US20140161622A1 - Propeller - Google Patents

Propeller Download PDF

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Publication number
US20140161622A1
US20140161622A1 US13/843,344 US201313843344A US2014161622A1 US 20140161622 A1 US20140161622 A1 US 20140161622A1 US 201313843344 A US201313843344 A US 201313843344A US 2014161622 A1 US2014161622 A1 US 2014161622A1
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US
United States
Prior art keywords
blade
propeller
blades
intersection
section
Prior art date
Legal status (The legal status 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 status listed.)
Abandoned
Application number
US13/843,344
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English (en)
Inventor
Gregory Charles Sharrow
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Sharrow Engineering LLC
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to US13/843,344 priority Critical patent/US20140161622A1/en
Priority to PL13875362T priority patent/PL2941539T3/pl
Priority to ES18191741T priority patent/ES2900554T3/es
Priority to ES13875362T priority patent/ES2706413T3/es
Priority to JP2015547445A priority patent/JP6140296B2/ja
Priority to DK18191741.0T priority patent/DK3431387T3/da
Priority to DK13875362.9T priority patent/DK2941539T3/en
Priority to CN201910966949.XA priority patent/CN110667825B/zh
Priority to CN201380063211.3A priority patent/CN104854310B/zh
Priority to EP13875362.9A priority patent/EP2941539B1/en
Priority to PL18191741T priority patent/PL3431387T3/pl
Priority to PCT/US2013/073811 priority patent/WO2014130134A2/en
Priority to EP18191741.0A priority patent/EP3431387B1/en
Publication of US20140161622A1 publication Critical patent/US20140161622A1/en
Priority to JP2016134830A priority patent/JP6140340B2/ja
Assigned to SHARROW ENGINEERING LLC reassignment SHARROW ENGINEERING LLC ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SHARROW, Gregory Charles
Assigned to SHARROW ENGINEERING LLC reassignment SHARROW ENGINEERING LLC ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SHARROW, Gregory Charles
Priority to US15/489,562 priority patent/US20170218772A1/en
Priority to US15/605,764 priority patent/US9926058B2/en
Priority to US15/897,767 priority patent/US11273892B2/en
Priority to US15/956,303 priority patent/US11603184B2/en
Priority to US17/577,587 priority patent/US11649026B2/en
Abandoned legal-status Critical Current

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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
    • 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
    • B63H1/265—Blades each blade being constituted by a surface enclosing an empty space, e.g. forming a closed loop
    • 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
    • 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
    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49332—Propeller making

