WO2020065304A1 - Propulseur cycloïdal - Google Patents

Propulseur cycloïdal Download PDF

Info

Publication number
WO2020065304A1
WO2020065304A1 PCT/GB2019/052698 GB2019052698W WO2020065304A1 WO 2020065304 A1 WO2020065304 A1 WO 2020065304A1 GB 2019052698 W GB2019052698 W GB 2019052698W WO 2020065304 A1 WO2020065304 A1 WO 2020065304A1
Authority
WO
WIPO (PCT)
Prior art keywords
fluid flow
blade
cyclorotor
rotation
pitch angle
Prior art date
Application number
PCT/GB2019/052698
Other languages
English (en)
Inventor
Harry BUTT
Qazi Rashid ALI
Original Assignee
Coventry University
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Coventry University filed Critical Coventry University
Publication of WO2020065304A1 publication Critical patent/WO2020065304A1/fr

Links

Classifications

    • 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
    • B64C11/30—Blade pitch-changing mechanisms
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/003—Aircraft not otherwise provided for with wings, paddle wheels, bladed wheels, moving or rotating in relation to the fuselage
    • B64C39/005—Aircraft not otherwise provided for with wings, paddle wheels, bladed wheels, moving or rotating in relation to the fuselage about a horizontal transversal axis

Definitions

  • the present invention relates to cyclorotors and in particular to actively configured cyclorotors.
  • a cyclorotor comprises a plurality of blades arranged around a central rotation axis. Each blade has a spanwise axis parallel to the axis of rotation.
  • Cyclorotors have primarily been developed for use as a means of propulsion and/or lift for air or water vehicles. The motion of the blades creates lift forces as they travel through the air or water. By varying the pitch of the blades as they rotate, the resultant lift forces created by each blade can be coordinated to provide an overall force in a desired direction. This is generally achieved by a mechanical linkage varying the pitch of the blades as the cyclorotor rotates. By adjusting the phase of the pitch variation relative to the rotation, the resultant force from the cyclorotor can be varied in direction.
  • a cyclorotor has a horizontal axis of rotation
  • the blades are driven to a positive pitch angle on the upper half of the rotation and a negative pitch angle on the lower half of the rotation.
  • a cyclorotor can be driven by a fluid flow and in turn drive a shaft.
  • a cyclorotor can be used as a wind turbine or the like.
  • the pitch of the blades is varied throughout rotation in response to the wind direction and the position of the blades in the rotation cycle. This can enable lift forces generated by the blades to produce rotation in response to the wind incident upon the cyclorotor.
  • the pitch angle of each blade is typically relatively small relative to the direction of travel of the blade.
  • the pitch angle is limited to less than the stalling angle of the blade. This ensures that the blade continues to produce lift at throughout the rotation cycle.
  • a cyclorotor comprising a plurality of rotor blades arranged around a central rotation axis, each rotor blade having a spanwise axis parallel to the rotation axis wherein at least one blade is provided with pitch adjustment means operable to adjust the pitch of the blade in response to rotation about the rotation axis wherein, the pitch adjustment means is operable to vary the pitch of the blades during the rotation cycle between: a positive pitch angle with respect to the direction of local fluid flow or desired thrust; a negative pitch angle with respect to the direction of local fluid flow or desired thrust and a transverse pitch angle with respect to the direction of local fluid flow or desired thrust so as to generate positive lift, negative lift or drag as required throughout the rotation cycle.
  • a method of varying the pitch of the blades of a cyclorotor of the type comprising a plurality of rotor blades arranged around a central rotation axis, each rotor blade having a spanwise axis parallel to the rotation axis wherein at least one blade is provided with pitch adjustment means operable to adjust the pitch of the blade in response to rotation about the rotation axis
  • the method comprising the step of varying the pitch of the blades during the rotation cycle between: a positive pitch angle with respect to the direction of local fluid flow or desired thrust; a negative pitch angle with respect to the direction of local fluid flow or desired thrust and a transverse pitch angle with respect to the direction of local fluid flow or desired thrust so as to generate positive lift, negative lift or drag as required throughout the rotation cycle.
  • the pitch angle of each blade may therefore be optimised for generating positive lift, when at a positive pitch angle negative lift when at a negative pitch angle and drag when at a transverse pitch angle.
  • Presenting a blade with a transverse pitch angle restricts said blade from generating lift, but still enables said blade to generate drag.
  • this can allow a blade to generate drag to aid rotation whilst moving in the direction of an incident fluid flow when the cyclorotor is being used as a turbine or to use drag to generate thrust when the blade is moving in the direction of desired force when the cyclorotor is used to generate a propulsive force.
  • This can increase the efficiency of the cyclorotor in such applications compared to known cyclorotors that rely on blades generating positive or negative lift throughout the rotation cycle.
  • each blade is provided with dedicated pitch adjustment means.
  • the cyclorotor may comprise any suitable number of blades.
  • the key limiting factor being the diameter of the cyclorotor and the chord of the blades to allow full rotation of the blade relative to the incident flow.
  • the blades may have a substantially symmetric or cambered profile.
  • the blades may be mounted on a suitable frame.
  • the frame may comprise mounting element for mounting each end of each blade securely.
  • the mounting elements may be provided on a disc projecting from a hub or on one or more spokes projecting from a hub.
  • One hub may be connected to a shaft.
  • the shaft may facilitate the mechanical connection between the cyclorotor and a generator or motor as appropriate.
  • the blades may be arranged around a rotation axis aligned in any suitable direction. In many embodiments, the blades may be arranged around a horizontal or vertical rotation axis.
  • the pitch adjustment means for each blade may comprise one or more dedicated motors.
  • the motors may be electric motors.
  • the motors may be stepper motors, DC servomotors or the like.
  • the motors may be connected directly to the blades or may be connected via a suitable gearing arrangement. Power to the motors may be supplied via slip rings.
  • Operation of the pitch adjustment means may be controlled by a control unit.
  • the control unit may utilise any suitable form of control algorithm in one embodiment, the control algorithm may be of the Proportional, Integral and Derivative (PID) form.
  • PID Proportional, Integral and Derivative
  • the control algorithm may be a self-tuning algorithm.
  • the pitch adjustment means may be controlled in response to rotation position.
  • rotation position may be detected by use of a rotation position sensor.
  • the rotation position sensor may be connected to the control unit.
