CN106593540A - Turbine blade and turbine composed of same - Google Patents
Turbine blade and turbine composed of same Download PDFInfo
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- CN106593540A CN106593540A CN201710062948.3A CN201710062948A CN106593540A CN 106593540 A CN106593540 A CN 106593540A CN 201710062948 A CN201710062948 A CN 201710062948A CN 106593540 A CN106593540 A CN 106593540A
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- blade
- spoon
- curve
- curved surface
- point
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- 239000002131 composite material Substances 0.000 claims description 10
- 238000003475 lamination Methods 0.000 claims description 10
- 241000208340 Araliaceae Species 0.000 claims description 3
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 claims description 3
- 235000003140 Panax quinquefolius Nutrition 0.000 claims description 3
- 230000003247 decreasing effect Effects 0.000 claims description 3
- 235000008434 ginseng Nutrition 0.000 claims description 3
- 239000012530 fluid Substances 0.000 abstract description 37
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- 230000005611 electricity Effects 0.000 description 4
- 230000001141 propulsive effect Effects 0.000 description 4
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- 230000007704 transition Effects 0.000 description 1
- 238000002834 transmittance Methods 0.000 description 1
- 239000002918 waste heat Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- 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)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Fluid Mechanics (AREA)
- Physics & Mathematics (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Ocean & Marine Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Hydraulic Turbines (AREA)
Abstract
The invention provides a turbine blade and a turbine composed of the same. A first blade curved surface and a second blade curved surface or a third blade curved surface are formed by virtue of smooth and non-inflection-point concave curved lines which are coplanar and do not intersect with a rotary shaft. The turbine blade structures of a single-blade curved surface, a multi-blade curved surface, a multi-stage-connected single-blade curved surface, a multi-stage-connected multi-blade curved surface, a multi-stage-connected composite-blade curved surface and the like are formed through combining the abovementioned blade curved surfaces. The turbine provided by the invention is driven by virtue of a vortex artificially formed in a fluid. According to the turbine blade and the turbine which are provided by the invention, the concept of a second-order curved surface is put forward, and the turbine and a turbine group are composed of the turbine blade formed by virtue of second-order blade curved surfaces; and a vortex field is manufactured through the coupling of a vortex flow field, that is, the rotational motion of the blade in the fluid, a Coriolis force is generated in the flow field and the blade is pushed to accelerate rotation through a boundary layer effect, and positive feedback is formed between the vortex and the blade, thus a high energy conversion rate is achieved. The heat efficiency can be additionally increased if the blade is used in the turbine group of a gas turbine engine.
Description
Technical field
The present invention relates to hydrodynamics field, specifically, is 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 with three-dimensional character, true inside turbomachinery in practical operation
Flowing is extremely complex, spatially shows as the three-dimensionality of flowing, and the non-stationarity for flowing is shown as in time, attached in blade
Closely there is boundary-layer feature, again the flow-disturbings such as attached face whirlpool occur near vane end faces.Be generally used for analyze fluid motion Na Wei-this
Lentor equation is difficult to use in solving the problems, such as so complexity in turbine design.Even so, we also can be from basic
The common defects of the turbine technology of prevalence are found in mechanics principle.First, popular turbine technology substantially adopts turbo blade
Change fluid direction of motion, while reciprocal thrust is obtained, and as the rotation of power maintenance turbine.Under this method,
Fluid leaves the propulsive force that the speed of turbo blade and turbo blade are obtained and the velocity correlation for rotating, and turbine propulsion power is bigger,
Rotate faster, it is meant that fluid leaves faster.Fluid to leave that mean sooner remaining kinetic energy in fluid bigger.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 for avoiding is that linear velocity is also different, or even difference is huge, especially with wheel footpath as the radius of turn of blade each point is different
The wind wheel of huge turbine such as wind-power electricity generation is for very.The blade of such as close rotor shaft, speed is very slow, and wind cannot be promoted, several
Can only be to bypass here, so as to be difficult to transmit energy, and at the tip of wind wheel, speed must exceed well over soon wind speed and even produce again
Back pressure, that is, vacuum side of blade caught up with air-flow, the angle of attack causes the air pressure of vacuum side of blade to be more than positive air pressure, causes very big
Rotational resistance.Therefore the difference of linear velocity can substantially reduce turbine efficiency.3rd, popular turbine technology without
Method avoids the energy loss that centrifugal force brings.Fluid leaves under the action of the centrifugal force turbine certainly will be with rotary cutting speed upwards
Component, this portion of energy inevitably have lost.4th, in the application such as gas turbine, the fluid of discharge contains substantial amounts of remaining
Heat, is not effectively transformed as mechanical energy, therefore also reduces temperature before whirlpool, also reduces gas turbine proficiency.5th, turbine leaf
Contradictory between the number and efficiency of piece, the wind wheel especially with wind-power electricity generation is as protrusion.The projection gross area of wind wheel blade claims wind
Wheel solidity is an index for being difficult to improve, and rotor solidity is not high, certainly will cause the loss of wind energy.And rotor solidity is improved, and
Windage can be caused to increase, wind speed reduces, reduce wind wheel efficiency.In view of this, the present invention propose a kind of novel turbine blade and
The turbine being made up of the turbo blade, to overcome disadvantages described above.
