US20080219848A1 - Propeller - Google Patents

Propeller Download PDF

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Publication number
US20080219848A1
US20080219848A1 US10/586,571 US58657105A US2008219848A1 US 20080219848 A1 US20080219848 A1 US 20080219848A1 US 58657105 A US58657105 A US 58657105A US 2008219848 A1 US2008219848 A1 US 2008219848A1
Authority
US
United States
Prior art keywords
blade
blades
propeller
hubs
fixed
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
US10/586,571
Other languages
English (en)
Inventor
Andrey Akaro
Anatoly Mikhailovich Zelinsky
Mikhail Mikhallovich Medvedev
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.)
NSK Ltd
Original Assignee
NSK Ltd
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 NSK Ltd filed Critical NSK Ltd
Publication of US20080219848A1 publication Critical patent/US20080219848A1/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
    • B64C11/001—Shrouded propellers
    • 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
    • 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
    • B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
    • B64C11/48—Units of two or more coaxial propellers

Definitions

  • the invention relates to propeller, which can be used in the area of aviation and special transportation (propeller-sleighs sled, air-support vessels).
  • a propeller which has a shaft with two hubs installed on it, with blades which are fixed on each of the hubs uniformly over a circumference.
  • the blades on the two hubs are driven in rotation in opposite directions by means of an motor (U.S. Pat. No. 2,953,320 IPC: 244-12, 1960).
  • a propeller which has a shaft with two hubs installed on it, with blades fixed on each of the hubs uniformly over a circumference.
  • the blades of the two hubs are driven in rotation in opposite directions by means of a motor (RU patent no. 2,062,246, IPC:B 64 C29/00, 1996).
  • a task which is solved in this invention is to create a propeller which provides a reduction of aerodynamic loads acting on it.
  • each blade has sharp front and rear edges, and is formed along an extension of a blade with a maximum thickness of profiles (0.10-0.25)b, where b is a length of a local chord of the blade and twisted relative to an axis extending through a middle of the local chords along the extension of the blade, wherein the maximum thickness of the profile is located in a middle of each local chord.
  • the arrangement of at least two hubs with blades fixed on each of them uniformly over a circumference leads to a reduction of sizes of the hubs with the blades, which leads to a reduction of aerodynamic loads acting on the propeller.
  • each blade together provide a reduction of aerodynamic resistance of the blades and as a result a reduction of aerodynamic loads acting on the propeller.
  • the maximum thickness of the profile of each blade, located in the middle of each local chord, provides a uniform distribution of aerodynamic loads along the length of the chord (width of the blade), which reduces aerodynamic loads acting on the propeller.
  • Fixing of the blades on each of the hubs inclinedly in a direction opposite to the rotation leads to the fact that an angle between an axis of the blade and a local speed of movement of the blade along a height becomes different from a direct angle, which leads to a reduction of a local aerodynamic resistance of the blade and, therefore, reduces aerodynamic loads acting on the propeller.
  • Provision of the propeller with an immovable cylindrical casing surrounding all blades and moved out forwardly of the blades of the front hub not less than by a length of the blade allows to increase a value of a torque.
  • the propeller throws air in a direction of rotation and forwardly against movement of the propeller.
  • the thrown off air is reflected by the casing so that the running-on flow becomes twisted in a direction of their rotation, which increases a torque and thereby efficiency of the propeller. Due to the reflection of this air the maximum twist of the running-on flow is obtained with a cylindrical casing.
  • a length of the casing is determined by a distance, over which a speed of the reflected air is close to zero. With optimal parameters of the blades and a speed of rotation of the propeller it becomes close to a radius of the propeller and therefore to a length of the blade.
  • FIG. 1 shows a general view of a propeller
  • FIG. 2 is a general view of the propeller with a casing
  • FIG. 3 is a side view of the propeller with the casing
  • FIG. 4 is a transverse cross-section of the blade
  • FIG. 5 is a view of a twisted blade from an end
  • FIG. 6 is a view of the propeller from the front with fixed blades inclined.
  • a propeller has a shaft 1 with at least two hubs 2 arranged on it with blades 3 fixed on each of the hubs uniformly over a circumference.
  • a number of the hubs with the blades 3 can be different.
  • the blades 3 on each subsequent hub 2 can be fixed both with a possibility of rotation in opposite direction, and with a possibility of rotation in one direction.
  • the rotation can be performed from a motor by means of a drive shaft and gear trains.
  • Each blade 3 has a sharp front edge 4 and a sharp rear edge 5 , and is configured along an extension of the blade 3 with a maximum thickness of profiles (0.10-0.25)b, wherein b is a length of a local chord of the blade 3 .
  • each blade 3 the maximum thickness 6 of the profile is located in a middle of each local chord.
  • the profiles can have different shapes, for example double-convex, wedge-like, rhombus-like.
  • the blades can be composed of profiles of different shapes.
  • Each blade 3 is twisted relative to an axis 8 , extending through a middle of the local chord along the extension of the blade 3 .
  • the blades can be fixed on each of the hubs 2 inclinedly in a direction opposite to the rotation of the propeller, as shown by arrow on FIG. 6 .
  • the propeller can be provided with an immovable cylindrical casing 9 which surrounds all blades 3 and is moved out in front of the blades 3 of the front hub 2 not less than by length of the blade L.
  • the hubs 2 with the blades 3 are driven in rotation by the shaft 1 of a motor, to generate aerodynamic forces and movements, which drive a vehicle into movement.
  • Sharp front and rear edges 4 and 5 of each blade 3 together provide a reduction of aerodynamic resistance of the blades 3 and as a result a reduction of aerodynamic loads acting on the propeller.
  • the maximum thickness 6 of the profile of each blade 3 located in a middle of each local chord 7 provides a uniform distribution of aerodynamic loads along the length of the chord 7 (width of the blade 3 ), which reduces aerodynamic loads acting on the propeller.
  • Twisting of each blade 3 relative to the axis 8 extending through the middle of its chord 7 along the extension of the blade 3 , provides a reduction of a dispersion of aerodynamic loads along the length of the blade 3 , which reduces aerodynamic loads acting on the propeller.
  • Fixing of the blades 3 on each of the hubs 2 inclinedly in a direction opposite to the rotation leads to the fact that the angle between the axis of the blade 3 and the local speed of movement of the blade 3 along the height becomes different from a direct angle, which leads to a reduction of local aerodynamic resistance of the blade 3 and, therefore, reduces the aerodynamic load on the propeller.
  • Provision of the propeller with the immovable cylindrical casing 10 surrounding all blades 3 and moved out in front of the blades 3 of the front hub 2 not less than by the length L of the blade 3 allows to increase a value of torque during the rotation of the propeller.
  • the present invention can be used most successfully in the area of aviation and a special transportation (air sled, air foil vessels).

