US20080219848A1 - Propeller - Google Patents
Propeller Download PDFInfo
- 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
Links
Images
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)
- Nitrogen And Oxygen Or Sulfur-Condensed Heterocyclic Ring Systems (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
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 (ko) |
EP (1) | EP1707485A4 (ko) |
JP (1) | JP2007518620A (ko) |
KR (1) | KR100806016B1 (ko) |
CN (1) | CN100436254C (ko) |
EA (1) | EA007477B1 (ko) |
RU (1) | RU2256585C1 (ko) |
UA (1) | UA80216C2 (ko) |
WO (1) | WO2005068292A1 (ko) |
Cited By (1)
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)
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)
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)
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 |
-
2004
- 2004-01-20 RU RU2004101034/11A patent/RU2256585C1/ru not_active IP Right Cessation
-
2005
- 2005-01-11 JP JP2006549178A patent/JP2007518620A/ja active Pending
- 2005-01-11 US US10/586,571 patent/US20080219848A1/en not_active Abandoned
- 2005-01-11 EA EA200600370A patent/EA007477B1/ru not_active IP Right Cessation
- 2005-01-11 EP EP05710991A patent/EP1707485A4/en not_active Ceased
- 2005-01-11 KR KR1020067012778A patent/KR100806016B1/ko not_active IP Right Cessation
- 2005-01-11 CN CNB2005800027395A patent/CN100436254C/zh not_active Expired - Fee Related
- 2005-01-11 WO PCT/RU2005/000004 patent/WO2005068292A1/ru not_active Application Discontinuation
- 2005-11-01 UA UAA200603747A patent/UA80216C2/uk unknown
Patent Citations (6)
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)
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 |
---|---|
UA80216C2 (en) | 2007-08-27 |
KR100806016B1 (ko) | 2008-02-26 |
KR20060103938A (ko) | 2006-10-04 |
WO2005068292A1 (en) | 2005-07-28 |
EA007477B1 (ru) | 2006-10-27 |
EP1707485A4 (en) | 2007-10-03 |
EA200600370A1 (ru) | 2006-06-30 |
RU2256585C1 (ru) | 2005-07-20 |
JP2007518620A (ja) | 2007-07-12 |
RU2004101034A (ru) | 2005-06-20 |
CN100436254C (zh) | 2008-11-26 |
CN1910081A (zh) | 2007-02-07 |
EP1707485A1 (en) | 2006-10-04 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |