CN106593540B - A kind of turbo blade and the turbine being made of the turbo blade - Google Patents
A kind of turbo blade and the turbine being made of the turbo blade Download PDFInfo
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- CN106593540B CN106593540B CN201710062948.3A CN201710062948A CN106593540B CN 106593540 B CN106593540 B CN 106593540B CN 201710062948 A CN201710062948 A CN 201710062948A CN 106593540 B CN106593540 B CN 106593540B
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- 230000001965 increasing effect Effects 0.000 description 3
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- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 description 2
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63H—MARINE PROPULSION OR STEERING
- B63H1/00—Propulsive elements directly acting on water
- B63H1/02—Propulsive elements directly acting on water of rotary type
- B63H1/12—Propulsive elements directly acting on water of rotary type with rotation axis substantially in propulsive direction
- B63H1/14—Propellers
- B63H1/26—Blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
-
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
-
- 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
- F03B—MACHINES OR ENGINES FOR LIQUIDS
- F03B3/00—Machines or engines of reaction type; Parts or details peculiar thereto
- F03B3/12—Blades; Blade-carrying rotors
-
- 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
- F03B—MACHINES OR ENGINES FOR LIQUIDS
- F03B3/00—Machines or engines of reaction type; Parts or details peculiar thereto
- F03B3/12—Blades; Blade-carrying rotors
- F03B3/121—Blades, their form or construction
-
- 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
- F03D3/00—Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor
- F03D3/06—Rotors
- F03D3/061—Rotors characterised by their aerodynamic shape, e.g. aerofoil profiles
-
- 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
- F03D3/00—Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor
- F03D3/06—Rotors
- F03D3/062—Rotors characterised by their construction elements
-
- 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
- F04D29/18—Rotors
-
- 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
- F04D29/18—Rotors
- F04D29/185—Rotors consisting of a plurality of wheels
-
- 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
-
- 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
- Y02E10/20—Hydro energy
-
- 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
- Y02E10/74—Wind turbines with rotation axis perpendicular to the wind direction
-
- 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
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
- Y02P70/50—Manufacturing or production processes characterised by the final manufactured product
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Chemical & Material Sciences (AREA)
- Sustainable Energy (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Ocean & Marine Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Hydraulic Turbines (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention provides a kind of turbo blade and the turbine being made of the turbo blade, using the concave curved of coplanar with rotary shaft and disjoint smooth no inflection point into the first spoon of blade, the second spoon of blade or third blade curved surface.And it is combined by more than spoon of blade and forms the turbine blade arrangements such as single blade curved surface, multiple-blade curved surface, multistage connected single blade curved surface, multistage connected multiple-blade curved surface, multistage connected composite blading curved surface.The turbine of the present invention is driven using the vortex artificially manufactured in fluid.The present invention proposes the concept of the surface of second order, and form turbine and turbine group using the turbo blade that second order spoon of blade is formed, by the coupling for being vortexed flow field, that is the rotary motion manufacture vortex field of blade in a fluid, Coriolis force is generated in flow field and blade is pushed to accelerate rotation by effect of boundary layer, positive feedback is formed between vortex and blade, high-energy conversion ratio is reached with this.If being used in the turbine group of gas turbine, it can also additionally increase the thermal efficiency.
Description
Technical field
The present invention relates to fluid dynamics field, specifically, being related to a kind of turbo blade and by the turbo blade group
Into turbine.The technology is also applied for the design of the slurry wing blade of ship and flying object etc..
Background technology
Turbine blade surface is the space curved surface for having three-dimensional character, true inside turbomachinery in practical operation
Flow it is extremely complex, spatially show as flowing it is three-dimensionality, show as in time flowing non-stationarity, it is attached in blade
Near to have boundary-layer feature, vane end faces nearby will appear the flow-disturbings such as attached face whirlpool again.Commonly used in analyze fluid motion Na Wei-this
Lentor equation, which is difficult to use in turbine design, solves the problems, such as so complexity.Nevertheless, we still can be from basic
The common defects of popular turbine technology are found in mechanics principle.First, popular turbine technology substantially uses turbo blade
Change fluid direction of motion, while obtain the thrust of negative direction, and as the rotation of power maintenance turbine.Under this method,
Fluid leaves the speed of turbo blade and the obtained propulsive force of turbo blade and the velocity correlation rotated, and turbine propulsion power is bigger,
Rotation is faster, it is meant that fluid leaves faster.Fluid leaves means that remaining kinetic energy is bigger in fluid sooner.It is so this
Considerable energy loss is inevitably brought using the turbine technology of fluid propulsive thrust.Secondly, popular turbine technology is difficult to
The problem avoided is different with the radius of turn of blade each point, and linear velocity is also different or even difference is huge, especially with wheel footpath
The wind wheel of huge turbine such as wind-power electricity generation is very.Such as the blade close to rotor shaft, speed is very slow, and wind can not push, several
It can only be to bypass here, so as to be difficult to transmit energy, and at the tip of wind wheel, fast obtain even generates speed far more than wind speed again
Back pressure, that is, vacuum side of blade have caught up with air-flow, and the angle of attack causes the air pressure of vacuum side of blade to be more than positive air pressure, cause very big
Rotational resistance.Therefore the difference of linear velocity can substantially reduce turbine efficiency.Third, popular turbine technology without
Method avoids the energy loss that centrifugal force is brought.Fluid leaves turbine under the action of the centrifugal force certainly will be with the upward speed of rotary cutting
Component, this portion of energy inevitably have lost.4th, in the applications such as gas turbine, the fluid of discharge contains a large amount of remaining
Heat is not effectively transformed as mechanical energy, therefore also reduces temperature before whirlpool, also reduces gas turbine proficiency.5th, turbine leaf
It is contradictory between the number and efficiency of piece, especially using the wind wheel of wind-power electricity generation as protrusion.The projection gross area or wind of wind wheel blade
It is an index for being difficult to improve to take turns solidity, and rotor solidity is not high, certainly will lead to the loss of wind energy.And rotor solidity is improved, again
Windage can be caused to increase, wind speed reduces, and reduces wind wheel efficiency.In view of this, the present invention propose a kind of novel turbine blade and
The turbine being made of the turbo blade, to overcome disadvantages described above.
