WO2019155656A1 - Hélice, procédé de conception d'hélice, programme pour procédé de conception d'hélice et support de stockage d'informations - Google Patents

Hélice, procédé de conception d'hélice, programme pour procédé de conception d'hélice et support de stockage d'informations Download PDF

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Publication number
WO2019155656A1
WO2019155656A1 PCT/JP2018/027481 JP2018027481W WO2019155656A1 WO 2019155656 A1 WO2019155656 A1 WO 2019155656A1 JP 2018027481 W JP2018027481 W JP 2018027481W WO 2019155656 A1 WO2019155656 A1 WO 2019155656A1
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WIPO (PCT)
Prior art keywords
blade
propeller
line
rotor blade
axis
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Application number
PCT/JP2018/027481
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English (en)
Japanese (ja)
Inventor
嶋　英志
誠司 堤
圭一郎 藤本
Original Assignee
国立研究開発法人宇宙航空研究開発機構
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Publication of WO2019155656A1 publication Critical patent/WO2019155656A1/fr

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    • 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
    • B64C11/18—Aerodynamic features
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03D—WIND MOTORS
    • F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
    • F03D1/06—Rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/30—Vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/72—Wind turbines with rotation axis in wind direction
    • 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
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Definitions

  • the present invention relates to a propeller, a propeller design method, a propeller design method program, and an information storage medium.
  • Propellers are widely used in air supply and aircraft propulsion engines. Some propeller blades have a loop shape for the purpose of improving the efficiency of the propeller (see, for example, Patent Document 1).
  • the external force acting on the propeller in the air is mainly centrifugal force, and the loop shape cannot be maintained at the time of rotation with a lightweight configuration unless appropriate consideration is given to the centrifugal force. Furthermore, the propeller is also required to reduce noise.
  • an object of the present invention is to provide a propeller, a propeller design method, a propeller design method program, and an information storage medium that are configured to be lightweight, maintain a loop shape during rotation, and have a low noise. is there.
  • a propeller includes a rotating shaft and a rotating blade.
  • the rotor blade is connected around the rotation axis, and has a first rotor blade portion having a first blade upper surface and a first blade lower surface and having a receding angle, and has a second blade upper surface and a second blade lower surface and moves forward.
  • a second rotor blade having a corner The upper surface of the second blade is connected to the lower surface of the first blade, the lower surface of the second blade is connected to the upper surface of the first blade, and a loop shape is formed by the first rotating blade portion and the second rotating blade portion.
  • the rotor blade When the direction perpendicular to the axial direction of the rotating shaft and from the rotating shaft toward the tip of the loop shape is the first direction, and the direction orthogonal to the axial direction and the first direction is the second direction, the rotor blade is centered on the rotating shaft. At least a part of the center line of the rotor blade formed when the rotor blade is rotated, the tension acting in the first direction of the rotor blade and the centrifugal force are in harmony, and the rotor blade second A catenary shape in which the tension acting in the direction and the centrifugal force are harmonized.
  • At least a part of the catenary line shape in which the centrifugal force acting on the rotor blades during rotation and the tension in the rotor blades balance becomes a loop shape, so that the rotor blades are deformed by the centrifugal force. It becomes difficult.
  • the connecting portion where the first rotating blade portion is connected to the rotating shaft and the connecting portion where the second rotating blade portion is connected to the rotating shaft are shifted in the axial direction, and the first connecting portion is the second connecting portion. You may locate in the downstream of the flow direction of air rather than a connection location.
  • the second rotating blade portion is less likely to hit the weak region emitted by the first rotating blade portion, and the rotating blade tends to rotate efficiently without receiving a load.
  • the first rotating blade portion and the second rotating blade portion may have the same angle of attack with respect to a plane orthogonal to the rotation axis.
  • the magnitudes of the twisting force of the first rotating blade received from the air and the twisting force of the second rotating blade received from the air are substantially the same, and they are offset.
  • chord line and the camber line in the rotor blade may coincide with each other at the tip of the loop shape.