The content of the invention
The present invention provides a kind of turbo blade, and when ignoring vane thickness, its 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 without flex point
Sag vertical curve, towards rotary shaft, the end points of the close rotary shaft of the first curve is referred to as near-end for the concave surface of the first curve, the first curve away from
The end points of rotary shaft is referred to as distal end, wherein, the first spoon of blade at least meets following curved surface features：First curve revolves around rotary shaft
Circle to form the plane of reference (M), the first spoon of blade (M1) is extended in the first curve to direction of rotation side, begin on the first curve
There is eventually burble point, on the first curve, the curved section between burble point and near-end extends to form intrinsic first spoon of blade, point
Curved section between point and distal end rotates the additional surface to be formed and overlaps with the plane of reference around rotary shaft, and the burble point is around rotation
The circular arc line that axle rotation is produced is referred to as defiber, and the defiber constitutes the boundary of intrinsic first spoon of blade and additional surface
Line, the point on intrinsic first spoon of blade not with the plane of reference overlap and intersect, take up an official post through intrinsic first spoon of blade
A bit (P2), the second curve is formed on intrinsic first spoon of blade, the distance phase of any point on the second curve and rotary shaft
Deng, any point on intrinsic first spoon of blade, the 3rd curve of formation on intrinsic first spoon of blade, the 3rd curve
On any point be on intrinsic first spoon of blade in the same plane of any point and 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
A little along the second curve to the side shifting of direction of rotation one, then with any point and the intersection point on intrinsic first spoon of blade
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 along the 3rd curve to rotation direction of principal axis movement, the intersection point (Q) homologous thread track also on the plane of reference is simultaneously mobile,
Then as distance gradually increases between any point and the intersection point on intrinsic first spoon of blade, the song of the 3rd curve
The difference of the curvature of the homologous thread track of rate and point of intersection also gradually increases, and travels through whole intrinsic first spoon of blade, institute
The normal for stating any point on intrinsic first spoon of blade intersects all the time 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 bent
Any two points are different parallel to axial height is rotated on line, also, on the 4th curve it is total have it is unique a little with the
Any point on one curve parallel to rotate it is axial highly identical, by the first spoon of blade parallel to rotary shaft
Height identical point keeps relative position constant and rotates around rotary shaft on direction, until on the point and the 4th curve of the first curve
Height identical point overlaps, and forms the second spoon of blade；Wherein, third blade curved surface at least meets following curved surface features：3rd
Spoon of blade is the plane of reference for being formed that rotated a circle around rotary shaft by the first curve；Wherein, it is intrinsic if burble point overlaps with distal end
First spoon of blade constitutes the first spoon of blade, if burble point overlaps with near-end, the first spoon of blade is equal to third blade
Curved surface.
Preferably, the first spoon of blade also includes the part reference of 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
Direction smooths the part cylindrical surface for extending naturally；It is opposite to the direction of rotation that second spoon of blade also includes that the first curve extends
When the tangent line of the part plane of reference of side and/or the first curve distal end is parallel with rotary shaft, the distal end of the second spoon of blade
Edge line smooths the part cylindrical surface for extending along rotation direction of principal axis naturally；Third blade curved surface also includes the first curve distal end
Tangent line it is parallel with rotary shaft when, the remote edge line of third blade curved surface is along the naturally smooth part extended of rotation direction of principal axis
Cylinder.
Preferably, first curve is cycloid.
