CN104340348A - Combined propeller blade structure - Google Patents
Combined propeller blade structure Download PDFInfo
- Publication number
- CN104340348A CN104340348A CN201310329750.9A CN201310329750A CN104340348A CN 104340348 A CN104340348 A CN 104340348A CN 201310329750 A CN201310329750 A CN 201310329750A CN 104340348 A CN104340348 A CN 104340348A
- Authority
- CN
- China
- Prior art keywords
- blade unit
- blade
- flabellum
- propeller fan
- combined type
- 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.)
- Pending
Links
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 26
- 241000883990 Flabellum Species 0.000 claims description 47
- 238000010586 diagram Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 239000002131 composite material Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
Classifications
-
- 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
-
- 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
Abstract
The invention provides a combined propeller blade structure comprising at least one rotating shaft and a rotating side face corresponding to the rotating shaft. A plurality of blades are arranged on the rotating side face. The combined propeller blade structure is characterized in that each blade is composed of a plurality of blade units, the distance between any two adjacent blades is larger than that between any two adjacent blade units, and a suction side of each blade unit on the downstream side is located on a pressure side of the corresponding blade unit on the upstream side. In the equal-radius section of any one blade, in the rotational axial direction, the arrangement position of a front-edge endpoint of each blade unit on the downstream side is behind a rear-edge endpoint of the adjacent blade unit on the upstream side, and the maximum distance between the endpoints does not exceed 25% of the radius of the adjacent blade unit on the upstream side; in the rotational direction, the arrangement position of the front-edge endpoint of each blade unit on the downstream side is located on the front-rear line pressure side of the adjacent blade unit on the upstream side, and the maximum angle of the rotational position does not exceed (360 degrees/2N), wherein the N is the number of the blades.
Description
Technical field
The present invention relates to a kind of propeller fan blade structure for working in fluid liquid, particularly a kind of combined type propeller fan blade structure.
Background technology
Propeller fan blade structure is the important equipment of human industry, comprises the propelling unit of boats and ships, submarine, all generally utilizes propeller fan blade structure to drive.Therefore, the enhancing efficiency of propeller fan blade structure, for cost control, work efficiency or energy conservation, all very important.
Typical propeller fan blade structure must possess at least one S. A. and the rotating side that arrange corresponding to this S. A., and this rotating side is configured with a plurality of identical flabellum.Prior art is that the size, angle etc. to this flabellum is carried out adjustment and asked for maximum efficiency, however at present the usefulness of gained to bottleneck, without further significantly promoting.
Therefore, the present invention proposes a kind of combined type propeller fan blade structure to promote the usefulness of propeller flabellum.
Summary of the invention
The object of the present invention is to provide a kind of combined type propeller fan blade structure, to promote the usefulness of propeller flabellum.
For achieving the above object, the technical solution used in the present invention is:
A kind of combined type propeller fan blade structure, possess at least one S. A. and the rotating side that arrange corresponding to this S. A., this rotating side is configured with a plurality of flabellum, it is characterized in that: each aforementioned flabellum is made up of plurality of vanes unit, wherein the distance of arbitrary adjacent two flabellums is greater than the distance between arbitrary adjacent two blade units, and the suction side of the blade unit in downstream is positioned at the blade unit of upstream side on the pressure side; And in the section such as radius such as grade of arbitrary aforementioned flabellum, the setting position of the leading edge end points of the blade unit in downstream, on axial rotary, after being positioned at the trailing edge end points of adjacent upstream lateral lobe blade unit, and the ultimate range between the trailing edge end points of the leading edge end points of the blade unit in this downstream and this adjacent upstream lateral lobe blade unit on axial rotary is no more than 25% of the radius of this adjacent upstream lateral lobe blade unit; And in a rotational direction, the setting position of the leading edge end points of the blade unit in this downstream is positioned at the center line acting face side of adjacent upstream lateral lobe blade unit, and maximum angle is in a rotational direction no more than 360 °/2N between the center line of the leading edge end points of the blade unit in this downstream and this adjacent upstream lateral lobe blade unit, wherein N is the quantity of flabellum.
Another object of the present invention is in aforesaid combined type propeller fan blade structure, in arbitrary aforementioned flabellum, minimum blade unit area is greater than 50% of maximum blade unit area.
Another object of the present invention is in aforesaid combined type propeller fan blade structure, in arbitrary aforementioned flabellum, minimum blade unit radius is greater than 60% of maximum blade unit radius.
Another object of the present invention is in aforesaid combined type propeller fan blade structure, in arbitrary aforementioned flabellum, there is reinforced structure to connect adjacent blade unit.