Definitions

  • This invention relates to blade apparatuses such as propellers.
  • propellers have been used in devices such as aircraft, watercraft, turbines, and other like apparatuses in a wide variety of configurations for transmitting power by converting rotational motion into thrust or fluid flow.
  • a propeller generally consists of two or more blades attached to a central post or hub with the blades curved, twisted, or otherwise shaped to generate a pressure difference between the forward and rear surfaces of a blade to propel a fluid, such as water or air, past the blades.
  • the shape, the pitch, and the twist of the blade all factor in the working efficiency of the propeller.
  • Embodiments of the invention provide a propeller that pulls air inward from the blade's side sections toward the propeller's axis of rotation and from the propeller's front to its back.
  • the propeller has a central post coincident with a rotational axis and one or more blades disposed around the central axis. Each blade has a distal end and a proximate end.
  • the blades include a top section, a bottom section, and a side section, with the side section disposed at or toward the distal end.
  • the top section and bottom section of the one or more blades are connected at their proximate ends to, and extend radially outward from, the central post.
  • the blade top portion intersects the central post at a blade top portion angle of intersection and the blade bottom portion intersects the central post at a blade bottom portion angle of intersection. As measured from a line perpendicular to the longitudinal axis of the propeller, the blade bottom portion angle of intersection is greater than the blade top portion angle of intersection.
  • the top blade portion can be non-symmetrical with the bottom blade portion.
  • the propeller blades can be in loop form, wherein each of the blades in loop form spins in the same plane of rotation. At least one of the blade sections can exhibit a non-zero blade angle.
  • the cross section of the blades can have an airfoil shape. Blades can be wider at their distal end as compared to their proximate end. Blades have a median line that can be straight or curved, independent of twists in the blade.
  • the propeller can have one or more pairs of blades opposing one another about the rotational axis.
  • the pair of opposing blades can form a single, contiguous loop.
  • the angles of intersection with respect to the rotational axis can be different between the opposing blades.
  • Propellers can be stacked on top of one another with or without spaces therebetween. Further, propellers can be comprised of a plurality of blades disposed in a helix about the central post.
  • the propeller blades can have a coarse pitch in the vicinity of the axis of rotation and decreasing pitch extending radially outward from the axis of rotation. Side sections of the blades exhibit a non-zero pitch.
  • the invention also includes devices having any of the disclosed propellers.
  • the invention further comprises a method of manufacturing a propeller comprising: selecting a desired direction of airflow, selecting a desired quantity of thrust, and selecting a blade curvature, combination of blades and blade intersection angles to create the selected airflow and thrust.
  • FIG. 1 is a side view of a schematic representative of a propeller according to an illustrative embodiment of the invention.
  • FIG. 2 is depicts a propeller with two opposing blades according to an illustrative embodiment of the invention.
  • FIG. 3A is a side view of a blade in loop form according to an illustrative embodiment of the invention.
  • FIGS. 3B and 3C are alternative cross-sectional views of the blade shown in FIG. 3A according to illustrative embodiments of the invention.
  • FIGS. 3D and 3E are alternative views of the blade shown in FIG. 3 according to an illustrative embodiment of the invention.
  • FIG. 4 is a cross-sectional view of a propeller with two opposing blades according to an illustrative embodiment of the invention.
  • FIG. 5 depicts a propeller with uprights attaching the upper and lower blade portions according to an illustrative embodiment of the invention.
  • FIG. 6A shows a three-loop propeller according to an illustrative embodiment of the invention.
  • FIG. 6B depicts a side view of a three-loop propeller according to an illustrative embodiment of the invention.
  • FIG. 7A depicts a four-loop propeller according to an illustrative embodiment of the invention.
  • FIG. 7B is a side view of a four-loop propeller according to an illustrative embodiment of the invention.
  • FIG. 8 shows a multiple-loop propeller according to an illustrative embodiment of the invention.
  • FIG. 9 is an isometric view of a two-loop propeller with unattached bottom blade sections.
  • FIG. 10 is an isometric view of a stacked propeller according to an illustrative embodiment of the invention.
  • FIG. 11 depicts a propeller according to an illustrative embodiment of the invention.
  • FIG. 12 depicts a stacked propeller according to an illustrative embodiment of the invention.
  • FIGS. 13A-B depict a top view and side view, respectively of a propeller with open-loop blades according to n illustrative embodiment of the invention.
  • the invention comprises a propeller having one or more “blades” wherein the blades are shaped to create an air flow inward from the propeller sides toward the axis of rotation, for example in a plane perpendicular to the axis of rotation, and also to create airflow in the longitudinal direction of the rotational axis, such as from “front” to “back” of the propeller.