Preferably, any point is made away from rotation on intrinsic first spoon of blade on intrinsic first spoon of blade
During the radial motion of axle, on intrinsic first spoon of blade any point and the plane of reference parallel to rotate axial distance with
The first spoon of blade any point and the distance of rotary shaft square are 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 is any between rotary shaft to defiber on first spoon of blade or the second spoon of blade
The part curved surface of intercepting, 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 forms multistage being connected
First curve, and by this it is multistage be connected first curve formed it is multistage be connected the first spoon of blade, it is multistage be connected the second spoon of blade,
Multistage connected third blade curved surface, multistage connected composite blading curved surface,
Wherein, multistage be connected the first spoon of blade each section all meets the curved surface features of the first spoon of blade,
Multistage be connected the second spoon of blade each section all meets the curved surface features of the second spoon of blade,
Each section of multistage connected third blade curved surface all meets the curved surface features of third blade curved surface,
Each section of multistage connected composite blading curved surface all meets the first spoon of blade or the second spoon of blade or the 3rd leaf
The curved surface features of piece curved surface,
The spoon of blade be it is multistage be connected the first spoon of blade, it is multistage be connected the second spoon of blade, it is multistage be connected the 3rd
One in spoon of blade or multistage connected composite blading curved surface.
Preferably, the position on turbo blade near rotary shaft offers the pod apertures for penetrating turbo blade.
Preferably, using the multistage connected third blade curved surface described in claim 6 as turbo blade, multistage phase is formed
Even single blade turbine, and rotary shaft arranges hole with turbo blade junction.
Preferably, using multistage the first spoon of blade or multistage second spoon of blade that is connected of being connected described in claim 6
Or multistage connected composite blading curved surface is used as turbo blade, multistage connected multiple-blade turbine is formed.
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 arranges 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 turbine, is made using above-described first spoon of blade or the second spoon of blade
For turbo blade, together with each blade is concentrically fitted to towards identical mode with concave curved surface with rotary shaft, wherein, all blades
First curve of curved surface is arranged on the plane of reference obtained by the rotation of the first curve, along the circumferential direction evenly distributed around rotary shaft
Blade, the plane of reference or special circulus that radial edges are integrated by seamless combination is 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 is less and less.
Description of the drawings
By being described to embodiment with reference to accompanying drawings below, the features described above and technological merit of the present invention will become
It is more clear and easy to understand.
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 schematic perspective view；
Fig. 3 be represent the present embodiments relate to the part plane of reference schematic perspective view；
Fig. 4 be represent the present embodiments relate to intrinsic first spoon of blade schematic perspective view one；
Fig. 5 be represent the present embodiments relate to intrinsic first spoon of blade schematic perspective view 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 schematic perspective view three；
Fig. 8 be represent the present embodiments relate to multiple-blade turbine schematic perspective view 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 schematic perspective view two；
Figure 11 be represent the present embodiments relate to multiple-blade turbine schematic perspective view three；
Figure 12 be represent the present embodiments relate to single blade turbine schematic perspective view；
Figure 13 be represent the present embodiments relate to coaxial lamination turbine schematic perspective view；
Figure 14 be represent the present embodiments relate to multistage turbine schematic perspective view；
Figure 15 be represent the present embodiments relate to hybrid turbine schematic perspective view；
Figure 16 be represent the present embodiments relate to it is multistage be connected the first curve schematic diagram；
Figure 17 be represent the present embodiments relate to pod apertures schematic diagram.
Specific embodiment
Below with reference to the accompanying drawings describing the embodiment of a kind of turbine of the present invention and turbo blade.This area it is general
Logical technical staff will recognize, in the case of without departing from the spirit and scope of the present invention, can be using a variety of modes
Or its combination is modified to described embodiment.Therefore, accompanying drawing and description are inherently illustrative, rather than are used for
Limit scope of the claims.Additionally, in this manual, accompanying drawing draws not in scale, and identical reference
Represent identical part.
The present invention provides a kind of turbo blade, and the turbo blade has curved surface features, to clearly describe spoon of blade feature,
Ignore the thickness of turbo blade, hereinafter only by taking a blade as an example illustrating the feature of spoon of blade.Blade is around assembling
The rotary shaft rotation of turbine afterwards, hereinafter referred to as rotary shaft is hereinafter placed on spoon of blade with Z axis 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 smooth without flex point sag vertical curve, and its concave surface is towards rotary shaft, and end point B and rotary shaft
It is close to and is referred to as near-end, another terminal A is with rotary shaft away from referred to as distal end.Any point P1 is taken on the first curve and makees tangent line, tangent line
90 degree are less than or equal in near-end B with the angle α of rotary shaft, A is more than or equal to 0 degree in distal end.Obviously, α means now equal to 0 degree
Tangent line is parallel with rotary shaft at the A of distal end.Moved to distal end A, the angle α monotone decreasing from near-end B with this point.If the first curve
AB available functions represent, its first derivative monotone increasing in domain of definition.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
The face of examining is that reference is illustrated, therefore, selected part plane of reference M.First curve AB extends the first leaf to direction of rotation side
Piece curved surface M1.