Another object of the present invention is in aforesaid combined type propeller fan blade structure, wherein each aforementioned flabellum by two, three or more blade units formed.
Another object of the present invention is in aforesaid combined type propeller fan blade structure, in arbitrary aforementioned flabellum, wherein the geometric configuration of blade unit may be the same or different.
The present invention relies on this composite blade structure, significantly can promote usefulness, the energy use efficiency of propeller flabellum, and have low cost and characteristic easy to implement.
Accompanying drawing explanation
Fig. 1 is the block diagram of existing propeller fan blade structure;
Fig. 2 is the block diagram of a kind of combined type propeller fan blade structure of the present invention;
Fig. 3 is a kind of combined type propeller fan blade structure of the present invention, is waiting the blade unit cross section relative position schematic diagram on radius;
Fig. 4 is improved efficiency schematic diagram of the present invention.
Description of reference numerals: 10,20 rotors; 11,21 flabellums; 22 blade units; The leading edge end points of the blade unit in 31 downstreams; The trailing edge end points of the blade unit of 32 upstream sides; 41,42 efficiency characteristic.
Detailed description of the invention
Of the present invention being described in more detail in describes subsequently, and preferred embodiment described herein as the purposes illustrated and describe, and is not used to limit scope of the present invention.
The present invention discloses a kind of combined type propeller fan blade structure, possess at least one S. A. and the rotating side that arrange corresponding to this S. A., this rotating side is configured with a plurality of flabellum, it is characterized by: each aforementioned flabellum is made up of plurality of vanes unit, wherein the distance of arbitrary adjacent two flabellums is greater than the distance between arbitrary adjacent two blade units, and the suction side (Suction Side) of the blade unit in downstream is positioned on the pressure side (the Pressure Side) of the blade unit of upstream side; And in the section such as radius such as grade of arbitrary aforementioned flabellum, the setting position of the leading edge end points of the blade unit in downstream, on axial rotary, after being positioned at the trailing edge end points of adjacent upstream lateral lobe blade unit, and its ultimate range is no more than 25% of the radius of this adjacent upstream lateral lobe blade unit; And in a rotational direction, be positioned at the center line acting face side of adjacent upstream lateral lobe blade unit, and its maximum angle is no more than (360 °/2N) place, wherein N is the quantity of flabellum.The present invention relies on the structure formed with single blade unit by each flabellum in prior art, change and formed with plurality of vanes unit, and rely on the relative position between blade unit, significantly can promote usefulness, the efficiency of energy utilization of propeller flabellum, and there is low cost and characteristic easy to implement.
Refer to Fig. 1, be existing propeller fan blade structure, it has a rotor 10, and the rotating side of this rotor 10 is configured with a plurality of identical flabellum 11, and wherein each flabellum 11 is single blade unit and forms.
Then Fig. 2 please be refer to, for combined type propeller fan blade structure of the present invention, it has a rotor 20, the rotating side of this rotor 20 is configured with a plurality of identical flabellum 21, wherein each flabellum 21 is made up of plurality of vanes unit 22, each flabellum 21 is made up of two blade units in the present embodiment, also can be made up of the blade unit of more than two, and such as three blade units formed.Wherein the distance of arbitrary adjacent two flabellums is greater than the distance between arbitrary adjacent two blade units.In addition, the blade unit arrangement in each combined type propeller flabellum or geometric configuration can identical also can be different.
Then refer to Fig. 3, be combined type propeller fan blade structure of the present invention, waiting the blade unit cross section relative position schematic diagram on radius; As seen from Figure 3, in the radius cross section such as grade of arbitrary aforementioned flabellum, the setting position of the leading edge end points 31 of the blade unit in downstream, on axial rotary A, after being positioned at the trailing edge end points 32 of adjacent upstream lateral lobe blade unit, and its ultimate range is no more than 25% (0.25R) of the radius R of this adjacent upstream lateral lobe blade unit; And on hand of rotation B, after being positioned at the center line L of adjacent upstream lateral lobe blade unit, and its maximum angle is no more than (360 °/2N) place, wherein N is the quantity of flabellum.
Another preferred embodiment of combined type propeller fan blade structure of the present invention, in arbitrary aforementioned flabellum, also can have reinforced structure to connect adjacent blade unit; The material of this reinforced structure can be identical with blade unit, also can be different from blade unit; This reinforced structure also can be arranged in integrated mode with blade unit.
