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
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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)
- Nitrogen And Oxygen Or Sulfur-Condensed Heterocyclic Ring Systems (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The inventive propeller consists of a shaft comprising at least two hubs which are mounted thereon and provided with blades fixed to each of them. Each blade has a front and rear sharp edges and is embodied in such a way that the greater airfoil thickness thereof is equal to (0.10-0.25)b along the blade span, wherein b is the mean chord of the blade. The greatest airflow thickness of each blade is located in the middle of each mean chord and is twisted around an axis passing through the middles of the mean chords along the blade span. The blade can be fixed to each hub at an angle of <90° with respect to the radius thereof, thereby reducing a local aerodynamic drag and aerodynamic loads. The inventive propeller can be provided with a fixed cylindrical enclosure which embraces all blades and extended in front of the blades of the front hub at a distance which is equal to or greater than the blade span, thereby increasing a torque effect value.
Description
- 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 is known, 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 is known, 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).
- The disadvantage of both known propellers is that each design of the propeller generates high aerodynamic loads which act on it, that leads to a necessity to provide its high strength and stiffness.
- A task which is solved in this invention is to create a propeller which provides a reduction of aerodynamic loads acting on it.
- This task during the creation of propeller is achieved in that, in the propeller which has a shaft with at least two hubs installed on it with blades fixed on each of the hubs uniformly over a circumference, 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.
- The sharp front and rear edges of 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 configuration along an extension of each blade with the maximum thickness of the profiles (0.10-0.25)b, wherein b is a length of local chord of the blade, provides within a selected range of the maximum thickness of the profiles, 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.
- Twisting of each blade relative to an axis, extending through the middle of the local chords along the extension of the blade, provides a reduction of dispersion of aerodynamic loads along the length 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. During the rotation 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 twohubs 2 arranged on it withblades 3 fixed on each of the hubs uniformly over a circumference. A number of the hubs with theblades 3 can be different. Theblades 3 on eachsubsequent 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 asharp front edge 4 and a sharprear edge 5, and is configured along an extension of theblade 3 with a maximum thickness of profiles (0.10-0.25)b, wherein b is a length of a local chord of theblade 3. - In each
blade 3 themaximum 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. Along the extension the blades can be composed of profiles of different shapes.
- Each
blade 3 is twisted relative to anaxis 8, extending through a middle of the local chord along the extension of theblade 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 onFIG. 6 . - The propeller can be provided with an immovable
cylindrical casing 9 which surrounds allblades 3 and is moved out in front of theblades 3 of thefront hub 2 not less than by length of the blade L. Thehubs 2 with theblades 3 are driven in rotation by theshaft 1 of a motor, to generate aerodynamic forces and movements, which drive a vehicle into movement. - The provision of at least two
hubs 2 with theblades 3 fixed on each of them uniformly over a circumference leads to a reduction of the sizes of thehubs 2 with theblades 3 which leads to a reduction of aerodynamic loads on the propeller. - Sharp front and
rear edges blade 3 together provide a reduction of aerodynamic resistance of theblades 3 and as a result a reduction of aerodynamic loads acting on the propeller. - The configuration along the extension of each
blade 3 with the maximum thickness of the profiles (0.10-0.25)b, wherein b is a length of a local chord of theblade 3, provides within a selected range of the maximum thickness of the profiles a reduction of aerodynamic resistance of theblades 3 and as a result a reduction of aerodynamic loads acting on the propeller. - The
maximum thickness 6 of the profile of eachblade 3 located in a middle of eachlocal 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 theaxis 8, extending through the middle of itschord 7 along the extension of theblade 3, provides a reduction of a dispersion of aerodynamic loads along the length of theblade 3, which reduces aerodynamic loads acting on the propeller. - Fixing of the
blades 3 on each of thehubs 2 inclinedly in a direction opposite to the rotation leads to the fact that the angle between the axis of theblade 3 and the local speed of movement of theblade 3 along the height becomes different from a direct angle, which leads to a reduction of local aerodynamic resistance of theblade 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 theblades 3 of thefront hub 2 not less than by the length L of theblade 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).