2 to 7 illustrate the feature of the first spoon of blades below in conjunction with the accompanying drawings.As shown in Fig. 2 always can look on the first curve AB
To a bit, referred to as burble point W, burble point W rotates the circular arc line to be formed around rotary shaft and is referred to as defiber L.
Line segment AW rotates the curved surface for extending around rotary shaft and overlaps with the plane of reference, referred to as additional surface.And prolonged by line segment WB
On the curved surface for stretching out, in addition to the defiber for being formed is rotated around rotary shaft except the first curve and by burble point W, on remaining curved surface
Any point not with plane of reference M overlap and intersect, this region is referred to as into 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 is not comprising the first curve and defiber, that is to say, that
Point on intrinsic first spoon of blade not with the plane of reference overlap and intersect.Intrinsic first spoon of blade, the first curve, point
Offline and additional surface collectively forms the first spoon of blade.In particular cases, it is when burble point W overlaps with remote point A, then intrinsic
First spoon of blade constitutes the first spoon of blade, and when burble point overlaps with near-end, the first spoon of blade is equal to the 3rd leaf
Piece curved surface.First spoon of blade only have the first curve and defiber (defiber for obtaining is rotated when burble point overlaps with distal end) with
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 is on curved surface M11, the second curve CD is C with the intersection point near the edge of the first curve, on the second curve CD
It is a little equal with the distance of Z axis.Cross point P2 and the 3rd curve EF, the 3rd curve are done on intrinsic first spoon of blade M11
On be in a little in the same plane that P2 points and rotary shaft determine.If with function representation, the second curve CD is bent with the 3rd
Line EF is continuous derivatived functions curve and without flex point.The normal for crossing the spoon of blade M1 of point P2 gives point Q with plane of reference M phases,
If also, point P2 moves to D points to the side shifting of direction of rotation one, that is, point P2 along the second curve CD from C points, between P2Q
Distance gradually increases, and curvature of the second curve CD at P2 points also gradually increases.If point P2 is moved along the 3rd curve EF to rotary shaft
Dynamic, i.e. point P2 is moved from E to F, and the normal of P2 points is with the intersection point Q of the plane of reference also on the plane of reference along the same time shift in homologous thread track
Dynamic, now distance gradually increases between P2Q, and curvature of the 3rd curve EF at P2 points with now Q points in homologous thread track
On the difference of curvature also gradually increase.The homologous thread track, namely refer to the 3rd curve EF and rotary shaft place plane with ginseng
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 curved surface feature definitions described by the second curve CD be single order curved surface, the curved surface described by the 3rd curve EF
Feature definitions are the surface of second order.Therefore the flexibility 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 whole intrinsic first spoon of blade M11 of traversal, crosses the normal of point P2 all the time with XOY plane (perpendicular to blade rotation
The plane of axle) there is intersection point.That is, crossing P2 point sections must not be equal to 90 degree with XOY plane angle.Whole first blade is bent
On face, only when α=0 degree, that is, A point tangent lines parallel to rotary shaft when, the distal end that A points extend on the first spoon of blade
On edge line the section of any point just can with and must be vertical with XOY plane.
Generally, the first curve be exactly blade back edge line (curved edges of side opposite to the direction of rotation, i.e.,
The rear side border 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 into blade
Curved surface, does not affect on 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 as back edge line using the first curve.
The second spoon of blade is illustrated 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 on ST curves, i.e. the 4th curve are taken up an official post
Anticipate at 2 points different parallel to axial height is rotated.Take up an official post in the first curve AB and take a point J, there is unique on the 4th curve ST
One point K is corresponded to therewith, and 2 points of numerical value in Z-direction of J, K are 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 axial highly identical parallel to rotating.Cross 2 points of J, K and form circular arc on plane of reference M
JK, its radian is 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, fallen in the direction of J points not according to K points
Together, θ values also have the difference of positive and negative values, θ=0 when J, K overlap.
The first spoon of blade with the first curve AB as back edge line is converted to ST curves as back by following rule
Second spoon of blade of edge line, its concrete grammar is：In making the first spoon of blade M1, the point of z values identical with J points is all with Z axis
Rotary shaft, to K points radian θ is rotated, and allows J points to travel through the first curve AB, so as to obtain with ST be new back edge line build the
Two spoon of blades.That is, by the first spoon of blade in the Z-axis direction height identical point keep mutual alignment it is constant around
The point that Z axis are rotated to the first curve overlaps with height identical point on the 4th curve, forms the second spoon of blade.If the 4th is bent
Line ST can represent with function, then can be briefly described for the first spoon of blade a little rotate the radian of θ=F (z) about the z axis
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, referred to as third blade curved surface merely with the plane of reference, 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 overlaps with near-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 by the first spoon of blade, the second spoon of blade, third blade curved surface any one constitute.
In a preferred embodiment, the first curve AB can be cycloid.
In a preferred embodiment, in some cases, the first curve burble point W overlaps with distal end A, and A point tangent lines
It is parallel with rotary shaft, now can further limit the curved surface features of the first spoon of blade and the second spoon of blade.For example, as schemed
Shown in 7, any point P3 is taken on the first spoon of blade, cross the parallel lines that point P3 makees Z axis, spacing of the parallel lines away from Z axis is
R, with the plane of reference M point Q3 is intersected at.When the parallel lines are radially moved to Z axis, point P3 and point Q3 the distance between with R's
Square in inverse proportion be incremented by.Thus obtained first spoon of blade is still obtained by the way of aforesaid 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 tangent line of the part plane of reference of curve side opposite to the direction of rotation and/or the first curve distal end is parallel with rotary shaft,
The part cylindrical surface that the remote edge line of the first spoon of blade extends straight up along Z axis, or any part of above-mentioned curved surface.
The part plane of reference and/or the first curve distal end of second spoon of blade also including the first curve side opposite to the direction of rotation
Tangent line it is parallel with rotary shaft when, the part cylindrical surface that the remote edge line of the second spoon of blade extends straight up along Z axis, or
Any part of above-mentioned curved surface.When third blade curved surface also includes that the tangent line of the first curve distal end is parallel with rotary shaft,
The part cylindrical surface that the remote edge line of third blade curved surface extends straight up along Z axis, or any part of above-mentioned curved surface.
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 meets feature (the natural extension area of in the first spoon of blade, the second spoon of blade and third blade curved surface
Except domain).The actual thickness of blade is decided according to the actual requirements on the basis of spoon of blade is met, when vane thickness is little,
" actual spoon of blade " and " spoon of blade " can be considered same curved surface.For specific certain fluid, the edge shape of blade can
To obtain as desired on actual spoon of blade.In practical application, also allow to arrange pod apertures or groove etc. on blade, such as scheme
Shown in 17, pod apertures 15 are provided with the position of rotary shaft in each blade, especially, pod apertures 15 are arranged on same circle
Zhou Shang.Pod apertures also allow streamiline wire to set up the structures such as reinforcement, or blade design is hollow arranging that cooling pipe etc. changes
It is dynamic.Due to the bending features of the first curve, whole blade has in the axial direction corresponding flexibility, is the turbo blade of the present invention
(including including single blade) is different from the key character of conventional turbine blade.
When burble point overlaps with distal end, intrinsic first spoon of blade constitutes the first spoon of blade, and thus obtains
Two spoon of blades, by the first spoon of blade or the second spoon of blade multiple-blade turbine can be formed.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 obtained by rotation
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 circulus 13.Turbine shape of the overall outline in plane of reference M, class
Like antenna pot shape.
The spoon of blade of part first and the spoon of blade of part second can also form multiple-blade turbine.Here so-called part,
Refer to the partial blade curved surface that the arbitrary curve section only taken between the first curve near-end B to burble point W is formed, that is, the first leaf
Piece curved surface or the second spoon of blade and do not include their defiber near the arbitrary portion of rotary shaft.Therefore formed after turbine,
Radial edges between adjacent blades are because apart from unequal, natural combination together, and will not by circulus 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 are because with rotary shaft apart from equal, understand natural combination together.For the fastness of structure, typically
Also blade edge is fixed together with circulus.
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 of blade production limits 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 just can be made more, and blade pitgh is bigger.
Multiple-blade turbine after assembling, from 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 typically has the part for overlapping each other, therefore cannot see the gap between blade, and 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 particular cases it can also be seen that
Gap.The blade edge shape of diagram and non-determined, true form according to specific needs (fluid, operating mode etc.) and determine.From many
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, and this is determined by the characteristic of spoon of blade.That is, the closer to whirlpool
Wheel rotary shaft, the gap between adjacent blades is bigger, and the closer to turbine edge, gap is less between blade.
Second embodiment
As shown in figure 12, single blade can also constitute a single blade turbine 2.Single blade turbine 2 only includes one with the
The turbo blade 21 that three spoon of blades are constituted, 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 at rotary shaft 22, or water conservancy diversion is set
Hole, for flow of fluid.