Invention content
The present invention provides a kind of turbo blade, and when ignoring vane thickness, spoon of blade is the first spoon of blade, the second leaf
One in piece curved surface or third blade curved surface, the first curve (AB) is coplanar with rotary shaft and disjoint smooth no inflection point
Concave curve, the concave surface of the first curve is towards rotary shaft, and the endpoint of the first curve close to rotary shaft is known as proximal end, and the first curve is separate
The endpoint of rotary shaft is known as distal end, wherein, the first spoon of blade at least meets following curved surface features：First curve is revolved around rotary shaft
It circles to form the plane of reference (M), the first curve extends the first spoon of blade (M1) to direction of rotation side, on the first curve begins
There is burble point eventually, on the first curve, the curved section between burble point and proximal end extends to form intrinsic first spoon of blade, point
The additional surface to be formed is rotated around rotary shaft from the curved section between point and distal end to overlap with the plane of reference, the burble point is around rotation
The circular arc line that axis rotation generates is known as defiber, and the defiber forms the boundary of intrinsic first spoon of blade and additional surface
Line, the point on intrinsic first spoon of blade are not overlapped and are intersected with the plane of reference, take up an official post by intrinsic first spoon of blade
A bit (P2), the second curve is formed on intrinsic first spoon of blade, any point and the distance phase of rotary shaft on the second curve
Deng, by any point on intrinsic first spoon of blade, the formation third curve on intrinsic first spoon of blade, third curve
On any point be on intrinsic first spoon of blade in any point and the same plane of rotary shaft, it is excessively described intrinsic
The normal of any point and the plane of reference form intersection point (Q) on first spoon of blade, if also, intrinsic first spoon of blade take up an official post
It is a little moved along the second curve to direction of rotation side, then with any point on intrinsic first spoon of blade and the intersection point
Between distance gradually increase, the second bent curvature of a curve also gradually increases, if also, intrinsic first spoon of blade take up an official post
A little to be moved along third curve to rotary axis direction, the intersection point (Q) is also moved simultaneously along the homologous thread track on the plane of reference,
Then as distance gradually increases between any point and the intersection point on intrinsic first spoon of blade, the song of the third curve
The difference of the curvature of this of rate and point of intersection homologous thread track also gradually increases, and traverses entire intrinsic first spoon of blade, institute
The normal for stating any point on intrinsic first spoon of blade intersects always with the plane perpendicular to rotary shaft；Intrinsic first blade is bent
Face, the first curve, defiber and additional surface collectively form the first spoon of blade；Wherein, the second spoon of blade at least meet with
Lower surface camber feature：When rotary shaft is vertical, takes up an official post in the plane of reference and take the 4th curve (ST) of one article of continuously smooth, and the 4th is bent
Any two points are different in the height for being parallel to rotary axis direction on line, also, always have on the 4th curve unique a little with the
Any point on one curve is identical in the height for being parallel to rotary axis direction, will be parallel to rotary shaft on the first spoon of blade
The identical point of height keeps relative position constant and is rotated around rotary shaft on direction, until on the point and the 4th curve of the first curve
Highly identical point overlaps, and forms the second spoon of blade；Wherein, third blade curved surface at least meets following curved surface features：Third
Spoon of blade is the plane of reference formed that rotated a circle by the first curve around rotary shaft；Wherein, it is intrinsic if burble point is overlapped with distal end
First spoon of blade forms the first spoon of blade, if burble point is overlapped with proximal end, the first spoon of blade is equal to third blade
Curved surface.
Preferably, the first spoon of blade further includes the part reference for the side opposite to the direction of rotation that the first curve extends
When the tangent line of face and/or the first curve distal end is parallel with rotary shaft, the remote edge line of the first spoon of blade is along rotary shaft
The part cylindrical surface that direction is smoothly extended naturally；Second spoon of blade further include the first curve extend it is opposite to the direction of rotation
When the part plane of reference of side and/or the tangent line of the first curve distal end parallel with rotary shaft, the distal end of the second spoon of blade
The part cylindrical surface that edge line smoothly extends naturally along rotary axis direction；Third blade curved surface further includes the first curve distal end
Tangent line it is parallel with rotary shaft when, part that the remote edge line of third blade curved surface smoothly extends naturally along rotary axis direction
Cylinder.
Preferably, first curve is cycloid.
Preferably, any point is made on intrinsic first spoon of blade far from rotation on intrinsic first spoon of blade
During the radial motion of axis, on intrinsic first spoon of blade any point and the plane of reference the distance for being parallel to rotary axis direction with
The distance of the first spoon of blade any point and rotary shaft square is successively decreased in inverse proportion.
Preferably, the spoon of blade of turbo blade is the portion intercepts of first spoon of blade or the second spoon of blade
Face, the portion intercepts face are arbitrary between rotary shaft to defiber on first spoon of blade or the second spoon of blade
The part curved surface of interception, also, the portion intercepts face does not include defiber.
Preferably, the curve of the first curvilinear characteristic of multistage satisfaction concaves towards consistent and head and the tail and is sequentially connected with, and is formed multistage connected
First curve, and by the multistage be connected the first curve formed multistage connected first spoon of blade, multistage connected second spoon of blade,
The connected third blade curved surface of multistage, multistage connected composite blading curved surface,
Wherein, each section of curved surface features for all meeting the first spoon of blade of multistage connected first spoon of blade,
The each section of curved surface features for all meeting the second spoon of blade of connected second spoon of blade of multistage,
The each section of curved surface features for all meeting third blade curved surface of the connected third blade curved surface of multistage,
Each section of the connected composite blading curved surface of multistage all meets the first spoon of blade or the second spoon of blade or third leaf
The curved surface features of piece curved surface,
The spoon of blade is multistage connected first spoon of blade, multistage connected second spoon of blade, multistage connected third
One in spoon of blade or multistage connected composite blading curved surface.
Preferably, the position on turbo blade close to rotary shaft offers the deflector hole for penetrating turbo blade.
Preferably, it is formed multistage connected single as turbo blade using above-described multistage connected third blade curved surface
Blade turbine, and rotary shaft sets hole with turbo blade junction.
Preferably, using above-described multistage connected first spoon of blade or multistage connected second spoon of blade or multistage
It is connected composite blading curved surface as turbo blade, forms multistage connected multiple-blade turbine.
The present invention also provides a kind of single blade turbine, using above-described third blade curved surface as turbo blade, shape
Into single blade turbine, and rotary shaft sets hole with turbo blade junction.
Preferably, multiple single blade turbines of different sizes are coaxially stacked together, and form coaxial lamination turbine, also,
Along spoon of blade from rotary shaft to blade radial edge, the gap between blade is less and less.
The present invention also provides a kind of multiple-blade turbines, are made using above-described first spoon of blade or the second spoon of blade
For turbo blade, each blade by concave curved surface towards being concentrically fitted to together with rotary shaft in a manner of identical, wherein, all blades
First curve of curved surface is arranged on the plane of reference of the first curve rotation gained, along the circumferential direction evenly distributed around rotary shaft
Blade, the plane of reference or special cyclic structure that radial edges are integrated by seamless combination are fixed together to form multiple-blade whirlpool
Wheel.
Preferably, multiple multiple-blade turbines of different sizes are coaxially stacked together, formed multistage turbine, from rotary shaft to
Turbine radial edges, the gap between turbine are less and less.
Description of the drawings
By the way that embodiment is described with reference to accompanying drawings below, features described above of the invention and technological merit will become
More understand and be readily appreciated that.
Fig. 1 be represent the present embodiments relate to the first curve schematic diagram；
Fig. 2 be represent the present embodiments relate to the plane of reference stereoscopic schematic diagram；
Fig. 3 be represent the present embodiments relate to the part plane of reference stereoscopic schematic diagram；
Fig. 4 be represent the present embodiments relate to intrinsic first spoon of blade stereoscopic schematic diagram one；
Fig. 5 be represent the present embodiments relate to intrinsic first spoon of blade stereoscopic schematic diagram two；
Fig. 6 be represent the present embodiments relate to the 4th curve schematic diagram；
Fig. 7 be represent the present embodiments relate to intrinsic first spoon of blade stereoscopic schematic diagram three；
Fig. 8 be represent the present embodiments relate to multiple-blade turbine stereoscopic schematic diagram one；
Fig. 9 be represent the present embodiments relate to multiple-blade turbine schematic top plan view；
Figure 10 be represent the present embodiments relate to multiple-blade turbine stereoscopic schematic diagram two；
Figure 11 be represent the present embodiments relate to multiple-blade turbine stereoscopic schematic diagram three；
Figure 12 be represent the present embodiments relate to single blade turbine stereoscopic schematic diagram；
Figure 13 be represent the present embodiments relate to coaxial lamination turbine stereoscopic schematic diagram；
Figure 14 be represent the present embodiments relate to multistage turbine stereoscopic schematic diagram；
Figure 15 be represent the present embodiments relate to hybrid turbine stereoscopic schematic diagram；
Figure 16 be represent the present embodiments relate to multistage be connected the schematic diagram of the first curve；
Figure 17 be represent the present embodiments relate to deflector hole schematic diagram.
Specific embodiment
The embodiment of a kind of turbine and turbo blade of the present invention described below with reference to the accompanying drawings.This field it is general
Logical technical staff will recognize, without departing from the spirit and scope of the present invention, can use a variety of different modes
Or combination is modified described embodiment.Therefore, attached drawing and description are regarded as illustrative in nature rather than are used for
Limit scope of the claims.In addition, in the present specification, attached drawing is drawn not in scale, and identical reference numeral
Represent identical part.
The present invention provides a kind of turbo blade, which has curved surface features, to clearly describe spoon of blade feature,
Ignore the thickness of turbo blade, the feature of spoon of blade is hereinafter only illustrated by taking a blade as an example.Blade is around assembling
The rotary shaft rotation of turbine afterwards, spoon of blade is hereinafter placed on using Z axis as rotary shaft by hereinafter referred to as rotary shaft
OXYZ rectangular coordinate systems in illustrate.
First embodiment
The feature of spoon of blade is described with reference to Fig. 1 to Fig. 7.As shown in Figure 1 and Figure 2, Z is rotary shaft, the first curve
AB is coplanar with rotary shaft and disjoint smoothly without inflection point concave curve, and concave surface is towards rotary shaft, and end point B and rotary shaft
Close to referred to as proximal end, another terminal A is with rotary shaft far from referred to as distal end.Any point P1 is taken to make tangent line, tangent line on the first curve
It is less than or equal to 90 degree in proximal end B with the angle α of rotary shaft, A is more than or equal to 0 degree in distal end.Obviously, α is equal to 0 degree and means at this time
Tangent line is parallel with rotary shaft at the A of distal end.It is moved with this point from proximal end B to distal end A, the angle α monotone decreasing.If the first curve
The expression of AB available functions, first derivative monotone increasing in domain.First curve AB is rotated a circle to form the plane of reference about the z axis
M, plane of reference M are an approximate antenna pot shape face, and G is rotation round track.As shown in Figure 3, Figure 4, because spoon of blade will be with ginseng
It is that reference illustrates to examine face, therefore, selected part plane of reference M.First curve AB extends the first leaf to direction of rotation side
Piece curved surface M1.
The feature of 2 to 7 the first spoon of blade of explanation below in conjunction with the accompanying drawings.As shown in Fig. 2, it can always be looked on the first curve AB
To a bit, referred to as burble point W, burble point W rotate around the axis of rotation the circular arc line to be formed and are known as defiber L.
