CA2455075A1 - Propulsion linearizing mechanism - Google Patents
Propulsion linearizing mechanism Download PDFInfo
- Publication number
- CA2455075A1 CA2455075A1 CA002455075A CA2455075A CA2455075A1 CA 2455075 A1 CA2455075 A1 CA 2455075A1 CA 002455075 A CA002455075 A CA 002455075A CA 2455075 A CA2455075 A CA 2455075A CA 2455075 A1 CA2455075 A1 CA 2455075A1
- Authority
- CA
- Canada
- Prior art keywords
- propeller
- mechanism according
- elements
- propeller elements
- baffle
- 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.)
- Granted
Links
- 239000012530 fluid Substances 0.000 claims abstract 10
- 239000007789 gas Substances 0.000 claims 2
- 238000011144 upstream manufacturing Methods 0.000 claims 2
- 239000012809 cooling fluid Substances 0.000 claims 1
- 230000008878 coupling Effects 0.000 claims 1
- 238000010168 coupling process Methods 0.000 claims 1
- 238000005859 coupling reaction Methods 0.000 claims 1
- 230000004927 fusion Effects 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 claims 1
- 238000005086 pumping Methods 0.000 claims 1
- 230000003068 static effect Effects 0.000 abstract 2
- 230000006698 induction Effects 0.000 abstract 1
- 238000009413 insulation Methods 0.000 abstract 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/16—Combinations of two or more pumps ; Producing two or more separate gas flows
- F04D25/166—Combinations of two or more pumps ; Producing two or more separate gas flows using fans
-
- 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
-
- 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
- B63H1/16—Propellers having a shrouding ring attached to 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
- B63H1/28—Other means for improving propeller efficiency
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63H—MARINE PROPULSION OR STEERING
- B63H5/00—Arrangements on vessels of propulsion elements directly acting on water
- B63H5/07—Arrangements on vessels of propulsion elements directly acting on water of propellers
- B63H5/08—Arrangements on vessels of propulsion elements directly acting on water of propellers of more than one propeller
-
- 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
- B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
Abstract
A fluid flow control mechanism is provided for linearizing a fluid flow. The mechanism includes a frame having a cylindrical outer baffle which rotatably supports a plurality of propeller elements thereon. Each propeller element defines a respective sweep area as the propeller element is rotated which overlaps sweep areas of adjacent propeller elements. The outer baffle circumscribes an outer periphery of the collective sweeps areas of the respective propeller elements. The propeller elements rotate in the same direction whereby forces of curvature flow of adjacent propeller elements substantially cancel one another to linearize fluid flow through the mechanism. Additional baffles and infills within the areas of non blade swee ps may be provided for particular applications of the mechanism. In various applications, linear forces of vector flow are formed by integrating curvatu re forces of tangential flow and economy flow systems are formed by integrating curvature forces potentials on the planes of rotating propellers to provide the emission and induction flow with an insulation whereby fluid in the immediate vicinity of the mobile flow remains in an undisturbed static state . This allows a fluid propulsion assembly to be fitted with an outer utility mantle in the static zone of the field.
Claims (38)
1. A fluid flow control mechanism for linearizing a fluid flow, the mechanism comprising:
a generally cylindrical outer baffle arranged to direct flow of fluid therethrough in a flow direction substantially parallel to a central main axis of the outer baffle from an upstream side to a downstream side of the outer baffle; and a plurality of propeller elements supported for rotation, each about a respective propeller axis, the propeller axes being parallel to one another and the main axis of the outer baffle and being spaced circumferentially about the main axis;
each propeller element defining a respective sweep area as the propeller element is rotated about the respective propeller axis thereof which lies perpendicular to the respective propeller axis;
the propeller elements being located such that the outer baffle circumscribes an outer periphery of the collective sweep areas of the respective propeller elements and such that the sweep area of each propeller element is arranged to overlap the sweep area of adjacent propeller elements;
the propeller elements being supported for rotation in the same direction whereby forces of curvature flow of adjacent propeller elements substantially cancel one another to linearize fluid flow in the flow direction.
a generally cylindrical outer baffle arranged to direct flow of fluid therethrough in a flow direction substantially parallel to a central main axis of the outer baffle from an upstream side to a downstream side of the outer baffle; and a plurality of propeller elements supported for rotation, each about a respective propeller axis, the propeller axes being parallel to one another and the main axis of the outer baffle and being spaced circumferentially about the main axis;
each propeller element defining a respective sweep area as the propeller element is rotated about the respective propeller axis thereof which lies perpendicular to the respective propeller axis;
the propeller elements being located such that the outer baffle circumscribes an outer periphery of the collective sweep areas of the respective propeller elements and such that the sweep area of each propeller element is arranged to overlap the sweep area of adjacent propeller elements;
the propeller elements being supported for rotation in the same direction whereby forces of curvature flow of adjacent propeller elements substantially cancel one another to linearize fluid flow in the flow direction.