3rd embodiment
As shown in figure 13, multiple single blade turbines 2 may be constructed coaxial lamination turbine 3, and coaxial lamination turbine 3 also can 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, gap left from each other, the rule in gap still defers to impeller clearance universal law, i.e., along spoon of blade from
, to blade radial edge, impeller clearance is less and less, but minimum clearance is more than zero for rotary shaft.Figure 13 illustrates cuing open for partial blade
Face figure, it can be seen that the rule of impeller clearance.Practice Leaf density may be much higher than shown in Figure 13.In not notable shadow
On 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
Overall firmness, and be distributed to reduce resistance along vortex filament.Because yardstick is generally relatively fine, Figure 13 have ignored this details
Show.The hole of central vane, the general satisfaction rule that from inside to outside central vane hole increases gradually, or outer ring blade are close
Increase increase pod apertures at rotary shaft, Figure 13 also ignores the displaying of this details.
Fourth embodiment
As shown in figure 14, also multiple multiple-blade turbines 41 can be made around rotary shaft 42 that different-diameter is coaxial to be superimposed on one
The turbine for rising, 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 with third blade by intrinsic first spoon of blade or the second spoon of blade
Face composition, that is to say, that burble point neither overlaps with the distal end of the first curve, also do not overlap with the near-end of the first curve.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 burble point neither overlaps with the distal end of the first curve,
When not overlapping with the near-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 end points head and the tail be sequentially connected with, and concave towards it is identical,
A'B' curves are expanded downwards from B end points, and from A ends A " B " curve is extended up out, and AB curves, A'B' curves, A " B " are bent
Line is satisfied by the definition of the above the first curve AB, i.e., " it is coplanar with rotary shaft and it is disjoint it is smooth without flex point and concave surface towards rotation
The sag vertical curve of rotating shaft, thereon the angle of the tangent line of any point and rotary shaft be more than or equal to 0 degree, and less than or equal to 90 degree ".A'B' is bent
Line can also continue to down extend, and A " B " curve can continue to up extend, and the curve for so being formed is referred to here as multistage phase
Connect the first curve.The curve of any of which section first rotates out of as the method previously described the plane of reference, forms multistage connected reference
Face simultaneously can obtain multistage first spoon of blade that is connected, multistage second spoon of blade that is connected, multistage connected third blade song
The composite blading curved surface that face and multistage connected above-mentioned spoon of blade are mixed.
For example, using multistage connected third blade curved surface as turbo blade, multistage connected single blade turbine is formed, and is revolved
Rotating shaft arranges hole with turbo blade junction.For example, using multistage the first spoon of blade or multistage second leaf that is connected of being connected
Piece curved surface or multistage connected composite blading curved surface form multistage connected multiple-blade turbine as turbo blade.Also, comprising multistage
The turbo blade of connected spoon of blade can equally constitute multiple-blade turbine, single blade turbine, coaxial lamination turbine and multistage
Turbine etc. and their hybrid combining form.
Below in conjunction with the accompanying drawings 10 sketching turbo driving principle, when fluid flows through blade from top to bottom, by spoon of blade,
Rotation and the common induction of stream pressure, the vortex for being close to blade is produced in the concave direction of turbine, and by effect of boundary layer to leaf
Piece transmits torque, referred to herein as induced swirl.Induced swirl promotes turbine rotation, turbine rotary motion further to strengthen induction
Vortex, therefore, turbine and induced swirl enter the mutual transmittance process of energy positive feedback, by this process, the energy of fluid input
Maximum is rapidly reached and the energy of turbine rotation output between and keep balance.The energy of flow of fluid is turned by induced swirl
Turn to the energy of turbine rotation.Different by the principle that fluid propulsive thrust produces rotation from conventional turbine, this turbine is by fluid
Induced swirl by effect of boundary layer promote rotation.
Single blade turbine and coaxial lamination turbine are applied to the fluid situations of high reynolds number.Single blade turbine and coaxial lamination
Turbine needs to be previously applied an initial rotational movement and just can start running, and after rotary motion starts, above-mentioned principle is still fitted
With.
In theory all fluids can use the turbine of the present invention to carry out energy exchange.It is particularly suited for wind power turbine
And hydroelectric turbines, can be also widely applied to steam turbine and gas turbine blade design at different levels.Can be also used for driving fluid,
In such as various pumps and airfoil design.