  • the blades are shaped so that air is pulled inward by the blades' outer portions, or “supports”, and compressed in the vicinity of the propeller's center. Consequently, as the propeller spins, the blades create pressure in the central area, which, in turn, results in greater thrust. Conversely, when spinning in the opposite direction of rotation, the propeller will create reverse thrust. In illustrative embodiments of the invention, the amount of reverse thrust may not equal the amount of thrust generated.
  • blade is used herein merely to designate a component that rotates about an axis to generate a desired airflow, and is not intended to denote a specific shape, such as flat.
  • the blade includes three sections: top, bottom, and side.
  • a propeller can be disposed at various angles, an example of the use of the terms is shown in FIG. 1 , and it is noted that, for example, if a propeller 102 is rotating in a vertical plane “top” and “bottom” may not correlate with the traditional meaning of those terms.
  • Propeller 102 has two blades 104 , 106 .
  • Blade 106 has a top section, a bottom section 110 opposing top 108 , and a side 112 .
  • Side section 112 is at a distal end of blade 108 and connects top section 108 with bottom section 110 .
  • side portion 112 is a general area of the blade between the top section and the bottom section.
  • a blade's side section can be a discrete portion of the blade such as the side section 516 in FIG. 5 .
  • blade angle measured in degrees, when used herein is defined as the angle between a lateral cross section of a blade and the plane of rotation.
  • pitch is used herein interchangeably with “blade angle.”
  • Embodiments of the invention provide blades having at least one section exhibiting a non-zero blade angle.
  • front when used with respect to a propeller designates the side/face of the propeller, which when viewed will show counter clockwise motion of the propeller.
  • the propeller “back” will be the opposing side. As the propeller spins, the direction of airflow will preferably be from front to back.
  • the length from the central post to the distal end of the blade's leading edge 114 is greater than the length from the central post to the distal end of the blade's trailing edge 116 .
  • This decrease in blade length from the length at the blade's leading distal edge to the length at the blade's trailing distal edge can result in greater compression of air and greater thrust as compared to a comparable propeller design without this feature.
  • FIG. 2 is a front view of a propeller according to an illustrative embodiment of the invention.
  • This embodiment comprises two blades in loop form 202 , 204 , opposing one another.
  • a “loop” defines a blade with a continuous curved surface.
  • the propeller includes a central post 206 to which the blades are connected.
  • the central post is coincident with the propeller's axis of rotation.
  • post does not indicate a particular shape or configuration, but merely indicates a component to which blades are attached or by which they are secured to one another.
  • proximal portion 210 of each loop has a width that is less than the width of distal portions 212 .
  • FIG. 3A depicts a looped blade according to an illustrative embodiment of the invention.
  • FIG. 3A depicts blade 302 attached to a central post 306 of a propeller according to an illustrative embodiment of the invention.
  • the axis of rotation of blade 302 is coincident with the longitudinal axis of central post 306 in this embodiment.
  • Blade 302 has a top section 308 and a bottom section 310 .
  • the median line blade 302 is defined as the locus of points midway between the blade's leading edge 312 and its trailing edge 314 as shown by the broken line 316 running from the proximal end 318 to the distal end 320 of blade 302 .
  • the median line will not be continuous from top section through side section to bottom section.
  • the median line of blade 302 is curved providing a curved appearance to the blade sections.
  • blade sections may be cambered or otherwise curved, angular or flat, or a combination thereof.
  • FIG. 5 depicts an embodiment wherein blade sections have substantially linear, and possibly non-continuous median lines.
  • Air is compressed in the vicinity of central post 306 as the propeller spins.
  • a gap 342 between bottom portion 310 and top portion 312 of blade 302 allows a larger volume of air to be compressed than if a gap did not exist. Air is caught on the inside surface of blade 302 , thus pulling in air and creating the air flow from the sides as described above, while the outside surfaces of blade 302 function to push the air toward the back of the propeller.
  • FIGS. 3B and 3C depict cross sections of blade 302 taken along lines A-A and B-B of FIG. 3A , respectively.
  • Cross-section B-B shows an airfoil shape comparable to a cross section of an airplane wing.
  • surface 332 of blade 302 is curved, while the opposing surface 330 is substantially flat.
  • the cross section of blade 302 is tapered laterally so that at a first area 334 it is thinner than at a second, opposing area 336 , also comparable to an airplane wing.
  • Other blade configurations are within the scope of the invention and will depend in part on the desired load on the propeller.
  • blade 302 intersects central post 306 at a first blade intersection 338 and a second blade intersection 340 .