  • the rotation position sensor may comprise a shaft encoder.
  • the shaft encoder may be fitted to a rotation shaft of the cyclorotor.
  • the pitch adjustment means may be controlled in response to rotation direction or desired rotation direction.
  • Rotation direction may be detected by use of the rotation position sensor.
  • Desired rotation direction may be determined by reference to the control unit, a desired thrust direction or by reference to an external fluid flow sensor.
  • a transverse pitch angle may be a pitch angle that increases or maximises the drag produced by the blade at that particular point of the rotation cycle.
  • a transverse pitch angle may be a pitch angle that is beyond the stall condition relative to the direction of local fluid flow or desired thrust.
  • a transverse pitch angle may be a pitch angle where drag exceeds lift.
  • a transverse pitch angle may be substantially perpendicular to the direction of local fluid flow or desired thrust.
  • each blade may be driven to a transverse pitch angle for that part of the rotation cycle where the blade motion is in the same direction as local fluid flow or desired thrust or is close to said direction.
  • the pitch angle of each blade may be relatively close to the direction of local fluid flow or desired thrust at all other parts of the rotation cycle. This minimises drag and maximises beneficial lift as is known in conventional cyclorotors.
  • the blades may have a substantially neutral pitch angle with respect to the direction of local fluid flow or desired thrust when the blade motion is in the opposite direction to local fluid flow or desired thrust or is close to said direction.
  • Each blade may move to a positive pitch angle with respect to the direction of local fluid flow or desired thrust in the part of the rotation cycle between the position where the blade motion is in the opposite direction to local fluid flow or desired thrust and the position where the blade motion is in the same direction to local fluid flow or desired thrust.
  • the pitch angle of each blade may be adjusted to produce optimum positive lift, negative lift or drag depending upon the position of the blade in its rotation cycle. The optimum pitch angle may be determined by the lift characteristics of the blade.
  • Each blade may move to a negative pitch angle with respect to the direction of local fluid flow or desired thrust in the part of the rotation cycle between the position where the blade motion is in the same direction to local fluid flow or desired thrust and the position where the blade motion is in the opposite direction to local fluid flow or desired thrust.
  • the pitch angle of each blade may be adjusted to produce optimum positive lift, negative lift or drag depending upon the position of the blade in its rotation cycle.
  • the optimum pitch angle of attack may be determined by the lift characteristics of the blade.
  • the cyclorotor may be adapted to operate with any suitable fluid.
  • suitable fluids might include but are not limited to air, water of the like.
  • the cyclorotor may be incorporated into a fluid flow power extraction device.
  • a fluid flow power extraction device may comprise a generator mechanically driven by the cyclorotor.
  • the fluid flow power extraction device may comprise a plurality of cyclorotors. Each cyclorotor may be connected so as to mechanically drive a single generator or so as to mechanically drive separate dedicated generators.
  • the fluid flow power extraction device may be adapted for mounting to a building or structure.
  • the fluid flow power extraction device may be adapted to be mounted in a horizontal orientation beneath a bridge, gantry or other overhang. This can beneficially allow the fluid flow power extraction device to generate power from urban wind tunnel effects.
  • the cyclorotor may be incorporated into a fluid propulsion device.
  • a fluid propulsion device may comprise a motor operable to mechanically drive the cyclorotor.
  • the fluid propulsion device may comprise a plurality of cyclorotors. Each cyclorotor may be connected so as to be mechanically driven by a single motor or so as to be mechanically driven by separate dedicated motors.
  • the fluid propulsion device may be fitted to a vehicle.
  • the vehicle may comprise an aircraft or watercraft.
  • a fluid flow power extraction device comprising a cyclorotor according to the first aspect of the present invention or a cyclorotor driven according to the method of the second aspect of the present invention.
  • the fluid flow power extraction device of the third aspect of the present invention may incorporate any or all features of the first two aspects of the present invention as desired or as appropriate.
  • a fluid propulsion device wherein the fluid propulsion device comprises a cyclorotor according to the first aspect of the present invention or a cyclorotor driven according to the method of the second aspect of the present invention.
  • the fluid propulsion device of the fourth aspect of the present invention may incorporate any or all features of the first two aspects of the present invention as desired or as appropriate.
  • a building or structure comprising one or more fluid flow power extraction devices according to the third aspect of the present invention.
  • the building or structure of the fifth aspect of the present invention may incorporate any or all features of the first, second and third aspects of the present invention as required or as desired.
  • a vehicle comprising one or more fluid propulsion devices according to the fourth aspect of the present invention.
  • the vehicle of the sixth aspect of the present invention may incorporate any or all features of the first, second and fourth aspects of the present invention as required or as desired.
  • Figure 1 is an illustration of a cyclorotor according to the present invention
  • Figure 2 is a schematic block diagram of the operation and control elements of the cyclorotor of figure 1 ;
  • Figure 3 is a schematic illustration of the variation in blade pitch angle through a rotation cycle