  • a plurality of rotor blades may be arranged around the rotation axis, and a plurality of rotor blades may be arranged at equal intervals.
  • Such propellers tend to exert large wind power because they have multiple rotor blades.
  • the rotor blade may be made of a flexible material.
  • a propeller As described above, according to the present invention, there are provided a propeller, a propeller design method, a propeller design method program, and an information storage medium that are light in weight, maintain a loop shape during rotation, and have a low noise.
  • FIG. 1A is a schematic top view showing an example of a propeller according to the present embodiment.
  • Fig. (B) is a schematic side view showing an example of a propeller according to the present embodiment. It is an example of the flowchart of the propeller design method which concerns on this embodiment. It is a schematic diagram which shows an example of the propeller design method which concerns on this embodiment.
  • FIG. 5A is a graph showing an example of a loop-shaped imaginary line projected onto the XY axis plane.
  • FIG. 5B is a graph showing an example of a loop-shaped virtual line projected on the YZ axis plane.
  • FIG. 1 is a schematic perspective view showing an example of a propeller according to the present embodiment.
  • FIG. 2A is a schematic top view showing an example of a propeller according to the present embodiment.
  • FIG. 2B is a schematic side view showing an example of a propeller according to the present embodiment.
  • the axial direction of the rotary shaft 10 is the Z-axis direction
  • the direction orthogonal to the Z-axis direction and from the rotary shaft 10 toward the tip 201 of the rotary blade 20 is the X-axis direction (first direction)
  • a direction orthogonal to the Z-axis direction and the X-axis direction is defined as a Y-axis direction (second direction).
  • the propeller 100 of the present embodiment includes a rotating shaft 10 and a pair of rotating blades 20 connected to the rotating shaft 10.
  • the pair of rotary blades 20 are arranged on a point target, for example, with the central axis 10c of the rotary shaft 10 as the center.
  • the pair of rotary blades 20 constitutes an 8-shaped blade.
  • the rotating shaft 10 is rotated counterclockwise about the central axis 10c by an external drive system (not shown), and the pair of rotary blades 20 are rotated counterclockwise about the rotating shaft 10.
  • the pair of rotor blades 20 is made of, for example, a polyamide-based resin and has light weight and flexibility.
  • Each of the pair of rotor blades 20 includes a rotor blade portion 21 (first rotor blade portion) and a rotor blade portion 22 (second rotor blade portion).
  • the rotary blade portion 21 has a blade upper surface 211 (first blade upper surface) and a blade lower surface 212 (first blade lower surface).
  • the rotary blade portion 22 has a blade upper surface 221 (second blade upper surface) and a blade lower surface (second blade lower surface) 222.
  • the rotary blade portion 21 has a receding angle that gradually recedes along a concentric circle with the rotating shaft 10 as the center.
  • the rotary blade portion 22 has an advance angle that gradually advances along a concentric circle centered on the rotary shaft 10.
  • a loop shape is formed by the rotary blade portion 21 and the rotary blade portion 22. That is, in the rotary blade 20, the distance between the rotary blade portion 21 and the rotary blade portion 22 gradually increases as the distance from the rotary shaft 10 increases, and the distance becomes narrow after the distance has once reached the maximum.
  • the rotary blade portion 21 and the rotary blade portion 22 that are divided into two branches from the rotary shaft 10 are connected at the tip 201 of the rotary blade 20.
  • the blade main surface is twisted back in the vicinity of the loop-shaped tip 201, the blade upper surface 221 is connected to the blade lower surface 212, and the blade lower surface 222 is connected to the blade upper surface 211.
  • the rotary blade portion 21 having the receding angle receives a torsional aerodynamic force (torsion moment), and the rotary blade portion 22 having the forward angle is twisted from the air. Receives increased aerodynamics.