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Nitrogen And Oxygen Or Sulfur-Condensed Heterocyclic Ring Systems (AREA)
US10/586,571 2004-01-20 2005-01-11 Propeller Abandoned US20080219848A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
RU2004101034 2004-01-20
RU2004101034/11A RU2256585C1 (ru) 2004-01-20 2004-01-20 Воздушный винт
PCT/RU2005/000004 WO2005068292A1 (en) 2004-01-20 2005-01-11 Propeller

Publications (1)

Publication Number Publication Date
US20080219848A1 true US20080219848A1 (en) 2008-09-11

Family

ID=34793510

Family Applications (1)

Application Number Title Priority Date Filing Date
US10/586,571 Abandoned US20080219848A1 (en) 2004-01-20 2005-01-11 Propeller

Country Status (9)

Country Link
US (1) US20080219848A1 (ja)
EP (1) EP1707485A4 (ja)
JP (1) JP2007518620A (ja)
KR (1) KR100806016B1 (ja)
CN (1) CN100436254C (ja)
EA (1) EA007477B1 (ja)
RU (1) RU2256585C1 (ja)
UA (1) UA80216C2 (ja)
WO (1) WO2005068292A1 (ja)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9527578B2 (en) 2010-08-06 2016-12-27 Ge Aviation Systems Limited Propellers for aircraft