  • first and second blade intersections 338 , 340 intersect central post 306 , which can be at about the same angle ⁇ as measured counterclockwise from a line perpendicular to the longitudinal axis of central post 306 , wherein the designated reference line appears as a “horizontal” line in FIG. 3B .
  • An illustrative angle of intersection is about 25°, with an illustrative range being about 10° to about 35°.
  • a further illustrative range of angles of intersection is about 15° to about 25°.
  • angles of intersection can be in the range of about 1° to about 89°. By “extreme” it is meant more toward the vertical.
  • An illustrative difference between the angle of intersection of the top portion of the blade as compared to the angle of intersection of the bottom portion of the blade is about 10°.
  • An illustrative range is about 5° to about 20° and a further illustrative range is about 7° to about 15°.
  • the angle of intersection of the top portion of the blade is about 30° and the angle of intersection of the bottom portion of the blade is about 40°.
  • the angle of intersection of the top portion of the blade is about 75° and the angle of intersection of the bottom portion of the blade is about 85°.
  • Blade 302 as shown in FIGS. 3A-C exhibits a coarse blade angle, or pitch, near the axis of rotation with the pitch decreasing radially outward from the axis of rotation. Despite this downward gradient, the outermost point of the blade will still exhibit non-zero pitch.
  • the blade may have a more course blade angle at the farthest point from the axis of rotation.
  • FIGS. 3D and 3E depict blade 302 as viewed so central post 306 is perpendicular to the page.
  • blade 302 would be rotating clockwise and has a leading edge 346 and a trailing edge 344 .
  • blade 302 would be rotating counterclockwise.
  • the pitches of opposing blade intersections on either side of the axis of rotation differ from each other. So for example, in FIG. 4 you have a first blade 402 having a first blade intersection 404 at angle ⁇ A and a second blade intersection 406 at an angle ⁇ B , and an opposing blade would have a first blade intersection angle and a second blade intersection angle of ⁇ A ⁇ x and ⁇ B ⁇ x, respectively. So in other words, the pitch of opposing blade intersections differs.
  • An illustrative difference in pitch between opposing blade intersections is about 50°, wherein for example one blade intersection has a 25° pitch and the opposing blade has an intersection with a negative 25° pitch. Differences can be equally or unequally distributed. A general range of differences between the pitch of opposing blades is about 40° to about 60°. The pitch of opposing blade intersections need not be equal from the plane of rotation as in the preceding example.
  • FIG. 5 depicts an illustrative embodiment that includes two blades 502 , 504 with substantially non-curved median lines.
  • Median line 506 of top blade section 508 and median line 510 of bottom blade section 512 of blade 502 are substantially linear and may or may not be parallel.
  • Blade 504 also has a substantially linear median line.
  • One or more substantially vertical wing segments 514 , 516 connect top blade section 508 and bottom blade section 510 at intervals radiating from a central post 518 up to but not necessarily including the distal end 520 of blade 502 .
  • Blade 504 may have similar or the same vertical segments.
  • the blades are flattened to an extent and would not necessarily be considered a “loop” with a continuous surface, the desired airflow may nonetheless be created with the addition of the wing segments, 514 , 516 , or both. As the propeller spins, wing segments 514 , 516 pull air in from the sides toward central post 518 , thus creating the desired airflow.
  • top blade section 1102 and bottom blade section 1104 are not symmetrical. This can be accomplished, for example, by bottom section 1104 being longer than the top section 1102 , with a side section 1106 angled toward the front of the propeller to connect to the shorter top section 1102 . This can facilitate the airflow being pulled in from the side section to propel the blade forward. In general, a more extreme angle between the side section and the top section of the blade will result in more thrust and a higher forward rake for the top section of the blade.
  • FIGS. 6A and 6B show a propeller with three loop-shaped blades 602 , 604 , 606 , according to an illustrative embodiment of the invention.
  • FIG. 6A is a view of the propeller rotating so that counterclockwise rotation would cause airflow into the page
  • FIG. 6B is a side view of the propeller.
  • Blades 602 , 604 , 606 radiate from central post 608 .
  • Blades 602 , 604 , 606 are generally coplanar. Any number of loops can be combined to obtain the desired air flow. See for example FIGS. 7A , 7 B with four blades and FIG. 8 with eight blades.
  • Propellers can be “stacked” so they rotate in different planes. By “stacked” it is not meant that they necessarily abut one another.
  • the stacked propellers can have gaps between them. They can be of uniform size or graduated from smaller to larger in a direction perpendicular to the plane of rotation from back to front, or larger to smaller in that direction.
  • FIG. 10 shows an eight-loop propeller 1002 having a first plane of rotation stacked onto another eight-loop propeller 1004 having a second plane of rotation.
  • the blades of propeller 1002 are attached to central post 1006
  • the blades of propeller 1004 are attached to central post 1008 .
  • FIG. 10 illustrates two discrete central posts 1006 and 1008 , propellers may also be stacked on a single central post.
  • FIG. 12 depicts a further embodiment of a stacked propeller. Blades are disposed about a central post in a helix fashion.
  • FIGS. 7A and 7B depict a propeller having four blades 702 , 704 , 706 , 708 , according to an illustrative embodiment of the invention.
  • Blades 702 , 704 , 706 , 708 radiate from a central post 710 wherein of blades 702 , 704 , 706 , 708 would generally spin in the same plane as the others.
  • FIG. 7A in this illustrative embodiment, there is a “gap” 712 between the attachment locations of a top portion of each blade and a bottom portion of each blade along central post 710 , with which the axis of rotation is coincident.
  • gap is used herein to describe the space around the axis of rotation between the center of the blade intersections with a central post created when a blade's top and bottom portion are attached at different longitudinal locations along a central post or axis of rotation.
  • FIG. 3B depicts the location of the gap as shown by line 340 .
  • the blade bottom portion may not be attached to the central post, such as shown in FIGS. 9 and 13 A-B, in which case the gap is the distance between the center of the top blade portion intersection with the central post and the center of where the bottom blade portion would intersect the central post if it was extended to reach it.
  • Propellers can be designed with various gap sizes.
  • An illustrative gap size range is approximately about 2% to 55% of the length of a propeller's.
  • Another illustrative gap size range is about 20% of a propeller's blade length to about 35% of a propeller's blade.
  • a third illustrative gap size range is about 30% of a propeller's blade length to about 55% of a propeller's blade length.
  • blades may be twisted, such as about the median line for example.
  • a twist can be seen for example in FIG. 5 .
  • Both top portion 508 and bottom portion 512 of blade 502 have an apparent twist.
  • Curved blades can also be additionally twisted, such as can been seen in FIGS. 7A-B , or as would result from a difference in blade intersection angles ⁇ as shown in FIG. 4 .
  • the propeller has a twist forming the curvature of the blades or relative curvature of opposing blades that is approximately 35 degrees.
  • An illustrative range of twist is in the range of about 30 degrees to about 40 degrees. Other degrees of twisting are within the scope of the invention and can create various degrees and directions of airflow.
  • FIG. 8 depicts an illustrative embodiment of the invention with eight “blades” 802 , 804 , 806 , 808 , 810 , 812 , 814 , 816 made of four circles that are all slightly angled but have no half turn.
  • At least the front edges of the loops are thin to cut through the air, but other edge shapes may be beneficial to achieve a desired air flow pattern.
  • the specific shape, quantity and arrangement of the loops can be chosen to create a desired air flow pattern.
  • FIG. 9 depicts a propeller having blades 902 , 904 in loop form opposing one another wherein the bottom blade sections 906 , 908 of blades 902 , 904 are not attached to central post 910 . Instead, “brace” 912 flexibly couples bottom blade section bottom 906 to top blade section 914 . Similarly, brace 916 flexibly couples bottom blade section 908 to top blade section 918 .
  • a “brace” as used herein is a blade component used to flexibly couple disparate blade sections.
  • a brace can be made of steel, aluminum, composite materials such as carbon and fiber glass, or any other suitable blade material.
  • Braces 912 , 916 are angled with respect to the plane of rotation to pull air in toward the axis of rotation as the propeller rotates, thus creating drag.
  • a brace may be angled in the same way as a blade's side section to achieve the desired air flow. Further, the thickness, length, width, and other such characteristics of a brace are designed to achieve desired operation of a particular blade application, such as by way of an example, flight.
  • Blades 902 , 904 are disposed with respect to central post 910 in this manner to provide the flexibility of adjusting their pitches.
  • the braces allow for the blades 902 , 904 to be manipulated to change pitch during activities such as take-off, flight, or landing.
  • the propeller can include an adjustment mechanism to allow selectable variations in the gap formed between top blade sections 914 , 918 and bottom blade sections 906 , 908 , respectively.
  • FIGS. 13A-B depict a top view and side view, respectively of a further embodiment of a propeller with open-loop blades according to an illustrative embodiment of the invention. This version does not include the braces as provided in FIG. 9 .
  • the invention includes various devices having various embodiments of the disclosed propeller employed therein.
  • the invention includes the following illustrative devices: aircraft, watercraft, wind turbines, cooling devices, heating devices, automobile engines, and air circulation devices.
  • the invention also includes a method of manufacturing a propeller according to any of the embodiments described, pictured or claimed herein; a method of manufacturing a device comprising any of the aforementioned propellers; a method of manufacturing a product wherein the method includes installing a device containing any of the aforementioned propellers.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Ocean & Marine Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Wind Motors (AREA)
US13/843,344 2012-12-10 2013-03-15 Propeller Abandoned US20140161622A1 (en)