  • Figure 4 is a schematic illustration of the fitting of multiple cyclorotors according to the present invention to (a) and over road gantry and (b) a bridge.
  • a cyclorotor 1 comprises a plurality of blades 2 arranged around a central rotation axis Z. Each blade 2 has a spanwise axis parallel to the axis of rotation Z. Whilst the cyclorotor in figure 1 is illustrated with eth rotation axis Z in a vertical direction, the rotation axis may equally be horizontal or in any other desired alignment.
  • the blades 2 are connected between frame elements 3a, 3b via bearings 7.
  • Each frame element 3a, 3b comprises a central hub 4 and spokes 5.
  • the frame end 3b is also connected to a drive shaft 6.
  • the drive shaft 6 can be connected either to a motor 20 so as to drive rotation of the cyclorotor 1 or to a generator 20 to enable rotation of the cyclorotor 1 to drive the generator.
  • the cyclorotor 1 of the present invention is operable to exploit drag forces as well as lift generated by the blades 2.
  • each blade 2 is provide with an individual pitch adjustment means 12, typically a motor or stepper motor.
  • separate motors 12 can be provided at each end of each blade 2.
  • the pitch adjustment means 12 is operable to controllably vary the pitch of each blade 2 individually at any desired point in the rotation cycle. Accordingly, rather than the relatively small variation in blade pitch angle relative to the tangential direction of motion achieved in known cyclorotors 1, in the present invention, the blades 2 can be driven up to a pitch angle perpendicular to the tangential direction of motion for at least part of the rotational cycle. This allows the blade to utilise drag to extract energy from a fluid flow or to use drag to generate thrust.
  • the individual pitch adjustment means 12 are controlled by a control unit 13 which is connected to a rotation sensor 14.
  • the rotation senor 14 is typically a rotary encoder. By operating the individual pitch adjustment means 12 in response to the rotation sensor 14, the motion of blades 2 can be synchronised with rotation of the cyclorotor 1.
  • the cyclorotor 1 is also shown as being connected to a motor or generator 20 by way of shaft 6.
  • FIG 3 a schematic illustration of the variation in pitch angle of a blade 2 throughout a rotary cycle is shown.
  • the blade 2 is being used to extract energy to drive clockwise rotation (as shown in figure 3) about an axis Z from a fluid flow in the direction X.
  • the blade 2 is driven to a small positive pitch angle, with respect to the direction of fluid flow X. This results in the generation of a lift force Ai by the fluid flow.
  • the lift force Ai is predominantly tangential to the rotation axis Z and thus helps drive rotation about axis Z.
  • the positive pitch angle will be selected so as to optimise positive lift characteristics and/or to facilitate transition to/from the optimum pitch angle at adjacent positions.
  • the blade 2 is driven to a small positive pitch angle, with respect to the direction of fluid flow X.
  • the pitch angle is more positive that at position A and thus closer to the stalling pitch angle of the blade, with respect to the direction of fluid flow X. This results in the generation of a lift force Bi by the fluid flow.
  • the lift force Bi is predominantly tangential to the rotation axis Z and thus helps drive rotation about axis Z.
  • the positive pitch angle will be selected so as to optimise negative lift characteristics and/or to facilitate transition to a transverse pitch angle at position C.
  • the blade 2 is driven to a transverse pitch angle substantially perpendicular to the direction of fluid flow X. This results in the generation of a drag force Ci by the fluid flow.
  • the drag force Ci is predominantly tangential to the rotation axis Z and thus helps drive rotation about axis Z.
  • the drag force Ci is substantially larger than any tangential lift force that could be generated at this stage of the rotation cycle by an alternative pitch angle of the blade 2.
  • the blade 2 is driven to a small negative pitch angle, with respect to the direction of fluid flow X.
  • the negative lift force Di, Ei or Fi is predominantly tangential to the rotation axis Z and thus helps drive rotation about axis Z.
  • the negative pitch angle will be vary at each location so as to optimise negative lift characteristics and/or to facilitate transition to/from the optimum pitch angle at adjacent positions.
  • the blade 2 is driven to a small positive pitch angle, with respect to the direction of fluid flow X. This results in the generation of a lift force Hi by the fluid flow.
  • the lift force Hi is predominantly tangential to the rotation axis Z and thus helps drive rotation about axis Z.
  • the positive pitch angle will be selected so as to optimise positive lift characteristics and/or to facilitate transition to/from the optimum pitch angle at adjacent positions.
  • the pattern of variation in pitch angle provided by the present invention thus increases the potential efficiency of the cyclorotor 1.
  • Cyclorotors 1 of the present invention may be particularly suited for use as wind turbines in an urban environment.
  • the increased efficiency of such cyclorotors and their relatively low profile allows them to be readily mounted on buildings and other urban structures whilst still producing sufficient rotation to efficiently drive a linked generator.
  • such cyclorotors can be positioned in locations where they can exploit so called urban wind tunnel effects. Such effects occur whereby buildings or other structures channel ambient winds into higher velocities in spaces between buildings.
  • FIG 4(a) the cyclorotors 1 are mounted beneath an overhead gantry 30 providing traffic information.
  • the cyclorotors 1 are mounted under the span of a bridge 40.
  • cyclorotors could be mounted in median (central reservations) of motorways or the like, utilising the wake vortex energy produced by vehicles in the offside lane.
  • the skilled man will of course appreciate that still other urban mounting locations are possible.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Control Of Water Turbines (AREA)