The turbine of the present invention has little moment of torsion, 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 near central area, that is, turbine is flowed out from the minimum region of linear velocity, it is ensured that fluid flows out turbine
Speed be to tend to minimum, it is meant that the remaining kinetic energy of fluid tends to minimum.Also, due to turbine each point linear velocity not
With so as to produce Coriolis force, turbine rotation is promoted.Because centrifugal force increased the pressure between fluid and blade so that whirlpool
Wheel obtains main torque.Due to the flow field of induced swirl, in the application such as gas turbine, vortex flow field can produce radial temperature
Gradient, the lip temperature for being close to vortex is high, and the central temperature for being close to vortex is low, and the fluid temperature (F.T.) for this ensures that thering discharge is low,
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
To reach absolutely, the wind-force therefore not brought is lost in.Again because the high speed of rotation, energy catharsis in time carrys out air quantity, no
Windage can be increased reduces efficiency.
The turbine that the present invention provides a kind of vortex using artificial manufacture in fluid to drive.The present invention proposes the surface of second order
Turbo blade concept, using the turbine and turbine group of turbo blade composition, by the coupling for being vortexed 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 to be superimposed an axial bending, with this
Eddy field, i.e. blade rotary motion manufacture vortex field in a fluid is formed, Coriolis force is produced in flow field and is passed through
Effect of boundary layer promotes blade to accelerate rotation, and between vortex and blade positive feedback is formed, and with this high-energy conversion ratio is reached.It is this
The benefit that drive pattern brings also includes the thermal efficiency using applications such as the temperature gradient effect of vortex field, raising gas turbines.
Because when fluid flows out this novel turbine, remaining kinetic energy and enthalpy are respectively less than typical turbine, its energy difference with initial fluid
The rotation acting of promotion blade is both used in, so having reached the purpose for improving efficiency.
The preferred embodiments of the present invention are the foregoing is only, the present invention is not limited to, for those skilled in the art
For member, the present invention can have various modifications and variations.All any modifications within the spirit and principles in the present invention, made,
Equivalent, improvement etc., should be included within the scope of the present invention.
Claims (13)
1. a kind of turbo blade, when ignoring vane thickness, its spoon of blade is the first spoon of blade, the second spoon of blade or the 3rd
One in spoon of blade,
First curve (AB) is coplanar with rotary shaft and disjoint smooth sag vertical curve without flex point, the concave surface direction of the first curve
Rotary shaft, the end points of the close rotary shaft of the first curve is referred to as near-end, and the first curve is referred to as distal end away from the end points of rotary shaft,
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 leaf is extended in the first curve to direction of rotation side
Piece curved surface (M1),
All the time there is burble point, on the first curve, the curved section between burble point and near-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
Close, the burble point rotates the circular arc line for producing around rotary shaft and is referred to as defiber, and it is bent that the defiber constitutes intrinsic first blade
Face and the boundary line of additional surface, the point on intrinsic first spoon of blade not with the plane of reference overlap and intersect,
Any point (P2) on intrinsic first spoon of blade, on intrinsic first spoon of blade the second curve is formed, and second is bent
Any point on line is equal with the distance of rotary shaft,
Any point on intrinsic first spoon of blade, forms the 3rd curve on intrinsic first spoon of blade, and the 3rd is bent
Any point on line was on intrinsic first spoon of blade in the same plane of any point and rotary shaft, described excessively
Levy the normal of any point on the first spoon of blade and form intersection point (Q) with the plane of reference,
If also, on intrinsic first spoon of blade any point along the second curve to the side shifting of direction of rotation one, 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 gradually
Increase,
If also, any point is moved along the 3rd curve to rotation direction of principal axis on intrinsic first spoon of blade, the intersection point (Q)
Also the homologous thread track on the plane of reference is simultaneously mobile, then with any point and the friendship on intrinsic first spoon of blade
Distance gradually increases between point, and the difference of the curvature of the homologous thread track of the described 3rd bent curvature of a curve and point of intersection also gradually increases
Greatly,
And travel through whole intrinsic first spoon of blade, on intrinsic first spoon of blade normal of any point all the time 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 at 2 points different parallel to axial height is rotated, also, on the 4th curve it is total have it is unique a little and the first curve
On any point parallel to rotate it is axial highly identical,
By height identical point keeps relative position constant and around rotation on parallel to rotation direction of principal axis on the first spoon of blade
Axle rotates, until the point of the first curve overlaps with height identical point 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 for being formed that rotated a circle around rotary shaft by the first curve；
Wherein, if burble point overlaps with distal end, intrinsic first spoon of blade constitutes the first spoon of blade, if burble point and near-end
Overlap, the first spoon of blade is equal to third blade curved surface.