Claims (4)
1-3. (canceled)
4. A propeller, comprising a shaft; at least two hubs arranged on said shaft; blades fixed on each of said hubs uniformly over a circumference, each of said blades having sharp front and rear edges and configured along an extension of a corresponding one of said blades with a maximum thickness of profiles (0.10-0.25)b wherein b is a length of a local chord of said blade, and being twisted relative to an axis extending through a middle of said local chords along said extension of said blade, wherein said maximum thickness of said profile is located in the middle of each of said local chords.
5. A propeller as defined in claim 4 , wherein said blades are fixed on each of said hubs inclinedly in a direction opposite to a direction of rotation.
6. A propeller as defined in claim 4 ; and further comprising an immovable cylindrical casing which surrounds all said blades and is moved out in front of said blades of a front hub not less than by length of said blade.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2004101034 | 2004-01-20 | ||
RU2004101034/11A RU2256585C1 (en) | 2004-01-20 | 2004-01-20 | Propeller |
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 (en) |
EP (1) | EP1707485A4 (en) |
JP (1) | JP2007518620A (en) |
KR (1) | KR100806016B1 (en) |
CN (1) | CN100436254C (en) |
EA (1) | EA007477B1 (en) |
RU (1) | RU2256585C1 (en) |
UA (1) | UA80216C2 (en) |
WO (1) | WO2005068292A1 (en) |
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 (en) * | 2014-06-09 | 2016-01-10 | Андрей Геннадьевич Винников | WIND POWER AND / OR HYDRAULIC DRIVE |
RU171041U1 (en) * | 2016-11-29 | 2017-05-17 | Российская Федерация от имени которой выступает Министерство промышленности и торговли РФ | Amphibious hovercraft propulsion system |
RU182553U1 (en) * | 2018-05-10 | 2018-08-22 | Андрей Геннадьевич Винников | WIND POWER DRIVE |
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 (en) * | 1960-12-19 | 1963-01-25 | Lyonnaise Ventilation | Advanced axial fan |
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 (en) * | 1985-11-19 | 1988-01-29 | Onera (Off Nat Aerospatiale) | IMPROVEMENTS ON AIR PROPELLERS WITH REGARD TO THE PROFILE OF THEIR BLADES |
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 (en) * | 1991-09-30 | 1994-06-30 | Владимир Ильич Петинов | Propeller blade |
GB9412414D0 (en) * | 1994-06-21 | 1994-08-10 | Secr Defence | Rotary winged aircraft |
-
2004
- 2004-01-20 RU RU2004101034/11A patent/RU2256585C1/en not_active IP Right Cessation
-
2005
- 2005-01-11 EA EA200600370A patent/EA007477B1/en not_active IP Right Cessation
- 2005-01-11 JP JP2006549178A patent/JP2007518620A/en active Pending
- 2005-01-11 WO PCT/RU2005/000004 patent/WO2005068292A1/en not_active Application Discontinuation
- 2005-01-11 CN CNB2005800027395A patent/CN100436254C/en not_active Expired - Fee Related
- 2005-01-11 KR KR1020067012778A patent/KR100806016B1/en not_active IP Right Cessation
- 2005-01-11 US US10/586,571 patent/US20080219848A1/en not_active Abandoned
- 2005-01-11 EP EP05710991A patent/EP1707485A4/en not_active Ceased
- 2005-11-01 UA UAA200603747A patent/UA80216C2/en 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 |
---|---|
EP1707485A1 (en) | 2006-10-04 |
RU2004101034A (en) | 2005-06-20 |
RU2256585C1 (en) | 2005-07-20 |
CN100436254C (en) | 2008-11-26 |
JP2007518620A (en) | 2007-07-12 |
KR100806016B1 (en) | 2008-02-26 |
EA007477B1 (en) | 2006-10-27 |
CN1910081A (en) | 2007-02-07 |
UA80216C2 (en) | 2007-08-27 |
WO2005068292A1 (en) | 2005-07-28 |
EA200600370A1 (en) | 2006-06-30 |
EP1707485A4 (en) | 2007-10-03 |
KR20060103938A (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 |