Line segment AW rotates the curved surface extended around rotary shaft and is overlapped with the plane of reference, referred to as additional surface.And prolonged by line segment WB
On the curved surface of stretching, in addition to except the first curve and by burble point W rotating around the axis of rotation the defiber formed, on remaining curved surface
Any point is not overlapped and is intersected with plane of reference M, this region is known as intrinsic first spoon of blade M11.Intrinsic first blade is bent
Face M11 and plane of reference M is bordered in the first curve AB and defiber L, but it does not include the first curve and defiber, that is to say, that
Point on intrinsic first spoon of blade is not overlapped and is intersected with the plane of reference.Intrinsic first spoon of blade, divides the first curve
Offline and additional surface collectively forms the first spoon of blade.In special circumstances, it is when burble point W is overlapped with remote point A, then intrinsic
First spoon of blade forms the first spoon of blade, and when burble point is overlapped with proximal end, the first spoon of blade is equal to third leaf
Piece curved surface.First spoon of blade only have the first curve and defiber (defiber that burble point rotates when being overlapped with distal end) and
The plane of reference overlaps.
Then, as shown in figure 5, taking up an official post in intrinsic first spoon of blade M11 takes a point P2, point P2 is crossed in intrinsic first blade
The second curve CD, the second curve CD is on curved surface M11 with the intersection point close to the edge of the first curve as C, on the second curve CD
All the points are equal with the distance of Z axis.It crosses point P2 and third curve EF, the third curve is done on intrinsic first spoon of blade M11
On all the points be in P2 points and same plane that rotary shaft determines in.If with function representation, the second curve CD is bent with third
Line EF is continuous derivatived functions curve and without inflection point.The normal and plane of reference M phases for crossing the spoon of blade M1 of point P2 give point Q,
Also, if point P2 is moved along the second curve CD to direction of rotation side, that is, point P2 is moved to D points from C points, between P2Q
Gradually increase, curvature of the second curve CD at P2 points also gradually increase distance.If point P2 is moved along third curve EF to rotary shaft
Dynamic, i.e. point P2 is moved from E to F, and the normal of P2 points and the intersection point Q of the plane of reference are also in the same time shift in plane of reference upper edge homologous thread track
Dynamic, distance gradually increases between P2Q at this time, and curvature of the third curve EF at P2 points with Q points at this time in homologous thread track
On the difference of curvature also gradually increase.The homologous thread track namely plane and ginseng where referring to third curve EF and rotary shaft
Examine the intersecting lens in face, it is clear that it is also the first curve that the plane of reference is rotated at this and formed along rotary shaft.
Wherein, the described curved surface feature definitions of the second curve CD be single order curved surface, the described curved surfaces of third curve EF
Feature definitions are the surface of second order.Therefore the curvature of the surface of second order is mainly by the first curve AB assignment.The surface of second order
Characteristic is also that this curved surface of turbine vane is different from the most important feature of other curved surface of turbine vane.
The entire intrinsic first spoon of blade M11 of traversal, the normal for crossing point P2 (rotate always with XOY plane perpendicular to blade
The plane of axis) there is intersection point.That is, must not be equal to by crossing P2 point tangent planes and XOY plane angle by 90 degree.Entire first blade is bent
On face, only when α=0 degree, that is, when A point tangent lines are parallel to rotary shaft, distal end that A points extend on the first spoon of blade
On edge line the tangent plane of any point just can with and must be vertical with XOY plane.
Under normal circumstances, the first curve be exactly blade back edge line (curved edges of side opposite to the direction of rotation, i.e.,
The rear side boundary of curved surface).But it is also possible to the part plane of reference of the first curve side opposite to the direction of rotation is added in into blade
Curved surface does not influence the performance of blade.But, hereinafter, the side opposite to the direction of rotation by the first curve is ignored
The part plane of reference, only illustrated using the first curve as back edge line.
Illustrate the second spoon of blade with reference to Fig. 6.As shown in fig. 6, taking up an official post in the plane of reference takes the of one article of continuously smooth
Four curve ST, S are up contour point, and T is down contour point, and ensure that any two points z values differ on ST curves, i.e., the 4th curve is taken up an official post
Anticipate at 2 points in the height difference for being parallel to rotary axis direction.Taking up an official post to take on point a J, the 4th curve ST in the first curve AB has uniquely
One point K is corresponding to it, and 2 points of numerical value in Z-direction of J, K is equal, i.e. on the 4th curve ST it is total have it is unique a little with the
Any point on one curve is identical in the height for being parallel to rotary axis direction.It crosses 2 points of J, K and forms circular arc on plane of reference M
JK, radian θ, if ST is a function curve, it is clear that θ can regard the function F (J) of J, θ=F (J (xyz)), for known as
Actual argument of first curve AB, the J point on AB only has z, therefore θ=F (z).Obviously, it is fallen according to K points in the direction of J points not
Together, θ values also have the difference of positive and negative values, θ=0 when J, K are overlapped.
It will be converted to using the first spoon of blade that the first curve AB is back edge line by following rule using ST curves as back
Second spoon of blade of edge line, specific method are：Enable in the first spoon of blade M1, the points of z values identical with J points all using Z axis as
Rotary shaft rotates radian θ to K points, J points is allowed to traverse the first curve AB, so as to obtain so that ST is new back edge line structure the
Two spoon of blade.That is, by the first spoon of blade in the Z-axis direction the identical point of height keep mutual alignment constant around
Z axis rotates point to the first curve point identical with height on the 4th curve and overlaps, and forms the second spoon of blade.If the 4th is bent
Line ST can be represented with function, then can be briefly described the radian for rotating θ=F (z) about the z axis for all the points of the first spoon of blade
Obtain the second spoon of blade.This change is referred to as radian θ rotation transformations.