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2014123151A (ru) * 2014-06-09 2016-01-10 Андрей Геннадьевич Винников Ветросиловой и/или гидросиловой привод
RU171041U1 (ru) * 2016-11-29 2017-05-17 Российская Федерация от имени которой выступает Министерство промышленности и торговли РФ Движительная установка амфибийного судна на воздушной подушке
RU182553U1 (ru) * 2018-05-10 2018-08-22 Андрей Геннадьевич Винников Ветросиловой привод

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5551841A (en) * 1994-06-27 1996-09-03 Marsushita Electric Works, Ltd. Axial-flow fan
US6168384B1 (en) * 1997-12-12 2001-01-02 Arthur Vanmoor Propeller blade configuration
US6379113B1 (en) * 1999-11-16 2002-04-30 Chang Sun Kim Propeller apparatus
US6533536B1 (en) * 1996-03-28 2003-03-18 Voith Hydro, Inc. Hydro-turbine runner
US6749401B2 (en) * 2002-07-22 2004-06-15 Arthur Vanmoor Hydrodynamically and aerodynamically optimized leading edge structure for propellers, wings, and airfoils
US6974309B2 (en) * 2001-11-08 2005-12-13 Tokai University Educational System Straight wing type wind and water turbine

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3127093A (en) * 1964-03-31 Ducted sustaining rotor for aircraft
US2953320A (en) * 1955-07-18 1960-09-20 Charles B Bolton Aircraft with ducted lifting fan
GB827916A (en) * 1957-11-01 1960-02-10 United Aircraft Corp Aircraft propeller
FR1315717A (fr) * 1960-12-19 1963-01-25 Lyonnaise Ventilation Ventilateur hélicoïde perfectionné
EP0103478A1 (en) * 1982-09-13 1984-03-21 Ian James Gilchrist Airfoil
US4796836A (en) * 1985-02-28 1989-01-10 Dieter Schatzmayr Lifting engine for VTOL aircrafts
FR2590229B1 (fr) * 1985-11-19 1988-01-29 Onera (Off Nat Aerospatiale) Perfectionnements apportes aux helices aeriennes en ce qui concerne le profil de leurs pales
GB2220712B (en) * 1988-07-13 1992-12-09 Rolls Royce Plc Open rotor blading
US5096383A (en) * 1989-11-02 1992-03-17 Deutsche Forschungsanstalt Fur Luft- Und Raumfahrt E.V. Propeller blades
US5152478A (en) 1990-05-18 1992-10-06 United Technologies Corporation Unmanned flight vehicle including counter rotating rotors positioned within a toroidal shroud and operable to provide all required vehicle flight controls
RU2015062C1 (ru) * 1991-09-30 1994-06-30 Владимир Ильич Петинов Лопасть воздушного винта
GB9412414D0 (en) * 1994-06-21 1994-08-10 Secr Defence Rotary winged aircraft

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5551841A (en) * 1994-06-27 1996-09-03 Marsushita Electric Works, Ltd. Axial-flow fan
US6533536B1 (en) * 1996-03-28 2003-03-18 Voith Hydro, Inc. Hydro-turbine runner
US6168384B1 (en) * 1997-12-12 2001-01-02 Arthur Vanmoor Propeller blade configuration
US6379113B1 (en) * 1999-11-16 2002-04-30 Chang Sun Kim Propeller apparatus
US6974309B2 (en) * 2001-11-08 2005-12-13 Tokai University Educational System Straight wing type wind and water turbine
US6749401B2 (en) * 2002-07-22 2004-06-15 Arthur Vanmoor Hydrodynamically and aerodynamically optimized leading edge structure for propellers, wings, and airfoils

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9527578B2 (en) 2010-08-06 2016-12-27 Ge Aviation Systems Limited Propellers for aircraft

Also Published As

Publication number Publication date
EP1707485A1 (en) 2006-10-04
CN100436254C (zh) 2008-11-26
RU2256585C1 (ru) 2005-07-20
KR100806016B1 (ko) 2008-02-26
RU2004101034A (ru) 2005-06-20
EA200600370A1 (ru) 2006-06-30
EP1707485A4 (en) 2007-10-03
KR20060103938A (ko) 2006-10-04
JP2007518620A (ja) 2007-07-12
EA007477B1 (ru) 2006-10-27
WO2005068292A1 (en) 2005-07-28
CN1910081A (zh) 2007-02-07
UA80216C2 (en) 2007-08-27

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