Abstract

L'invention concerne un propulseur cycloïdal comprenant une pluralité de pales de rotor disposées autour d'un axe de rotation central. Chaque pale de rotor comporte un axe d'envergure parallèle à l'axe de rotation. Au moins une pale est pourvue de moyens de réglage de pas actionnables pour ajuster le pas de la pale en réponse à une rotation autour de l'axe de rotation entre : un angle de pas positif par rapport à la direction d'écoulement de fluide local ou de poussée souhaitée ; un angle de pas négatif par rapport à la direction d'écoulement de fluide local ou de poussée souhaitée et un angle de pas transversal par rapport à la direction d'écoulement de fluide local ou de poussée souhaitée de façon à générer une portance positive, une portance négative ou une traînée selon les besoins tout au long du cycle de rotation.
PCT/GB2019/052698 2018-09-28 2019-09-25 Propulseur cycloïdal WO2020065304A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB201815895 2018-09-28
GB1815895.6 2018-09-28

Publications (1)

Publication Number Publication Date
WO2020065304A1 true WO2020065304A1 (fr) 2020-04-02

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PCT/GB2019/052698 WO2020065304A1 (fr) 2018-09-28 2019-09-25 Propulseur cycloïdal

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20220050476A1 (en) * 2020-08-11 2022-02-17 Pitch Aeronautics LLC Multirotor Vertical Takeoff And Landing Aircraft With Cyclorotor For Lateral Control

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080008587A1 (en) * 2006-07-10 2008-01-10 Siegel Aerodynamics, Inc. Cyclical wave energy converter
WO2008125806A2 (fr) * 2007-04-12 2008-10-23 Adrian Janssen Turbine à fluide
US20130076036A1 (en) * 2009-09-17 2013-03-28 Western Michigan University Research Foundation Method and device for power generation
US9346535B1 (en) * 2012-04-05 2016-05-24 The United States Of America As Represented By The Secretary Of The Air Force Ring cam and ring cam assembly for dynamically controlling pitch of cycloidal rotor blades
WO2017021844A1 (fr) * 2015-07-31 2017-02-09 Baroni Carlo Machine
DE202018100654U1 (de) * 2017-02-15 2018-05-17 Ladislav Pejša Schaufelpanetenantrieb

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080008587A1 (en) * 2006-07-10 2008-01-10 Siegel Aerodynamics, Inc. Cyclical wave energy converter
WO2008125806A2 (fr) * 2007-04-12 2008-10-23 Adrian Janssen Turbine à fluide
US20130076036A1 (en) * 2009-09-17 2013-03-28 Western Michigan University Research Foundation Method and device for power generation
US9346535B1 (en) * 2012-04-05 2016-05-24 The United States Of America As Represented By The Secretary Of The Air Force Ring cam and ring cam assembly for dynamically controlling pitch of cycloidal rotor blades
WO2017021844A1 (fr) * 2015-07-31 2017-02-09 Baroni Carlo Machine
DE202018100654U1 (de) * 2017-02-15 2018-05-17 Ladislav Pejša Schaufelpanetenantrieb

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20220050476A1 (en) * 2020-08-11 2022-02-17 Pitch Aeronautics LLC Multirotor Vertical Takeoff And Landing Aircraft With Cyclorotor For Lateral Control
US11614754B2 (en) * 2020-08-11 2023-03-28 Pitch Aeronautics LLC Multirotor vertical takeoff and landing aircraft with cyclorotor for lateral control

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