Alternatively, it is also possible to form spoon of blade merely with the plane of reference, referred to as third blade curved surface, third blade curved surface also may be used
Regard the special case of the first spoon of blade when the burble point W of the first curve is overlapped with proximal end B as.
Above in association with the essential characteristic for having illustrated the first spoon of blade, the second spoon of blade, third blade curved surface.And
Turbo blade can be made of any of the first spoon of blade, the second spoon of blade, third blade curved surface.
In a preferred embodiment, the first curve AB can be cycloid.
In a preferred embodiment, in some cases, the first curve burble point W is overlapped with distal end A, and A point tangent lines
It is parallel with rotary shaft, the curved surface features of the first spoon of blade and the second spoon of blade can be further limited at this time.For example, as schemed
Shown in 7, any point P3 is taken on the first spoon of blade, crosses the parallel lines that point P3 makees Z axis, spacing of the parallel lines away from Z axis is
R intersects at point Q3 with plane of reference M.When the parallel lines are radially moved to Z axis, point P3 and point Q3 the distance between with R's
Square it is incremented by inverse proportion.Thus obtained first spoon of blade is still obtained by the way of aforementioned radian θ rotation transformations
Corresponding second spoon of blade.
In a preferred embodiment, other curved surfaces are may further include on spoon of blade and natural prolongation is (flat
Sliding transition portion), natural elongated area need not meet the definition of above-mentioned spoon of blade.First spoon of blade can also include first
When the part plane of reference of curve side opposite to the direction of rotation and/or the tangent line of the first curve distal end parallel with rotary shaft,
The part cylindrical surface or an arbitrary part for above-mentioned curved surface that the remote edge line of first spoon of blade extends straight up along Z axis.
Second spoon of blade further includes the part plane of reference of the first curve side opposite to the direction of rotation and/or first curve distal end
Tangent line it is parallel with rotary shaft when, part cylindrical surface that the remote edge line of the second spoon of blade extends straight up along Z axis or
An arbitrary part for above-mentioned curved surface.Third blade curved surface further include the first curve distal end tangent line it is parallel with rotary shaft when,
The part cylindrical surface or an arbitrary part for above-mentioned curved surface that the remote edge line of third blade curved surface extends straight up along Z axis.
First spoon of blade, the second spoon of blade, third blade curved surface are referred to as spoon of blade.Ignore the thickness of turbo blade
Degree, spoon of blade meet feature (the natural extension area of one in the first spoon of blade, the second spoon of blade and third blade curved surface
Except domain).The thickness of blade reality is decided according to the actual requirements on the basis of spoon of blade is met, when vane thickness is little,
" practical spoon of blade " and " spoon of blade " can be considered same curved surface.For certain specific fluid, the edge shape of blade can
To be obtained as needed on practical spoon of blade.Also allow to set deflector hole or slot etc. in practical application, on blade, such as scheme
Shown in 17, deflector hole 15 is provided on position of each blade close to rotary shaft, particularly, deflector hole 15 is arranged on same circle
Zhou Shang.Deflector hole also allows streamiline wire to add the structures such as reinforcing rib or blade design is hollow to arrange that cooling pipe etc. changes
It is dynamic.Due to the bending features of the first curve, entire blade has corresponding curvature in the axial direction, is the turbo blade of the present invention
(including single blade) is different from the important feature of conventional turbine blade.
When burble point is overlapped with distal end, intrinsic first spoon of blade is the first spoon of blade of composition, and thus obtains the
Two spoon of blade can form multiple-blade turbine by the first spoon of blade or the second spoon of blade.It is leafy as shown in Fig. 7 to 10
Piece turbine 1 is along the circumferential direction spliced by multiple blades 11, and the first curve AB of spoon of blade is placed on rotation gained
On plane of reference M, circumference in equal parts, around the evenly distributed blade of rotary shaft, each blade 11 is fixed together with rotary shaft 12, longitudinal edge
Edge is fixed together to form multiple-blade turbine by cyclic structure 13.The outer profile of turbine entirety is in the shape of plane of reference M, class
Like antenna pot shape.
The first spoon of blade of part and the second spoon of blade of part can also form multiple-blade turbine.Here so-called part,
The partial blade curved surface for referring to only take the arbitrary curve section between the first curve proximal end B to burble point W to be formed, that is, the first leaf
Piece curved surface or the second spoon of blade close to rotary shaft arbitrary portion, without including their defiber.Therefore after forming turbine,
Radial edges between adjacent blades are because apart from unequal, natural combination together, and will not by cyclic structure with rotary shaft
They are fixed together.If the blade that complete first spoon of blade comprising defiber or the second spoon of blade are formed, then
The radial edges of adjacent blades because with rotary shaft apart from equal, can natural combination together.For the fastness of structure, generally
Also blade edge is fixed together with cyclic structure.
Multiple-blade curved surface of turbine vane parameter and blade number and fluid viscosity coefficient, operating mode (velocity pressure temperature etc.) and
The processing conditions limitation of blade production is related.Newtonian fluid ideally, in the premise that processing technology and the strength of materials are permitted
Under, blade is made more Bao Yuehao.Usually, fluid viscosity coefficient is bigger, and spoon of blade average curvature is also bigger, correspondingly blade
Number can be made more, and blade pitgh is bigger.
Multiple-blade turbine after assembling, in terms of its concave side, under Newtonian fluid and preferable operating mode, because of the blade of multiple-blade turbine
Roomy enough, the orthographic projection of turbo blade generally has the part to overlap each other, therefore can not see the gap between blade, this is
The general features of turbine of the present invention.But according to the difference of fluid, the difference of blade edge shape, in special circumstances it can also be seen that
Gap.The blade edge shape of diagram is simultaneously non-determined, true form according to specific needs (fluid, operating mode etc.) and determine.From more
The blade turbine back side sees that impeller clearance universal law is：As shown in Figure 10,11, along spoon of blade from rotary shaft 12 to blade ring
Shape structure 13, the gap between blade is less and less, this is determined by the characteristic of spoon of blade.That is, closer to whirlpool
Rotary shaft is taken turns, the gap between adjacent blades is bigger, and closer to turbine edge, gap is smaller between blade.
