CN216834227U - Laminar flow wing blade structure and propeller - Google Patents
Laminar flow wing blade structure and propeller Download PDFInfo
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- CN216834227U CN216834227U CN202220369293.0U CN202220369293U CN216834227U CN 216834227 U CN216834227 U CN 216834227U CN 202220369293 U CN202220369293 U CN 202220369293U CN 216834227 U CN216834227 U CN 216834227U
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Abstract
The utility model discloses a laminar flow wing type blade structure and a propeller, which comprises blades, wherein the wing type family to which the blades belong is a laminar flow wing type, and the blades are respectively provided with a blade tip end and a blade root end; the blades are respectively provided with a section airfoil maximum thickness and a section airfoil chord length, the section airfoil maximum thickness is the airfoil maximum thickness of the section airfoil chord length in the normal direction of the section airfoil chord length, and the ratio of the section airfoil maximum thickness to the section airfoil chord length forms a relative thickness value of the airfoil; along the direction from the tip end to the root end of the propeller, the cross section shape of the propeller blade is gradually changed, the chord length of the section airfoil is gradually increased, and the relative thickness value of the airfoil is gradually reduced. The propeller solves the technical problems that the propeller structure is large in overall size design and weight and inconvenient to carry and transport, the propeller structure is limited in assistance brought by improving the power efficiency due to the existing streamline design blades, the motor power is limited to be converted into the propulsion power to a greater extent, the energy consumption is improved, and the propeller structure is difficult to exert the optimal performance.
Description
Technical Field
The utility model relates to a hydrodynamic force hydrodynamics designs technical field, particularly, relates to a surface of water, for underwater vehicle laminar flow wing section paddle structure, screw.
Background
At present, the propeller structure of the water wing plate is formed by combining a columnar propeller rod and a shovel-shaped propeller blade. The blade is generally in a special streamline shape, namely, the section shape of the blade can be synchronously changed along with the continuous change of the distance between the blade and a blade rod, so that the power efficiency is increased on the basis of the conventional blade.
However, when a requirement of a certain power efficiency needs to be met, because the existing streamline design has limited help for improving the power efficiency, the size of the blade has to be increased to improve the efficiency, so that the blade with the existing streamline design still has the problems of large size design and large overall weight of the propeller structure in practical application, further causing inconvenience in carrying and transportation, and limiting the motor power to be converted into propulsion power to a greater extent, improving the energy consumption, and the propeller structure is difficult to exert the optimal performance.
SUMMERY OF THE UTILITY MODEL
Therefore, the utility model provides a laminar flow wing section paddle structure, screw to the streamlined design paddle of solving among the prior art is limited to the help that promotes power efficiency and bring, and the screw structure overall dimension design and weight that lead to are big on the left and right sides, and carry the transportation inconvenience, and have restricted the bigger limit of motor power to convert into propulsive power, and screw structure is difficult to exert the technical problem of optimal performance.
In order to achieve the above object, the present invention provides the following technical solutions:
a laminar flow airfoil blade structure comprises blades, wherein the airfoil family to which the blades belong is a laminar flow airfoil, and the blades are respectively provided with a blade tip end and a blade root end;
the blade is respectively provided with a section airfoil maximum thickness and a section airfoil chord length, the section airfoil maximum thickness is the airfoil maximum thickness of the section airfoil chord length in the normal direction of the section airfoil chord length, and the ratio of the section airfoil maximum thickness to the section airfoil chord length forms the relative thickness value of the airfoil;
along the direction of oar tip to the oar root end, the cross sectional shape of paddle changes gradually, the section airfoil chord length progressively increases, the relative thickness numerical value of airfoil progressively reduces.
On the basis of the above technical solution, it is right that the present invention is further explained as follows:
as a further proposal of the utility model, the shape of the paddle is a Kaplan series shape, and the tip of the paddle is a flat head.
As a further aspect of the present invention, the paddle forms an outer duct, the paddle tip with parallel correspondence between the outer ducts.
As a further aspect of the present invention, the two sides of the paddle have a pressure surface and a suction surface in a one-to-one correspondence, the pressure surface and the suction surface are arranged opposite to each other, and the suction surface is a smooth outer convex surface.
As a further aspect of the present invention, the propeller outer diameter that the paddle formed is 0.12m, the propeller radius that the paddle formed does half of the propeller outer diameter, the propeller radius is 0.06 m.