Priority Applications (19)

Application Number Priority Date Filing Date Title
US13/843,344 US20140161622A1 (en) 2012-12-10 2013-03-15 Propeller
EP13875362.9A EP2941539B1 (en) 2012-12-10 2013-12-09 Propeller
EP18191741.0A EP3431387B1 (en) 2012-12-10 2013-12-09 Propeller
ES18191741T ES2900554T3 (es) 2012-12-10 2013-12-09 Hélice
JP2015547445A JP6140296B2 (ja) 2012-12-10 2013-12-09 プロペラ
DK18191741.0T DK3431387T3 (da) 2012-12-10 2013-12-09 Propel
DK13875362.9T DK2941539T3 (en) 2012-12-10 2013-12-09 Propeller
CN201910966949.XA CN110667825B (zh) 2012-12-10 2013-12-09 螺旋桨
CN201380063211.3A CN104854310B (zh) 2012-12-10 2013-12-09 螺旋桨
PCT/US2013/073811 WO2014130134A2 (en) 2012-12-10 2013-12-09 Propeller
PL18191741T PL3431387T3 (pl) 2012-12-10 2013-12-09 Śmigło
PL13875362T PL2941539T3 (pl) 2012-12-10 2013-12-09 Śruba
ES13875362T ES2706413T3 (es) 2012-12-10 2013-12-09 Hélice
JP2016134830A JP6140340B2 (ja) 2012-12-10 2016-07-07 プロペラ
US15/489,562 US20170218772A1 (en) 2012-12-10 2017-04-17 Propeller
US15/605,764 US9926058B2 (en) 2012-12-10 2017-05-25 Propeller
US15/897,767 US11273892B2 (en) 2012-12-10 2018-02-15 Propeller
US15/956,303 US11603184B2 (en) 2012-12-10 2018-04-18 Propeller
US17/577,587 US11649026B2 (en) 2012-12-10 2022-01-18 Propeller