Second embodiment
As shown in figure 12, single blade can also form a single blade turbine 2.Single blade turbine 2 only includes one with the
The turbo blade 21 that three spoon of blade are formed, turbo blade 21 can be considered as the infinitesimal multiple-blade turbine in gap between blade,
It is exactly the plane of reference of a complete tape thickness, in antenna pot shape face, there is a cavity or setting water conservancy diversion at rotary shaft 22
Hole, so that fluid flows.
3rd embodiment
As shown in figure 13, multiple single blade turbines 2 may be constructed coaxial lamination turbine 3, and coaxial lamination turbine 3 can also be regarded as
That multiple single blade turbines 31 surround the multistage turbine in series of rotary shaft 32, i.e., it is the different single blade of diameter is coaxial
Be superimposed together, from each other there are gap, the rule in gap still defers to impeller clearance universal law, i.e., along spoon of blade from
Rotary shaft is to blade radial edge, and impeller clearance is less and less, but minimum clearance is more than zero.Figure 13 illustrates cuing open for partial blade
Face figure, it can be seen that the rule of impeller clearance.Leaves density may be much higher than shown in Figure 13 in practice.In not notable shadow
Under the premise of ringing efficiency, in spoon of blade, some special nodes also still allow for structure fastened to each other between blade, to strengthen
Whole firmness, and be distributed along vortex filament to reduce resistance.Because scale is usually relatively fine, Figure 13 has ignored this details
Displaying.The hole of central vane, increased rule or outer ring blade are close gradually for central vane hole from inside to outside for general satisfaction
Increase increase deflector hole at rotary shaft, Figure 13 also ignores the displaying of this details.
Fourth embodiment
As shown in figure 14, multiple multiple-blade turbines 41 can also be made around rotary shaft 42 that different-diameter is coaxial to be superimposed on one
The turbine risen, the gap rule between each turbine is analogous to above-mentioned coaxial lamination turbine, i.e., from rotary shaft to turbine radial edges,
Gap between turbine is less and less, is referred to herein as multistage turbine 4.
5th embodiment
As shown in figure 15, the blade of the turbine is bent by intrinsic first spoon of blade or the second spoon of blade and third blade
Face composition, that is to say, that distal end of the burble point neither with the first curve overlaps, and also the proximal end not with the first curve overlaps.This
When the first spoon of blade then include intrinsic first spoon of blade and additional surface.The turbo blade formed by the first spoon of blade
Feature with multiple-blade turbine 1 and single blade turbine 2.Similarly, when distal end of the burble point neither with the first curve overlaps,
When not overlapped with the proximal end of the first curve, the turbo blade that the second spoon of blade is formed also has multiple-blade turbine 1 and single blade
The feature of turbine 2.Equally, this turbine can also be made into the multistage turbine of the coaxial overlapping of different-diameter.
As shown in figure 16, multiple curves for meeting the first curve AB features endpoint head and the tail be sequentially connected with, and concave towards it is identical,
A'B' curves are expanded downwards from B endpoints, and A " B " curve is extended up out, and AB curves, A'B' curves, A " B " are bent from A ends
Line be satisfied by more than the first curve AB definition, i.e., " coplanar with rotary shaft and disjoint smooth no inflection point and concave surface are towards rotation
The concave curve of shaft, the tangent line of any point and the angle of rotary shaft are more than or equal to 0 degree, and less than or equal to 90 degree thereon ".A'B' is bent
Line can also continue to extend down, and A " B " curve can continue to up extend, and the curve formed in this way is referred to here as multistage phase
Even the first curve.The first curve of any of which section rotates out of the plane of reference as the method previously described, forms multistage connected reference
Face simultaneously can obtain multistage first spoon of blade that is connected, multistage connected second spoon of blade, multistage connected third blade song
The composite blading curved surface that face and multistage connected above-mentioned spoon of blade mix.
For example, multistage connected single blade turbine is formed, and revolve as turbo blade using multistage connected third blade curved surface
Shaft sets hole with turbo blade junction.For example, using multistage connected first spoon of blade or multistage connected second leaf
Piece curved surface or multistage connected composite blading curved surface form multistage connected multiple-blade turbine as turbo blade.Also, include multistage
The turbo blade of connected spoon of blade can equally form multiple-blade turbine, single blade turbine, coaxial lamination turbine and multistage
Turbine etc. and their hybrid combining form.
10 sketch turbo driving principle below in conjunction with the accompanying drawings, when fluid flows through blade from top to bottom, by spoon of blade,
Rotation and the common induction of stream pressure are close to the vortex of blade, and pass through effect of boundary layer to leaf in the concave direction generation of turbine
Piece transmits torque, referred to herein as induced swirl.Induced swirl pushes turbine rotation, and turbine rotary motion is further strengthened inducing
Vortex, therefore, turbine and induced swirl enter the mutual transmittance process of energy positive feedback, pass through this process, the energy of fluid input
Maximum value is rapidly reached between the energy of turbine rotation output and keeps balancing.The energy of fluid flowing is turned by induced swirl
Turn to the energy of turbine rotation.The principle for being generated rotation by fluid propulsive thrust from conventional turbine is different, this turbine is by fluid
Induced swirl pass through effect of boundary layer push rotation.
Single blade turbine and coaxial lamination turbine are suitable for the fluid situations of high reynolds number.Single blade turbine and coaxial lamination
Turbine, which needs an initial rotational movement is previously applied, can just start running, and after rotary motion starts, above-mentioned principle is still fitted
With.
Theoretically the turbine of the present invention can be used to carry out energy exchange for all fluids.It is particularly suitable for wind power turbine
And hydroelectric turbines, it can be also widely applied to steam turbine and gas turbine blade designs at different levels.Driving fluid is can be also used for,
Such as in various pumps and airfoil design.