2. turbo blade according to claim 1, it is characterised in that the first spoon of blade also extends including the first curve
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 rotation direction of principal axis
Naturally the part cylindrical surface for extending is smoothed；
Second spoon of blade also include the part plane of reference of side opposite to the direction of rotation that the first curve extends 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 rotation direction of principal axis
Naturally the part cylindrical surface for extending is smoothed；
When third blade curved surface also includes that the tangent line of the first curve distal end is parallel with rotary shaft, the distal end of third blade curved surface
Edge line smooths the part cylindrical surface for extending along rotation direction of principal axis naturally.
3. turbo blade according to claim 1, it is characterised in that first curve is cycloid.
4. turbo blade according to claim 1, it is characterised in that any point is in institute on intrinsic first spoon of blade
State when making away from moving radially of the axis of rotation on intrinsic first spoon of blade, any point and ginseng on intrinsic first spoon of blade
Face is examined parallel to rotating axial distance 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, it is characterised 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 is 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
Comprising defiber.
6. turbo blade according to claim 1, it is characterised in that multistage meets the curve of the first curvilinear characteristic and concaves towards
Cause and be sequentially connected with from beginning to end, form multistage first curve that is connected, and multistage connected first is formed by multistage first curve that is connected
Spoon of blade, multistage be connected the second spoon of blade, multistage connected third blade curved surface, multistage connected composite blading curved surface,
Wherein, multistage be connected the first spoon of blade each section all meets the curved surface features of the first spoon of blade,
Multistage be connected the second spoon of blade each section all meets the curved surface features of the second spoon of blade,
Each section of multistage connected third blade curved surface all meets the curved surface features of third blade curved surface,
Each section of multistage connected composite blading curved surface 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 first spoon of blade that is connected, multistage the second spoon of blade, the multistage connected third blade of being connected
One in curved surface or multistage connected composite blading curved surface.
7. turbo blade according to claim 1, it is characterised in that the position on turbo blade near rotary shaft offers
Penetrate the pod apertures of turbo blade.
8. turbo blade according to claim 6, it is characterised in that be connected the 3rd using multistage described in claim 6
Spoon of blade forms multistage connected single blade turbine as turbo blade, and rotary shaft is provided with hole with turbo blade junction
Hole.
9. turbo blade according to claim 6, it is characterised in that be connected first using multistage described in claim 6
Spoon of blade or multistage connected second spoon of blade or multistage connected composite blading curved surface form multistage being connected as turbo blade
Multiple-blade turbine.
10. a kind of single blade turbine, using the third blade curved surface any one of claims 1 to 3 as turbo blade,
Single blade turbine is formed, and rotary shaft arranges hole with turbo blade junction.
11. single blade turbines according to claim 10, it is characterised in that multiple single blade turbines of different sizes are coaxial
It is stacked together, forms coaxial lamination turbine, also, along spoon of blade from rotary shaft to blade radial edge, between blade
Gap is less and less.
A kind of 12. multiple-blade turbines, it is bent using the first spoon of blade any one of claim 1 to 5 or the second blade
Face as turbo blade, together with each blade is concentrically fitted to towards identical mode with concave curved surface with rotary shaft, wherein, own
First curve of spoon of blade is arranged on the plane of reference obtained by the rotation of the first curve, along the circumferential direction uniform around rotary shaft
Arrangement blade, the plane of reference or special circulus that radial edges are integrated by seamless combination is fixed together to form leafy
Piece turbine.
13. multiple-blade turbines according to claim 12, it is characterised 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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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN113982988A (en) * | 2020-04-16 | 2022-01-28 | 李伟 | Centrifugal axial flow turbine and novel jet engine mode and operation method |
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| CN201250794Y (en) * | 2008-09-18 | 2009-06-03 | 上海东方泵业(集团)有限公司 | Mounted impeller |
| US20130129521A1 (en) * | 2011-11-17 | 2013-05-23 | John E. Tharp | Turbine blade skirt |
| CN203649666U (en) * | 2013-12-31 | 2014-06-18 | 无锡透平叶片有限公司 | Groove structure for turbine blade air inlet edge laser cladding |
| 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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| 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 |
| CN113982988A (en) * | 2020-04-16 | 2022-01-28 | 李伟 | Centrifugal axial flow turbine and novel jet engine mode and operation method |
| CN113982988B (en) * | 2020-04-16 | 2023-04-25 | 李伟 | Centrifugal axial flow turbine and novel jet engine mode and operation method |
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