As a further aspect of the present invention, the paddle has a pitch, the pitch is a distance that the plane of the paddle passes through by a rotation circle in the non-flowing medium, the pitch with the ratio between the outer diameters of the propellers forms a forward speed coefficient.
Along the direction from the propeller tip end to the propeller root end, the cross-sectional shape of the blade at the real-time position between the propeller tip end and the propeller root end is gradually changed, and the ratio of the section airfoil chord length to the outer diameter of the propeller and the advancing speed coefficient are gradually changed.
As a further aspect of the present invention, along the direction from the tip end of the propeller to the root end of the propeller, the ratio between the chord length of the cross-section airfoil and the outer diameter of the propeller is gradually increased; the gradual change sequence of the acceleration coefficient is firstly reduced, then increased and then reduced.
As a further aspect of the present invention, the blade further has a blade angle, a lateral bevel angle, and a pitch angle.
The blade angle is the twist angle of the blade, the twist angle of the blade is the included angle between the straight line where the chord length of the section airfoil is located and the rotating plane where the blade is located, the included angle is changed synchronously along with the change of the radius of the propeller, the cross section shape of the blade at the real-time position between the blade tip end and the blade root end is gradually changed along the direction from the blade tip end to the blade root end, and the blade angle is gradually reduced.
The blade is provided with an orthographic projection, the outline of the orthographic projection is a projection outline, the projection outline is a symmetrical blade shape based on a central reference line, and the lateral oblique angle and the pitch angle are unchanged.
A propeller comprises a columnar propeller rod and a laminar flow airfoil blade structure.
The paddle is provided with three blades, and the three blades are uniformly and fixedly connected to the outer side of the paddle rod.
The paddle tip end is located at one side end of the paddle, which is far away from the paddle rod, and the paddle root end is located at one side end of the paddle, which is close to the paddle rod.
The utility model discloses following beneficial effect has:
this structural shape can effectively promote the power efficiency of screw in practical application under specific operating mode, can accomplish the minimum with the screw size simultaneously under the prerequisite of guaranteeing efficiency, and the aspect is carried, lightens weight.
Drawings
In order to clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below, and the structures, proportions, sizes, etc. shown in the present specification are only used to match the contents disclosed in the specification, so as to be understood and read by those skilled in the art, and any modifications of the structures, changes of the proportion relations, or adjustments of the sizes, should still fall within the scope of the technical contents disclosed in the present invention without affecting the functions and the achievable objects of the present invention.
Fig. 1 is the embodiment of the present invention provides a schematic view of an overall structure of a laminar flow airfoil blade structure and a propeller.
Fig. 2 is a schematic view of a laminar flow airfoil blade structure and a projection structure of a propeller in the axial direction of a propeller shaft provided by an embodiment of the present invention.
Fig. 3 is a schematic view of a laminar flow airfoil blade structure and a projection structure of a propeller on a radial direction of a blade rod provided by an embodiment of the present invention.
Fig. 4 is a schematic distribution diagram of a laminar flow airfoil blade structure in a cross-sectional shape from a blade tip to a blade root according to an embodiment of the present invention.
Fig. 5 is a schematic diagram of a performance curve of a propeller according to an embodiment of the present invention.
Fig. 6 is a schematic diagram of a performance curve of a propeller according to an embodiment of the present invention.
In the drawings, the components represented by the respective reference numerals are listed below:
a paddle lever 1;
the paddle 2: tip 21, root 22, pressure surface 23, suction surface 24.
The outer diameter D of the propeller, the radius R of the propeller, the chord length c of the section airfoil and the maximum thickness t of the section airfoil0The pitch P.
Detailed Description
The present invention is described in terms of specific embodiments, and other advantages and benefits of the present invention will become apparent to those skilled in the art from the following disclosure. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In the present specification, the terms "upper", "lower", "left", "right" and "middle" are used for convenience of description, and are not intended to limit the scope of the present invention, and changes or adjustments of the relative relationship thereof without substantial changes in the technical content should be regarded as the scope of the present invention.
As shown in fig. 1 to 4, the embodiment of the present invention provides a laminar flow airfoil blade structure and a propeller, including a columnar blade rod 1 and three blades 2 uniformly and fixedly connected to the outer side of the blade rod 1, so as to overcome the medium resistance through the rotation of the blades 2 to realize the predetermined propulsion function.
Specifically, with continued reference to fig. 1 and 2, the blade 2 is in the shape of a kaplan series of shapes, and the blades 2 respectively have a tip 21 end far away from the shaft 1 and a root 22 end near the shaft 1, wherein the tip 21 end is a flat end, and the tip 21 end and the outer duct of the propeller (the air flow channel of the blade 2) are in parallel correspondence.
Referring to fig. 3 and 4, the blade 2 formed from the root 22 to the tip 21 is an airfoil of NACA65A0xx series (where xx is a percentage of a cross-sectional airfoil thickness to a cross-sectional airfoil chord length c), the airfoil family to which the blade 2 belongs is a laminar airfoil, two surfaces of the blade 2 respectively correspond to a pressure surface 23 and a suction surface 24 one by one, the pressure surface 23 and the suction surface 24 are disposed away from each other, and the suction surface 24 is a smooth outer convex surface, so that a surface pressure distribution generated by the suction surface 24 when the medium with a predetermined flow velocity passes through the suction surface 24 is relatively flat, on one hand, a laminar area is enlarged, and a resistance is relatively low; on the other hand, a higher pressure peak value is avoided, cavitation is not easy to occur, and the propelling efficiency is improved.
On any of the blades 2, the cross-sectional shape of the blade 2 gradually changes along the direction from the tip 21 end to the root 22 end, and the specific geometrical information of the cross section of a typical position is shown in the following table 1.
In the embodiment of the present invention, please refer to fig. 2, the diameter of the propeller shaft 1 is 0.04m, the outer diameter D of the propeller is 0.12m, and the radius R of the propeller is D/2 ═ 0.06 m.
Referring to FIG. 3, c is the chord length of the airfoil section, i.e., the maximum length of the connecting line between two end points of the airfoil section, and c/D is the ratio of the chord length to the maximum length; t is t0Is the maximum thickness of the sectional airfoil, i.e. the maximum thickness of the sectional airfoil in the direction of the normal of the chord length c thereof, t0The/c is the ratio of the two, and refers to the relative thickness value of the airfoil; p is the pitch, namely the distance covered by the plane where the propeller rotates for one circle in the non-flowing medium and the blade 2 is located, and P/D is the ratio of the two, and the P/D refers to the advancing speed coefficient. Pitch is a blade angle, that is, a twist angle of the blade 2, and refers to an included angle between a straight line where a section airfoil chord length c of the blade 2 is located and a rotation plane where the blade 2 is located, and the included angle changes with the change of the propeller radius R, and the change rule is the most important factor influencing the working performance of the blade 2.
The propeller needs to be specially designed according to common working conditions in order to achieve optimal efficiency, otherwise the propeller cannot achieve optimal performance, and cannot convert the motor power into propulsion power to the maximum extent.
The embodiment of the utility model provides an above-mentioned data design is applied to the revolution and is 3000rpm, and the pulling force is 13kg, and the speed of a ship is near this use operating mode of 25km/h and the special design who goes on for the screw has the biggest propulsion efficiency performance. The specific performance curve is shown in fig. 5, where KT is the coefficient of tension, KQ is the coefficient of torque, EFFY is the efficiency, and Js is the forward ratio.
As a preferred solution of the present embodiment, besides applying the above-determined geometric shape to the thickness of the existing propeller blade, the thickness of the blade 2 is increased by a geometric shape of 0.2mm to 0.4mm on the whole of the pressure surface 23 and/or the suction surface 24, and the present invention also belongs to the protection scope of the present invention.
The suction surface 24 of the blade 2 in the above embodiment adopts a smooth outer convex surface, so that a performance curve that the surface pressure distribution generated by the suction surface 24 when passing through a medium with a given flow velocity is relatively flat is shown in fig. 6, and a first line from top to bottom can be seen as relatively flat, which means that the pressure peak value is relatively low and cavitation is not easy to occur, and if the laminar flow airfoil and the suction surface 24 are not arranged, the line is greatly expanded, so that the laminar flow area is expanded on one hand, and the resistance is relatively low; on the other hand, a higher pressure peak value is avoided, cavitation is not easy to occur, and the propelling efficiency is improved.