The turbine of the present invention has small torque, high rotating speed, efficient operating characteristics.If for generating electricity, can directly connect
Sending and receiving motor saves the acceleration mechanisms such as gearbox.
And coaxial lamination turbine, multistage turbine, hybrid turbine can then improve the efficiency of turbine.
The rotation of the turbine of the present invention not primarily relies on propulsive thrust during fluid outflow turbine, and fluid is only in turbine
Turbine could be flowed out, that is, turbine is flowed out from the minimum region of linear velocity close to central area, it is ensured that fluid flows out turbine
Speed be to tend to be minimum, it is meant that the remaining kinetic energy of fluid tends to be minimum.Also, due to turbine each point linear velocity not
With so as to generate Coriolis force, turbine rotation is pushed.Because centrifugal force increases the pressure between fluid and blade so that whirlpool
Wheel obtains main torque.Due to the flow field of induced swirl, in the applications such as gas turbine, vortex flow field can generate radial temperature
Gradient, the lip temperature close to vortex is high, and the central temperature close to vortex is low, ensures that the fluid temperature (F.T.) of discharge is low in this way,
Waste heat is few, therefore also just improves temperature and combustion engine efficiency before whirlpool.In addition, this turbine is used in wind-power electricity generation, rotor solidity can
It is lost in reaching the wind-force absolutely, not brought therefore.Again because of the high speed of rotation, energy catharsis in time carrys out air quantity, no
Windage, which can be increased, reduces efficiency.
The present invention provides a kind of turbine driven using the vortex artificially manufactured in fluid.The present invention proposes the surface of second order
Turbo blade concept, using the turbine and turbine group of turbo blade composition, by being vortexed the coupling in flow field, realize high efficiency
Energy conversion.The so-called surface of second order is on the basis of the curved surface of typical turbine blade, then is superimposed an axial bending, with this
Eddy field, i.e. the rotary motion manufacture vortex field of blade in a fluid are formed, Coriolis force is generated in flow field and passes through
Effect of boundary layer pushes blade to accelerate rotation, forms positive feedback between vortex and blade, reaches high-energy conversion ratio with this.It is this
The benefit that drive mode is brought further includes the temperature gradient effect using vortex field, improves the thermal efficiency of the applications such as gas turbine.
Because when fluid flows out the utility model turbine, remaining kinetic energy and enthalpy are respectively less than typical turbine, and the energy difference of initial fluid
The rotation acting of promotion blade is both used in, so having achieved the purpose that improve efficiency.
The foregoing is merely the preferred embodiment of the present invention, are not intended to restrict the invention, for those skilled in the art
For member, the invention may be variously modified and varied.Any modification for all within the spirits and principles of the present invention, being made,
Equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (13)
1. a kind of turbo blade, when ignoring vane thickness, spoon of blade is the first spoon of blade, the second spoon of blade or third
One in spoon of blade,
First curve (AB) is the concave curve of coplanar with rotary shaft and disjoint smooth no inflection point, the concave surface direction of the first curve
Rotary shaft, the endpoint of the first curve close to rotary shaft are known as proximal end, and endpoint of first curve far from rotary shaft is known as distal end,
Wherein, the first spoon of blade at least meets following curved surface features：
First curve rotates a circle to form the plane of reference (M) around rotary shaft, and the first curve extends the first leaf to direction of rotation side
Piece curved surface (M1),
Always there is burble point, on the first curve, the curved section between burble point and proximal end extends to form this on first curve
The first spoon of blade is levied, the curved section between burble point and distal end rotates the additional surface to be formed and plane of reference weight around rotary shaft
It closes, the burble point rotates the circular arc line generated around rotary shaft and is known as defiber, and it is bent that the defiber forms intrinsic first blade
Face and the boundary line of additional surface, the point on intrinsic first spoon of blade are not overlapped and are intersected with the plane of reference,
By any point (P2) on intrinsic first spoon of blade, the second curve is formed on intrinsic first spoon of blade, second is bent
Any point on line is equal with the distance of rotary shaft,
By any point on intrinsic first spoon of blade, third curve is formed on intrinsic first spoon of blade, third is bent
Any point on line was on intrinsic first spoon of blade in any point and the same plane of rotary shaft, described excessively
It levies the normal of any point on the first spoon of blade and forms intersection point (Q) with the plane of reference,
If also, any point is moved along the second curve to direction of rotation side on intrinsic first spoon of blade, with institute
State on intrinsic first spoon of blade that distance gradually increases between any point and the intersection point, the described second bent curvature of a curve is also gradual
Increase,
If also, any point is moved along third curve to rotary axis direction on intrinsic first spoon of blade, the intersection point (Q)
Also it is moved simultaneously along the homologous thread track on the plane of reference, then with any point on intrinsic first spoon of blade and the friendship
Distance gradually increases between point, and the difference of the curvature of the homologous thread track of the third song curvature of a curve and point of intersection also gradually increases
Greatly,
And entire intrinsic first spoon of blade of traversal, on intrinsic first spoon of blade normal of any point always with perpendicular to
The plane of rotary shaft intersects；
Intrinsic first spoon of blade, the first curve, defiber and additional surface collectively form the first spoon of blade；
Wherein, the second spoon of blade at least meets following curved surface features：
When rotary shaft is vertical, takes up an official post in the plane of reference and take the 4th curve (ST) of one article of continuously smooth, and the 4th curve is taken up an official post
Anticipate 2 points it is different in the height for being parallel to rotary axis direction, also, always have on the 4th curve it is unique a little and the first curve
On any point it is identical in the height for being parallel to rotary axis direction,
By the identical point of height keeps relative position constant and around rotation on rotary axis direction is parallel on the first spoon of blade
Axis rotates, until the point coincidence that the point of the first curve is identical with height on the 4th curve, forms the second spoon of blade；
Wherein, third blade curved surface at least meets following curved surface features：
Third blade curved surface is the plane of reference formed that rotated a circle by the first curve around rotary shaft；
Wherein, if burble point is overlapped with distal end, intrinsic first spoon of blade forms the first spoon of blade, if burble point and proximal end
It overlaps, the first spoon of blade is equal to third blade curved surface.