  • the rotary blade portion 21 and the rotary blade portion 22 are connected by the tip 201 of the rotary blade 20. Further, on the XY axis plane, the center line 21L of the rotary blade part 21 and the center line 22L of the rotary blade part 22 are arranged line-symmetrically with respect to the central axis 20c of the rotary blade 20.
  • the torsional aerodynamic force and the torsional aerodynamic force cancel each other out in the rotor blade 20, and even if the rotor blade 20 has a thin and light structure, the rotor blade 20 is not deformed by aerodynamic force. It is hard to get up.
  • the rotary blade 21 and the rotary blade 22 have the same angle of attack with respect to an XY axis plane (rotary surface) orthogonal to the rotary shaft 10.
  • size of the torsional force of the rotary blade part 21 received from air and the torsional force of the rotary blade part 22 received from air become substantially the same, and they cancel.
  • the rotor blade can be made of a strong rigid body that is not subject to torsional deformation.
  • the rotor blade having such rigidity inevitably increases in weight and cannot be reduced in weight.
  • the centrifugal force acts on the rotor blade 20 more strongly than the aerodynamic force.
  • the propeller 100 is desired to have a configuration in which the rotor blade 20 is not easily deformed even by centrifugal force.
  • a suspended line shape in which a centrifugal force acting on the rotary blade 20 during rotation and a tension in the rotary blade 20 is balanced is introduced as a loop shape.
  • the shape of at least a part of the center lines 21L and 22L formed when the rotor blade 20 rotates about the rotation shaft 10 is at an arbitrary position of at least a part of the center lines 21L and 22L.
  • a tension acting in the X-axis direction and a centrifugal force acting in the X-axis direction are harmonized, and a tension line shape in which the tension acting in the Y-axis direction of the rotor blade 20 and the centrifugal force acting in the Y-axis direction are harmonized.
  • the propeller 100 has a lightweight structure in which a bending moment does not work.
  • connection location 11 (1st connection location) where the rotary blade part 21 was connected to the rotating shaft 10
  • connection location 12 (2nd connection location) where the rotary blade part 21 was connected to the rotary shaft 10
  • the connection location 11 is located downstream of the connection location 12 in the air flow direction.
  • the shape of at least a part of the loop-shaped center lines 21L and 22L formed when the rotary blade 20 rotates about the rotation shaft 10 is an arbitrary part of at least a part of the center lines 21L and 22L.
  • the tension acting in the X-axis direction of the rotor blade 20 and the centrifugal force acting in the X-axis direction are harmonized, and the suspension force in which the tension acting in the Y-axis direction of the rotor blade 20 and the centrifugal force acting in the Y-axis direction are harmonized.
  • FIG. 3 is an example of a flowchart of the propeller design method according to the present embodiment.
  • FIG. 4 is a schematic diagram illustrating an example of a propeller design method according to the present embodiment.
  • the radius R of the propeller 100, the diameter R1 of the rotating shaft 10 (hub) of the propeller 100, the airfoil (blade cross-sectional shape) at each radial position, the chord length, and the rotation plane are formed.
  • An angle (attack angle) is determined in advance (step S101). Establish the following differential equation.
  • FIG. 4 shows an example in which the rotary blade 21 is regarded as a cable.
  • a vector extending from the center axis 10c of the rotating shaft 10 to the center line 21L of the rotating blade portion 21 is represented by r.
  • the position parameter in the X-axis direction is x
  • the position parameter in the Y-axis direction is y
  • the position parameter in the Z-axis direction is z.
  • the angular velocity at which the rotary blade portion 21 rotates around the central axis 10c of the rotary shaft 10 is ⁇
  • the material density of the rotary blade 20 is ⁇
  • the linear density of the rotary blade 20 is ⁇ line
  • S be the area of the blade cross-section definition plane 21w of the rotary blade section 21 and ⁇ be the angle between the blade cross-section definition plane 21w and the line direction of the cable (center line 21L).
  • the blade cross-section definition plane 21w is a plane that is parallel to the rotation axis 10 and arranged orthogonally.