Although the invention has been described in detail with respect to the general description and the specific embodiments, it will be apparent to those skilled in the art that modifications and improvements can be made based on the invention. Therefore, such modifications and improvements are intended to be within the scope of the invention as claimed.
Claims (9)
1. A laminar flow airfoil blade structure comprises blades and is characterized in that an airfoil family to which the blades belong is a laminar flow airfoil, and the blades are respectively provided with a blade tip end and a blade root end;
the blade is respectively provided with a section airfoil maximum thickness and a section airfoil chord length, the section airfoil maximum thickness is the airfoil maximum thickness of the section airfoil chord length in the normal direction of the section airfoil chord length, and the ratio of the section airfoil maximum thickness to the section airfoil chord length forms the relative thickness value of the airfoil;
along the direction of oar tip to the oar root end, the cross sectional shape of paddle changes gradually, the section airfoil chord length progressively increases, the relative thickness numerical value of airfoil progressively reduces.
2. The laminar flow airfoil blade structure of claim 1,
the shape of the paddle is a Kaplan series shape, and the tip of the paddle is a flat head.
3. The laminar flow airfoil blade structure of claim 2,
the blades form an outer duct, and the tips of the blades correspond to the outer duct in parallel.
4. The laminar flow airfoil blade structure of claim 1,
the two sides of the paddle are respectively provided with a pressure surface and a suction surface in a one-to-one correspondence mode, the pressure surface and the suction surface are arranged in a back-to-back mode, and the suction surface is a smooth outer convex surface.
5. The laminar flow airfoil blade structure of claim 1,
the propeller outer diameter that the paddle formed is 0.12m, the propeller radius that the paddle formed is half of the propeller outer diameter, the propeller radius is 0.06 m.
6. The laminar flow airfoil blade structure of claim 5,
the propeller is characterized in that the propeller blade has a pitch, the pitch is the distance which the plane of the propeller blade rotates for one circle in a non-flowing medium, and the ratio of the pitch to the outer diameter of the propeller forms a speed advancing coefficient;
along the direction from the propeller tip end to the propeller root end, the cross-sectional shape of the blade at the real-time position between the propeller tip end and the propeller root end is gradually changed, and the ratio of the section airfoil chord length to the outer diameter of the propeller and the advancing speed coefficient are gradually changed.
7. The laminar flow airfoil blade structure of claim 6,
the ratio of the section airfoil chord length to the propeller outer diameter is gradually increased along the direction from the propeller tip end to the propeller root end; the gradual change sequence of the acceleration coefficient is firstly reduced, then increased and then reduced.
8. The laminar flow airfoil blade structure of claim 6,
the blade also has a blade angle, a side cant angle, and a pitch angle;
the blade angle is the twist angle of the blade, the twist angle of the blade is the included angle between the straight line where the chord length of the section airfoil is located and the rotating plane where the blade is located, the included angle is synchronously changed along with the change of the radius of the propeller, the cross section shape of the blade at the real-time position between the blade tip end and the blade root end is gradually changed along the direction from the blade tip end to the blade root end, and the blade angle is gradually reduced;
the blade is provided with an orthographic projection, the outline of the orthographic projection is a projection outline, the projection outline is a symmetrical blade shape based on a central reference line, and the lateral oblique angle and the pitch angle are unchanged.
9. A propeller comprising a cylindrical shaft, further comprising a laminar flow airfoil blade structure according to any of claims 1-8;
the number of the blades is three, and the three blades are uniformly and fixedly connected to the outer side of the paddle rod;
the paddle tip end is located at one side end of the paddle, which is far away from the paddle rod, and the paddle root end is located at one side end of the paddle, which is close to the paddle rod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220369293.0U CN216834227U (en) | 2022-02-23 | 2022-02-23 | Laminar flow wing blade structure and propeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220369293.0U CN216834227U (en) | 2022-02-23 | 2022-02-23 | Laminar flow wing blade structure and propeller |
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| Publication Number | Publication Date |
|---|---|
| CN216834227U true CN216834227U (en) | 2022-06-28 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202220369293.0U Active CN216834227U (en) | 2022-02-23 | 2022-02-23 | Laminar flow wing blade structure and propeller |
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| Country | Link |
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| CN (1) | CN216834227U (en) |
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- 2022-02-23 CN CN202220369293.0U patent/CN216834227U/en active Active
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