2. turbo blade according to claim 1, which is characterized in that the first spoon of blade further includes the first curve and extends
Side opposite to the direction of rotation the part plane of reference and/or
When the tangent line of the first curve distal end is parallel with rotary shaft, the remote edge line of the first spoon of blade is along rotary axis direction
Naturally the part cylindrical surface smoothly extended；
Second spoon of blade further include the side opposite to the direction of rotation that the first curve extends the part plane of reference and/or
When the tangent line of the first curve distal end is parallel with rotary shaft, the remote edge line of the second spoon of blade is along rotary axis direction
Naturally the part cylindrical surface smoothly extended；
Third blade curved surface further include the first curve distal end tangent line it is parallel with rotary shaft when, the distal end of third blade curved surface
The part cylindrical surface that edge line smoothly extends naturally along rotary axis direction.
3. turbo blade according to claim 1, which is characterized in that first curve is cycloid.
4. turbo blade according to claim 1, which is characterized in that any point is in institute on intrinsic first spoon of blade
It states and makees on intrinsic first spoon of blade far from when moving radially of the axis of rotation, any point is with joining on intrinsic first spoon of blade
Examine face in the distance for being parallel to rotary axis direction with the distance of the first spoon of blade any point and rotary shaft square in anti-
Ratio is successively decreased.
5. turbo blade according to any one of claim 1 to 4, which is characterized in that the spoon of blade of turbo blade is
The portion intercepts face of first spoon of blade or the second spoon of blade, the portion intercepts face are in first spoon of blade
Or the second part curved surface arbitrarily intercepted between rotary shaft to defiber on spoon of blade, also, the portion intercepts face is not
Include defiber.
6. turbo blade according to claim 1, which is characterized in that the curve that multistage meets the first curvilinear characteristic concaves towards one
It causes and is sequentially connected with from beginning to end, multistage connected first curve of formation, and form multistage connected first by connected first curve of the multistage
Spoon of blade, multistage connected second spoon of blade, multistage connected third blade curved surface, multistage connected composite blading curved surface,
Wherein, each section of curved surface features for all meeting the first spoon of blade of multistage connected first spoon of blade,
The each section of curved surface features for all meeting the second spoon of blade of connected second spoon of blade of multistage,
The each section of curved surface features for all meeting third blade curved surface of the connected third blade curved surface of multistage,
Each section of the connected composite blading curved surface of multistage all meets the first spoon of blade or the second spoon of blade or third blade is bent
The curved surface features in face,
The spoon of blade is multistage connected first spoon of blade, multistage connected second spoon of blade, multistage connected third blade
One in curved surface or multistage connected composite blading curved surface.
7. turbo blade according to claim 1, which is characterized in that the position on turbo blade close to rotary shaft offers
Penetrate the deflector hole of turbo blade.
8. turbo blade according to claim 6, which is characterized in that be connected third using the multistage described in claim 6
Spoon of blade forms multistage connected single blade turbine, and rotary shaft is provided with hole with turbo blade junction as turbo blade
Hole.
9. turbo blade according to claim 6, which is characterized in that be connected first using the multistage described in claim 6
Spoon of blade or multistage connected second spoon of blade or multistage connected composite blading curved surface form multistage be connected as turbo blade
Multiple-blade turbine.
10. a kind of single blade turbine, using the third blade curved surface described in any one of claims 1 to 3 as turbo blade,
Single blade turbine is formed, and rotary shaft sets hole with turbo blade junction.
11. single blade turbine according to claim 10, which is characterized in that multiple single blade turbines of different sizes are coaxial
It is stacked together, coaxial lamination turbine is formed, also, along spoon of blade from rotary shaft to blade radial edge, between blade
Gap is less and less.
12. a kind of multiple-blade turbine, bent using the first spoon of blade described in any one of claim 1 to 5 or the second blade
Face as turbo blade, each blade by concave curved surface towards being concentrically fitted to together with rotary shaft in a manner of identical, wherein, own
First curve of spoon of blade is arranged on the plane of reference of the first curve rotation gained, along the circumferential direction uniform around rotary shaft
Arrange blade, the plane of reference or special cyclic structure that radial edges are integrated by seamless combination be fixed together to be formed it is leafy
Piece turbine.
13. multiple-blade turbine according to claim 12, which is characterized in that multiple multiple-blade turbines of different sizes are coaxial
It is stacked together, forms multistage turbine, from rotary shaft to turbine radial edges, the gap between turbine is less and less.
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| CN110439751A (en) * | 2019-08-07 | 2019-11-12 | 吴志成 | Power generator |
| CN110454330A (en) * | 2019-08-07 | 2019-11-15 | 吴志成 | Blower and power generator for power generator |
| CN111456965B (en) * | 2020-04-16 | 2022-02-15 | 李伟 | Centrifugal axial flow turbine and novel jet engine mode and operation method |
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| US20130129521A1 (en) * | 2011-11-17 | 2013-05-23 | John E. Tharp | Turbine blade skirt |
| CN206608215U (en) * | 2017-02-03 | 2017-11-03 | 刘欧阳 | A kind of turbo blade and the turbine being made up of the turbo blade |
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| FR1442526A (en) * | 1965-05-07 | 1966-06-17 | Rateau Soc | Improvements to curved canals traversed by gas or vapor |
| JPH09296701A (en) * | 1996-05-08 | 1997-11-18 | Mitsubishi Heavy Ind Ltd | Axial flow turbine blade |
| CN201250794Y (en) * | 2008-09-18 | 2009-06-03 | 上海东方泵业(集团)有限公司 | Mounted impeller |
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