  • a minute volume v portion with a dot
  • v S ⁇ h
  • ds the differential amount of the length along the line direction of the cable
  • h ds ⁇ sin ⁇
  • the linear density ⁇ line in the ds direction is expressed by ⁇ ⁇ S ⁇ sin ⁇ .
  • ds corresponds to an integration step value, which will be described later, and is set to ds ⁇ 0.01R (step S102).
  • T is a tension acting in the rotary blade portion 21.
  • the left sides of (1), (2), and (3) are forces acting per unit length of the X-axis, Y-axis, and Z-axis, and correspond to fx, fy, and fz.
  • the tension T z in the Z-axis direction is set as an initial value in advance.
  • R is a distance from the central axis 10c of the rotation axis 10 to the loop-shaped tip 201 on the XY axis plane.
  • T z is a tension acting in the Z-axis direction.
  • Let (x, y, z) (0, 0, 0) be the end point in line integration.
  • the linear density ⁇ line material density in the direction along the loop-shaped line of the rotor blade 20 is set to a desired value. A value is set (step S106).
  • the rotor blade goes back to the front of step S106 and takes into consideration the airfoil (blade cross-sectional shape), blade chord length, and the angle formed by the rotating surface.
  • the operation of setting the line density ⁇ line of 20 to a desired value is repeated. Thereby, a loop-shaped imaginary line is obtained.
  • FIG. 5A is a graph showing an example of a loop-shaped imaginary line projected onto the XY axis plane.
  • FIG. 5B is a graph showing an example of a loop-shaped imaginary line projected onto the YZ axis plane.
  • Q 0 and T z when Q 0 and T z are regarded as tension parameters, Q 0 and T z have a degree of freedom. From Q 0 and T z to a desired value in the Y-axis direction or the Z-axis direction by the Newton iteration method or the like. The shape of the cable (swelling in the Y-axis direction or Z-axis direction) can be determined.
  • step S109 when Q 0 is set large, the angle ⁇ formed by the X-axis direction and the cable line direction can be set large, and by setting Q 0 small, the angle ⁇ can be set small.
  • step S110 After determining whether the angle ⁇ is the target value (step S109), if the angle ⁇ is not the target value, Q 0 is corrected by the Newton method (step S110), and before step S104. Going back, the corrected Q 0 becomes the initial value, and the integration by the Runge-Kutta method is performed again.
  • the center line 21L of the rotor blade 21 and the center line 22L of the rotor blade 22 are arranged symmetrically with respect to the center axis 20c, the first miracle of the center line 21L is obtained after obtaining the miracle.
  • the virtual line of the center line 22L of the rotor blade 22 is also determined.
  • At least a part of the loop-shaped imaginary line derived from the differential equation is set as the center lines 21L and 22L of the rotor blade 20.
  • step S 111 After displacement amount Z 1 is made a determination whether the target value (step S 111), when the deviation amount Z 1 is not a target value, due Newton method, is corrected displacement amount Z 1 (step S112 ), the deviation amount Z 1 fixed becomes the initial value, integration by Runge-Kutta method is performed again.
  • the desired displacement amount Z 1 it is preferable to set at equal intervals as possible wake region emanating from a plurality of rotor blades.
  • FIG. 6 is a schematic diagram of a wake region generated by a general rotor blade.
  • spiral wake region WR generated by friction between the rotating blade BL and air or the like in the wake of the rotating blade BL (the wake of the rotation direction R) during rotation.
  • each rotor blade be arranged so as to avoid a wake region that arises from the rotor blade that rotates first.
  • each rotor blade is arranged so that the wake area interval in the Z-axis direction is L / B, each rotor blade is less likely to hit the wake area during rotation.
  • each of the pair of rotor blades 20 includes two pairs of rotor blade portions 21 and 22, the blades are substantially four blades. Therefore, the optimum value of the wake area interval in the Z-axis direction is L / 4.
  • Propeller 100 is not limited to two pairs of rotary blades 21 and 22, if they have a B 'group of the rotating wings, the optimum value of Z 1 is expressed by the following equation.