In another preferred embodiment (not shown) of combined type propeller fan blade structure of the present invention, in arbitrary aforementioned flabellum, the blade unit of side, upstream and downstream, also can the mode of different area size arrange, wherein, the area A 2 of minimum blade unit, is greater than 50% of the area A 1 of maximum blade unit.
In another preferred embodiment (not shown) of combined type propeller fan blade structure of the present invention, in arbitrary aforementioned flabellum, the blade unit of side, upstream and downstream, also can the mode of different radii size arrange, such as, the radius R 2 of minimum blade unit, is greater than 60% of the radius R 1 of maximum blade unit.
Then referring to Fig. 4, is improved efficiency schematic diagram of the present invention; Wherein J is propeller operating condition Va/nD (Va is speed of advance, and n is rotating speed per second, and D is propeller diameter), and η is propulsion coefficient; As seen from Figure 4, use combined type propeller fan blade structure of the present invention, its efficiency characteristic 41, the efficiency characteristic 42 that high can have propeller fan blade structure is a lot of; Therefore, combined type propeller fan blade structure of the present invention, really can reduce power consumption, significantly promote the usefulness of propeller flabellum.
Inventor analyzes through computer fluid mechanics numerical operation, and after a large amount of computing research, discovery must be concluded by side; Utilize combined type propeller blade construction, the interlobate physical dimension in front and back and relative position, there is important impact, meeting under respective conditions proposed by the invention, really its effect can be promoted particularly, not only otherwise effectively cannot promote effect, usefulness can be caused on the contrary to reduce, non-random change and completing easily.
More than illustrate just illustrative for the purpose of the present invention; and nonrestrictive, those of ordinary skill in the art understand, when not departing from the spirit and scope that claim limits; many amendments, change or equivalence can be made, but all will fall within protection scope of the present invention.
Claims (7)
1. a combined type propeller fan blade structure, possess at least one S. A. and the rotating side that arrange corresponding to this S. A., this rotating side is configured with a plurality of flabellum, it is characterized in that: each aforementioned flabellum is made up of plurality of vanes unit, wherein the distance of arbitrary adjacent two flabellums is greater than the distance between arbitrary adjacent two blade units, and the suction side of the blade unit in downstream is positioned at the blade unit of upstream side on the pressure side; And in the section such as radius such as grade of arbitrary aforementioned flabellum, the setting position of the leading edge end points of the blade unit in downstream, on axial rotary, after being positioned at the trailing edge end points of adjacent upstream lateral lobe blade unit, and the ultimate range between the trailing edge end points of the leading edge end points of the blade unit in this downstream and this adjacent upstream lateral lobe blade unit on axial rotary is no more than 25% of the radius of this adjacent upstream lateral lobe blade unit; And in a rotational direction, the setting position of the leading edge end points of the blade unit in this downstream is positioned at the center line acting face side of adjacent upstream lateral lobe blade unit, and maximum angle is in a rotational direction no more than 360 °/2N between the center line of the leading edge end points of the blade unit in this downstream and this adjacent upstream lateral lobe blade unit, wherein N is the quantity of flabellum.
2. combined type propeller fan blade structure according to claim 1, it is characterized in that: in arbitrary aforementioned flabellum, minimum blade unit area is greater than 50% of maximum blade unit area.
3. combined type propeller fan blade structure according to claim 1, it is characterized in that: in arbitrary aforementioned flabellum, minimum blade unit radius is greater than 60% of maximum blade unit radius.
4. combined type propeller fan blade structure according to claim 1, is characterized in that: in arbitrary aforementioned flabellum, also has reinforced structure to connect adjacent blade unit.
5. combined type propeller fan blade structure according to claim 1, is characterized in that: each aforementioned flabellum is made up of two blade units.
6. combined type propeller fan blade structure according to claim 1, is characterized in that: each aforementioned flabellum is made up of three blade units.