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201261735140P 2012-12-10 2012-12-10
US13/843,344 US20140161622A1 (en) 2012-12-10 2013-03-15 Propeller

Related Child Applications (3)

Application Number Title Priority Date Filing Date
US15/489,562 Continuation US20170218772A1 (en) 2012-12-10 2017-04-17 Propeller
US15/605,764 Continuation-In-Part US9926058B2 (en) 2012-12-10 2017-05-25 Propeller
US15/956,303 Continuation US11603184B2 (en) 2012-12-10 2018-04-18 Propeller

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US20140161622A1 true US20140161622A1 (en) 2014-06-12

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WO2017106617A1 (en) * 2015-12-17 2017-06-22 Amazon Technologies, Inc. Redundant aircraft propulsion system using multiple motors per drive shaft
US20170174323A1 (en) * 2015-12-17 2017-06-22 Amazon Technologies, Inc. Redundant Aircraft Propulsion System Using Co-rotating Propellers Joined By Tip Connectors
WO2017205680A1 (en) * 2016-05-27 2017-11-30 Sharrow Engineering Llc Propeller
US9926058B2 (en) 2012-12-10 2018-03-27 Sharrow Engineering Llc Propeller
US10836466B2 (en) 2017-11-06 2020-11-17 Massachusetts Institute Of Technology Toroidal propeller
CN112746933A (zh) * 2021-01-16 2021-05-04 李颖 风力发电用风机机身快速连接装置及其使用方法
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
CN114245786A (zh) * 2019-09-23 2022-03-25 沃尔沃遍达公司 用于船舶的螺旋桨
US11603184B2 (en) 2012-12-10 2023-03-14 Sharrow Engineering Llc Propeller
WO2023163278A1 (ko) * 2021-10-27 2023-08-31 박규리 발전용 선박
US11840999B2 (en) * 2018-06-06 2023-12-12 Marten Bondestam Rotor
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US20110274558A1 (en) * 2010-05-10 2011-11-10 Kathryn Chase Modular windmill
US11603184B2 (en) 2012-12-10 2023-03-14 Sharrow Engineering Llc Propeller
US11273892B2 (en) * 2012-12-10 2022-03-15 Sharrow Engineering Llc Propeller
US9926058B2 (en) 2012-12-10 2018-03-27 Sharrow Engineering Llc Propeller
US20180186439A1 (en) * 2012-12-10 2018-07-05 Sharrow Engineering Llc Propeller
WO2017106617A1 (en) * 2015-12-17 2017-06-22 Amazon Technologies, Inc. Redundant aircraft propulsion system using multiple motors per drive shaft
US20170174323A1 (en) * 2015-12-17 2017-06-22 Amazon Technologies, Inc. Redundant Aircraft Propulsion System Using Co-rotating Propellers Joined By Tip Connectors
CN108367804A (zh) * 2015-12-17 2018-08-03 亚马逊技术股份有限公司 每个驱动轴使用多个马达的冗余飞行器推进系统
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JP2019500277A (ja) * 2015-12-17 2019-01-10 アマゾン テクノロジーズ インコーポレイテッド ドライブシャフトにつき複数のモーターを使用する冗長航空機推進システム
CN108367804B (zh) * 2015-12-17 2021-06-04 亚马逊技术股份有限公司 每个驱动轴使用多个马达的冗余飞行器推进系统
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AU2017268808C1 (en) * 2016-05-27 2020-02-13 Sharrow Engineering Llc Propeller
AU2019203301B2 (en) * 2016-05-27 2021-03-04 Sharrow Engineering Llc Propeller
KR102070835B1 (ko) 2016-05-27 2020-01-29 섀로우 엔지니어링 엘엘씨 프로펠러
KR20200010605A (ko) * 2016-05-27 2020-01-30 섀로우 엔지니어링 엘엘씨 프로펠러
TWI660884B (zh) * 2016-05-27 2019-06-01 美商雪洛工程有限責任公司 螺旋槳及具有該螺旋槳之裝置
KR102143022B1 (ko) 2016-05-27 2020-08-11 섀로우 엔지니어링 엘엘씨 프로펠러
KR20200096688A (ko) * 2016-05-27 2020-08-12 섀로우 엔지니어링 엘엘씨 프로펠러
TWI703072B (zh) * 2016-05-27 2020-09-01 美商雪洛工程有限責任公司 螺旋槳及製造具有葉片之螺旋槳之方法
WO2017205680A1 (en) * 2016-05-27 2017-11-30 Sharrow Engineering Llc Propeller
KR102202445B1 (ko) 2016-05-27 2021-01-13 섀로우 엔지니어링 엘엘씨 프로펠러
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TWI738453B (zh) * 2016-05-27 2021-09-01 美商雪洛工程有限責任公司 螺旋槳
AU2017268808B2 (en) * 2016-05-27 2019-02-14 Sharrow Engineering Llc Propeller
CN106142681A (zh) * 2016-09-29 2016-11-23 河北大艾智能科技股份有限公司 空心螺旋桨及其制造方法
US10836466B2 (en) 2017-11-06 2020-11-17 Massachusetts Institute Of Technology Toroidal propeller
US11840999B2 (en) * 2018-06-06 2023-12-12 Marten Bondestam Rotor
CN114245786A (zh) * 2019-09-23 2022-03-25 沃尔沃遍达公司 用于船舶的螺旋桨
US12030604B2 (en) 2019-09-23 2024-07-09 Volvo Penta Corporation Propeller for a marine vessel
CN112746933A (zh) * 2021-01-16 2021-05-04 李颖 风力发电用风机机身快速连接装置及其使用方法
USD1029041S1 (en) * 2021-04-21 2024-05-28 Sharrow Engineering Llc Duo-propeller
WO2023163278A1 (ko) * 2021-10-27 2023-08-31 박규리 발전용 선박
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

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EP2941539A2 (en) 2015-11-11
WO2014130134A3 (en) 2015-03-26
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US20170218772A1 (en) 2017-08-03
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US11603184B2 (en) 2023-03-14
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CN104854310B (zh) 2019-09-13

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