  • the wake interval differs depending on the position from the central axis 10c.
  • the wake region interval is optimized so that the width of the rotary wing part 21 (rotary wing part 22) becomes the maximum (position 70% of the distance R from the central axis 10c).
  • the shift amount (Z 1 ) may be determined based on the tension parameter T z .
  • the bulges (the magnitude of ⁇ ) of the center lines 21L and 22L and the shift amount Z 1 of the center lines 21L and 22L are determined using (Q 0 , T z ).
  • the above design procedure is automatically executed by a computer program using a computer. Further, the propeller design method program is stored in an information storage medium such as a hard disk, an optical disk, a USB memory, or a memory card.
  • the sections are arranged along the center line.
  • FIG. 7 is a schematic diagram showing the concept of a method for determining the cross section of the rotor blade.
  • FIG. 7 also shows a coordinate system (inside the broken line) when the rotary blade 21 is viewed toward the vector r.
  • the rotor blade 20 is determined by arranging two-dimensional blade cross sections along the center lines 21L and 22L.
  • the blade cross section is defined as a two-dimensional shape in the X''Y '' axis plane using the X '' axis, which is the air flow direction in the blade cross section, and the Y '' axis perpendicular to the X '' axis.
  • the in this embodiment the blade cross section is defined by the unit vector x ′, y ′ after the blade cross section is rotated on the X ”Y” axis plane by a predetermined torsion angle ⁇ and rotated by ⁇ . 20s is introduced.
  • x ′ is defined as a unit vector that is perpendicular to the vector r and has an angle ⁇ with the propeller rotation plane (XY plane). Note that the X ′′ axis is parallel to the XY plane.
  • l ′ be a unit vector indicating the direction of the center line 21L.
  • y ′ is defined as follows. Note that an axis parallel to the unit vector x ′ is an X ′ axis, and an axis parallel to the unit vector y ′ is a Y ′ axis.
  • the blade section defining section 20s is determined using the unit vectors x ′ and y ′, and the blade section defining section 20s is arranged so that the center of gravity of the blade section defining section 20s passes through the center lines 21L and 22L (step S113).
  • the cross-sectional shape of the rotor blade 20 having a loop shape is determined. That is, by using the unit vector x ′ orthogonal to the vector r and the unit vector y ′ orthogonal to the unit vector x ′ and the unit vector l ′, even if the rotor blade 20 draws a loop shape, the center line 21L , 22L and the cross section perpendicular to 22L is determined by (x ′, y ′).
  • n ′ is a normal vector of the blade cross section defining cross section 20s.
  • 8 (a) to 8 (e) are schematic diagrams showing the concept of a method for correcting the camber line of the blade cross section definition cross section.
  • the camber C of the blade cross section defining cross section 20s includes a camber line CL (line obtained by averaging the lines of the blade upper surface and the blade lower surface) and the chord line (blade cross section defining cross section 20s). The distance from the leading edge to the trailing edge).
  • the distance from the camber line CL to the blade upper surface is the thickness t / 2
  • the distance from the camber line CL to the blade lower surface is the thickness t / 2.
  • the line on the blade upper surface of the blade cross section defining section 20s is C (x ′) + t / 2
  • the line on the blade lower surface of the blade cross section defining section 20s is C (x ′) ⁇ t / 2.
  • the distance from 0 on the X ′ axis to the intersection of the X ′ axis and the camber line CL corresponds to the chord length.
  • the inner product of the vector r and the normal vector n ′ of the blade cross section defining cross section 20s is multiplied by C (x) to correct the camber along the center line (step S114).
  • the local velocity of the transverse wave running in the rotor blade 20 is a cable
  • the shape stability of the rotor blade 20 is similar to the shape stability of the jump rope when the jump rope is rotated, the shape stability of the lasso, and the like. For example, even if a jumping rope jumps to the ground and deforms greatly, it immediately returns to its original shape. Therefore, the rotary blade 20 can be made of a material that maintains a suspended shape when rotating, even if it is not suspended when not rotating (for example, when stationary).