7. combined type propeller fan blade structure according to claim 1, is characterized in that: each aforementioned flabellum is all identical.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310329750.9A CN104340348A (en) | 2013-07-31 | 2013-07-31 | Combined propeller blade structure |
| US14/141,158 US20150037157A1 (en) | 2013-07-31 | 2013-12-26 | Composite propeller blade structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310329750.9A CN104340348A (en) | 2013-07-31 | 2013-07-31 | Combined propeller blade structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104340348A true CN104340348A (en) | 2015-02-11 |
Family
ID=52427824
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310329750.9A Pending CN104340348A (en) | 2013-07-31 | 2013-07-31 | Combined propeller blade structure |
Country Status (2)
| Country | Link |
|---|---|
| US (1) | US20150037157A1 (en) |
| CN (1) | CN104340348A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108367801A (en) * | 2016-05-27 | 2018-08-03 | 夏洛工程有限公司 | Propeller |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140161622A1 (en) | 2012-12-10 | 2014-06-12 | Gregory Charles Sharrow | Propeller |
| US9926058B2 (en) | 2012-12-10 | 2018-03-27 | Sharrow Engineering Llc | Propeller |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3082827A (en) * | 1962-04-20 | 1963-03-26 | United Aircraft Corp | Marine propeller |
| JPS6243391A (en) * | 1985-08-21 | 1987-02-25 | Ishikawajima Harima Heavy Ind Co Ltd | Propeller for propulsion for ship or the like |
| GB2204643A (en) * | 1986-09-03 | 1988-11-16 | Dennis George Bourne | Marine propeller |
| TW303334B (en) * | 1994-12-21 | 1997-04-21 | Honda Motor Co Ltd | |
| CN101135318A (en) * | 2006-08-31 | 2008-03-05 | 财团法人工业技术研究院 | Blade wheel structure and centrifugal fan device using the same |
| WO2012050441A1 (en) * | 2010-10-11 | 2012-04-19 | Jan Terlouw | Marine propeller with front and further blade |
| CN202574600U (en) * | 2012-03-23 | 2012-12-05 | 苑青林 | Double-vane propeller |
Family Cites Families (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US680671A (en) * | 1901-05-02 | 1901-08-13 | Myers Screw Propeller Syndicate Ltd | Screw-propeller. |
| US1779026A (en) * | 1928-04-12 | 1930-10-21 | Wragg Charles Arthur | Multiple-blade propeller |
| US1775315A (en) * | 1929-03-27 | 1930-09-09 | Charles Henry Butler | Propeller |
| US1868113A (en) * | 1930-09-22 | 1932-07-19 | Spontan Ab | Fan |
| US2199823A (en) * | 1939-05-02 | 1940-05-07 | Kessery Peter | Propeller |
| US2552651A (en) * | 1947-09-10 | 1951-05-15 | John F Skold | Fan wheel with arcuate blade forming strips |
| US4789306A (en) * | 1985-11-15 | 1988-12-06 | Attwood Corporation | Marine propeller |
| ATE56407T1 (en) * | 1986-07-07 | 1990-09-15 | Edwin S Geary | PROPELLER AND CONNECTOR. |
| US5890875A (en) * | 1997-01-27 | 1999-04-06 | Silvano; David | Blade apparatus |
| ATE438787T1 (en) * | 2001-01-26 | 2009-08-15 | Minoru Yoshida | FLOW MACHINE |
| US20040126242A1 (en) * | 2002-12-30 | 2004-07-01 | Larry Howard | Boat propeller and guard device |
| EP2311726B1 (en) * | 2009-10-16 | 2012-12-05 | Charles Steven Powers | Marine propeller with reverse thrust cup |
| USD630724S1 (en) * | 2010-06-20 | 2011-01-11 | Pan Air Electric Co., Ltd. | Ceiling fan blade |
| TWI468590B (en) * | 2011-10-21 | 2015-01-11 | Pan Air Electric Co Ltd | Blade structure and ceiling fan employing the same |
-
2013
- 2013-07-31 CN CN201310329750.9A patent/CN104340348A/en active Pending
- 2013-12-26 US US14/141,158 patent/US20150037157A1/en not_active Abandoned
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3082827A (en) * | 1962-04-20 | 1963-03-26 | United Aircraft Corp | Marine propeller |
| JPS6243391A (en) * | 1985-08-21 | 1987-02-25 | Ishikawajima Harima Heavy Ind Co Ltd | Propeller for propulsion for ship or the like |
| GB2204643A (en) * | 1986-09-03 | 1988-11-16 | Dennis George Bourne | Marine propeller |
| TW303334B (en) * | 1994-12-21 | 1997-04-21 | Honda Motor Co Ltd | |
| CN101135318A (en) * | 2006-08-31 | 2008-03-05 | 财团法人工业技术研究院 | Blade wheel structure and centrifugal fan device using the same |
| WO2012050441A1 (en) * | 2010-10-11 | 2012-04-19 | Jan Terlouw | Marine propeller with front and further blade |
| CN202574600U (en) * | 2012-03-23 | 2012-12-05 | 苑青林 | Double-vane propeller |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108367801A (en) * | 2016-05-27 | 2018-08-03 | 夏洛工程有限公司 | Propeller |
Also Published As
| Publication number | Publication date |
|---|---|
| US20150037157A1 (en) | 2015-02-05 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150211 |