 日本电产凯宇汽车电器（江苏）有限公司 | Electronic fan assembly for automobile radiator |
| CN107965352A (en) * | 2017-12-26 | 2018-04-27 | 北京全四维动力科技有限公司 | The bent blades of water erosion danger, leaf grating and industrial steam turbine using it can be reduced |
| CN108980106A (en) * | 2018-07-25 | 2018-12-11 | 清华大学 | compressor blade and compressor |
-
2019
- 2019-05-23 CN CN201910435055.8A patent/CN110173459A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1564374A1 (en) * | 2004-02-12 | 2005-08-17 | Siemens Aktiengesellschaft | Turbine blade for a turbomachine |
| WO2009103528A2 (en) * | 2008-02-19 | 2009-08-27 | Paolo Pietricola | Parametric blades with either sinusoidal lean or airfoils with arcs of ellipses |
| CN103452904A (en) * | 2012-06-01 | 2013-12-18 | 航空技术空间股份有限公司 | S-shaped profile blade of axial turbomachine compressor, corresponding compressor and turbomachine |
| GB2507493A (en) * | 2012-10-30 | 2014-05-07 | Solyvent Flakt Ab | Air movement fan with protrusions on the leading and trailing edges of the blades |
| CN204828043U (en) * | 2015-08-03 | 2015-12-02 | 江森自控楼宇设备科技(无锡)有限公司 | Blade |
| CN105275854A (en) * | 2015-10-26 | 2016-01-27 | 日本电产凯宇汽车电器（江苏）有限公司 | Electronic fan assembly for automobile radiator |
| CN107965352A (en) * | 2017-12-26 | 2018-04-27 | 北京全四维动力科技有限公司 | The bent blades of water erosion danger, leaf grating and industrial steam turbine using it can be reduced |
| CN108980106A (en) * | 2018-07-25 | 2018-12-11 | 清华大学 | compressor blade and compressor |
Non-Patent Citations (1)
| Title |
|---|
| 黄文俊等: "基于 SolidWorks 的汽轮机扭曲叶片造型研究", 《机械设计与制造》 * |
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| CN110497036B (en) * | 2019-08-28 | 2020-10-16 | 西安陕鼓动力股份有限公司 | Molding method and processing method of movable blade tooth-shaped special-shaped chamfer |
| CN110497036A (en) * | 2019-08-28 | 2019-11-26 | 西安陕鼓动力股份有限公司 | The formative method and its processing method of movable vane flute profile abnormity chamfering |
| CN110985410A (en) * | 2019-12-19 | 2020-04-10 | 中国航空发动机研究院 | Transonic compressor plane cascade with bionic wavy structure leading edge |
| CN113048007A (en) * | 2019-12-26 | 2021-06-29 | 江苏金风科技有限公司 | Blade, wind generating set and method for reducing blade breathing effect |
| CN112610513B (en) * | 2020-12-04 | 2021-08-31 | 北京航空航天大学 | Non-uniform wave-shaped front edge stationary blade and modeling method thereof |
| CN112610513A (en) * | 2020-12-04 | 2021-04-06 | 北京航空航天大学 | Non-uniform wave-shaped front edge stationary blade and modeling method thereof |
| CN112855284A (en) * | 2021-01-18 | 2021-05-28 | 西北工业大学 | Construction method of low-pressure turbine stator blade wave front edge |
| CN113323796A (en) * | 2021-06-29 | 2021-08-31 | 中国科学院工程热物理研究所 | Bionic leading edge wind power blade and optimal design method |
| CN113669194A (en) * | 2021-08-09 | 2021-11-19 | 中国科学院工程热物理研究所 | Flow separation control method based on bionic concave-convex front edge structure |
| CN114688083A (en) * | 2022-04-28 | 2022-07-01 | 宁波方太厨具有限公司 | Blade, impeller with blade, fan system and range hood |
| CN114688083B (en) * | 2022-04-28 | 2023-02-28 | 宁波方太厨具有限公司 | Blade, impeller applying same, fan system and range hood |
| CN114962329A (en) * | 2022-05-27 | 2022-08-30 | 哈尔滨工程大学 | Novel compressor rotor clearance structure and application |
| CN114962329B (en) * | 2022-05-27 | 2024-04-26 | 哈尔滨工程大学 | Compressor rotor clearance structure and application |
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