  • the propeller 100 can significantly reduce high-frequency sound from the analysis result by the FW & H (Ffowcs. Williams-Hawkings) equation.
  • the waves may strengthen in some places, but at low frequencies, the wavelength is sufficiently long compared to the size of the propeller. As a result, even if the angle is different, the phase does not change greatly and is canceled over a wide range.
  • the Fourier component of aerodynamic sound generated from a propeller having B rotor blades and an angular frequency ⁇ can be expressed as follows in a complex number display.
  • a propeller that rotates synchronously while maintaining the phase difference of the angle ⁇ can be regarded as rotating at a time shifted by ⁇ / ⁇ , so its Fourier component is
  • n m ⁇ l + j and 0 ⁇ j ⁇ m ⁇ 1 (j: remainder when n is divided by integer m)
  • FIG. 9 is a schematic perspective view showing a propeller of a first modified example of the present embodiment.
  • a propeller 101 shown in FIG. 9 includes a cylindrical duct member 30 in addition to the propeller 100.
  • the propeller 100 is provided in the duct member 30.
  • the central axis 10 c of the propeller 100 coincides with the central axis 30 c of the duct member 30.
  • FIG. 10 is a schematic perspective view showing a propeller of a second modified example of the present embodiment.
  • the number of the rotary blades 20 is not limited to two around the rotary shaft 10 and may be three or more.
  • three rotor blades 20 are arranged at equal intervals.
  • the wind power generated by the propeller 102 increases as compared to the propeller 100 due to the increase in the number of the rotor blades 20.
  • FIG. 11 is a schematic perspective view showing a propeller of a third modified example of the present embodiment.
  • connection location 11 and the connection location 12 in the Z-axis direction are smaller than that of the propeller 100.
  • the connection location 11 and the connection location 12 are located on the same XY axis plane.
  • the rotary blade 20 is designed based on a catenary line in which centrifugal force and tension are balanced, so that the loop shape is maintained during rotation.
  • FIG. 12 is a schematic perspective view showing a propeller of a fourth modified example of the present embodiment.
  • a part of the loop shape may be a rigid body part.
  • the rotor blade 20 is less susceptible to the bending moment.
  • an extending portion 204 that also functions as a counterweight is provided near the tip portion 201.
  • FIG. 13 is a schematic perspective view showing a propeller of a fifth modification of the present embodiment.
  • the rigid body portion may be a flat portion 205 like a propeller 105 shown in FIG. With such a configuration, the propeller 105 has the same effect as the propeller 104. Furthermore, when the propeller 105 is attached to the duct member 30, since the tip portion 201 is configured by the flat portion 205, the shape affinity with the duct member 30 is improved.
  • FIG. 14 is a schematic perspective view showing a propeller of a sixth modified example of the present embodiment.
  • FIG. 14 shows the periphery of the rotating shaft 10.
  • the rigid body portion may be provided not near the tip portion 201 of the rotary blade 20 but near the rotating shaft 10.

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Abstract

Le problème décrit par la présente invention est de fournir une hélice qui est conçue pour être légère, conserve une forme de boucle pendant la rotation, et présente un faible bruit, un procédé de conception d'hélice, un programme pour procédé de conception d'hélice et un support de stockage d'informations. La solution selon la présente invention porte sur une hélice comprenant une pale rotative raccordée autour d'un arbre rotatif, et comprenant : une première partie pale rotative qui comprend une première surface supérieure de pale et une première surface inférieure de pale et présente un angle de flèche ; et une seconde partie pale rotative qui comprend une seconde surface supérieure de pale et une seconde surface inférieure de pale et présente un angle d'avance. La seconde surface supérieure de pale est continue avec la première surface inférieure de pale. La seconde surface inférieure de pale est continue avec la première surface supérieure de pale. La première partie pale rotative et la seconde partie pale rotative forment une forme de boucle. Lorsque la pale rotative se met en rotation autour de l'arbre rotatif, au moins une partie d'une ligne centrale de la pale rotative a une forme, formée dans au moins une position arbitraire partielle, correspondant à la forme d'une ligne caténaire de telle sorte qu'une tension et une force centrifuge agissant dans une première direction de la pale rotative sont équilibrées, et de telle sorte qu'une tension et une force centrifuge agissant dans une seconde direction de la pale rotative sont équilibrées.
PCT/JP2018/027481 2018-02-08 2018-07-23 Hélice, procédé de conception d'hélice, programme pour procédé de conception d'hélice et support de stockage d'informations WO2019155656A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2018021270A JP6979205B2 (ja) 2018-02-08 2018-02-08 プロペラ、プロペラの設計方法、プロペラ設計方法プログラム及び情報記憶媒体
JP2018-021270 2018-02-08

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114104266A (zh) * 2021-12-17 2022-03-01 亿航智能设备（广州）有限公司 一种螺旋桨、动力组件和飞行器
DE102021004136A1 (de) 2021-08-09 2023-02-09 Friedrich B. Grimm Vorrichtung für ein Drehflügelfahrzeug oder für eine Drehflügelturbine
GB2615531A (en) * 2022-02-09 2023-08-16 Leybold Gmbh Rotor and vacuum pump

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2002188403A (ja) * 2000-12-19 2002-07-05 Y & Y:Kk 流体機械
JP2003503643A (ja) * 1999-07-06 2003-01-28 ルドルフ バンアッシュ， 分岐型ロータブレードを備えたロータ
US20040009063A1 (en) * 2002-07-12 2004-01-15 Polacsek Ronald R. Oscillating system entraining axial flow devices
JP2006063932A (ja) * 2004-08-30 2006-03-09 Akira Miyanishi 風車
JP2016502034A (ja) * 2013-01-04 2016-01-21 イヴァン ペルヌＹｖａｎ ＰＥＲＲＥＮＯＵＤ 螺旋状のタービンブレード
JP2016222242A (ja) * 2012-12-10 2016-12-28 シャロウ エンジニアリング リミティド ライアビリティ カンパニー プロペラ

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2003503643A (ja) * 1999-07-06 2003-01-28 ルドルフ バンアッシュ， 分岐型ロータブレードを備えたロータ
JP2002188403A (ja) * 2000-12-19 2002-07-05 Y & Y:Kk 流体機械
US20040009063A1 (en) * 2002-07-12 2004-01-15 Polacsek Ronald R. Oscillating system entraining axial flow devices
JP2006063932A (ja) * 2004-08-30 2006-03-09 Akira Miyanishi 風車
JP2016222242A (ja) * 2012-12-10 2016-12-28 シャロウ エンジニアリング リミティド ライアビリティ カンパニー プロペラ
JP2016502034A (ja) * 2013-01-04 2016-01-21 イヴァン ペルヌＹｖａｎ ＰＥＲＲＥＮＯＵＤ 螺旋状のタービンブレード

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102021004136A1 (de) 2021-08-09 2023-02-09 Friedrich B. Grimm Vorrichtung für ein Drehflügelfahrzeug oder für eine Drehflügelturbine
WO2023016901A1 (fr) 2021-08-09 2023-02-16 Friedrich Grimm Véhicule à voilure tournante et turbine à voilure tournante
DE102021004136B4 (de) 2021-08-09 2023-03-09 Friedrich B. Grimm Vorrichtung für ein Drehflügelfahrzeug oder für eine Drehflügelturbine
CN114104266A (zh) * 2021-12-17 2022-03-01 亿航智能设备（广州）有限公司 一种螺旋桨、动力组件和飞行器
GB2615531A (en) * 2022-02-09 2023-08-16 Leybold Gmbh Rotor and vacuum pump
GB2615531B (en) * 2022-02-09 2024-04-24 Leybold Gmbh Rotor and vacuum pump

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