2. The mechanism according to claim 1 wherein each propeller element comprises a pair of diametrically opposed blades.
3. The mechanism according to claim 2 wherein the propeller elements are all supported for rotation within a common plane, rotation of each propeller element being fixed in timing with rotation of adjacent propeller elements to avoid collision of the propeller elements at the overlapping sweep areas.
4. The mechanism according to claim 1 wherein the propeller axes are fixed in position relative to one another.
5. The mechanism according to claim 1 wherein the propeller elements each comprise a plurality of blades, each propeller element being rotatable within the respective sweep area which is parallel and spaced in a direction of the main axis from the overlapping sweep areas of adjacent propeller elements.
6. The mechanism according to claim 1 wherein each propeller element comprises a plurality of blades, the sweep area of each propeller element overlapping the sweep area of adjacent propeller elements within a range of 40% to 60% of a length of the blades of the propeller elements.
7. The mechanism according to claim 6 wherein the sweep area of each propeller element overlaps the sweep area of adjacent propeller elements by approximately 50% of a length of the blades of the propeller elements.
8. The mechanism according to claim 1 wherein there is provided a generally cylindrical inner baffle inscribed within an inner periphery of the collective sweep areas of the respective propeller elements.
9. The mechanism according to claim 8 wherein the propeller elements are located relative to one another such that an unswept cross sectional area between the inner and outer baffles is substantially equal to an overlapping portion of the sweep areas of the propeller elements.
10. The mechanism according to claim 8 wherein the inner and outer baffles at the upstream side of the outer baffles extend in a direction of the main axis beyond the propeller elements.
11. The mechanism according to claim 8 wherein the outer baffle includes a shelf extending radially outward a distance substantially equal or greater than a diameter of one of the sweep areas of the propeller elements.
12. The mechanism according to claim 8 wherein there is provided 8 propeller elements supported at even circumferential spacings between the inner and outer baffles, a cross sectional inner area spanning the inner baffle being substantially equal to the sweep area of one of the propeller elements.
13. The mechanism according to claim 12 wherein the inner area spanning the inner baffle is enclosed.
14. The mechanism according to claim 12 wherein there is provided a driving motor housed within the inner area for driving rotation of the propeller elements.
15. The mechanism according to claim 12 wherein there is provided a driven rotor housed within the inner area for being driven by rotation of the propeller elements when supported in a moving fluid.
16. The mechanism according to claim 12 wherein the inner area houses common gearing coupling the propeller elements for rotation together at a predetermined timing relative to one another.
17. The mechanism according to claim 8 wherein there is provided a cylindrical central baffle concentrically spaced between the inner and outer baffles, the propeller axes being located at spaced positions about the central baffle.
18. The mechanism according to claim 18 wherein there is provided a plurality of radial baffles extending in a radial direction from the main axis between the inner and outer baffles and supporting the central baffle.
19. The mechanism according to claim 18 wherein each propeller axis is located at an intersection of the central baffle and a respective one of the radial baffles.
20. The mechanism according to claim 18 wherein the central baffle and the radial baffles are supported on a downstream side of the propeller elements.
21. The mechanism according to claim 1 wherein an unswept area between the outer baffle and the collective sweep areas of the propeller elements is enclosed by contoured infills which surround the collective sweep areas of the propeller elements, the contoured infills being in relief and fixed with respect to the outer baffle.
22. The mechanism according to claim 21 wherein the contoured infills are tapered to be substantially flush with the outer baffle as the contoured infills extend in a direction of the main axis away from opposing sides of the propeller elements.
23. The mechanism according to claim 21 in a pumping configuration.
24. The mechanism according to claim 21 wherein there is provided a central infill spanning a central unswept area surrounded by the collective sweep areas of the propeller elements, the central infill being tapered towards opposing apexes along the main axis on opposing sides of the propeller elements.
25. The mechanism according to claim 24 in a turbine generator configuration in which the central infill houses a rotor which is coupled to the propeller elements so as to be driven by rotation of the propeller elements and wherein there is provided a power take off mechanism for capturing power from rotation of the rotor.
26. The mechanism according to claim 25 wherein each propeller element comprises a plurality of blades at various positions about a full circumference of the propeller element, the blades of each propeller element being rotatable in one or more planes which are offset in a direction of the main axis from the blades of adjacent propeller elements.
27. The mechanism according to claim 26 wherein length of the blades increases in the flow direction.
28 28. The mechanism according to claim 1 wherein there is provided four propeller elements supported at evenly spaced positions about the main axis, an inner periphery of each sweep area being intersected by the main axis.
29. The mechanism according to claim 28 wherein there is provided a generally cylindrical central baffle intersecting the propeller axes.
30. The mechanism according to claim 29 wherein there is provided a plurality of radial baffles extending in a radial direction of the main axis and supporting the central baffle, the radial baffles intersecting one another at the main axis.
31. The mechanism according to claim 1 wherein the propeller elements are rotatably supported on a frame with the propeller axes in fixed relation to one another and the frame, the frame being supported for rotation about the main axis.
32. The mechanism according to claim 1 in a turbo fan jet compressor configuration, the mechanism further comprising:
contoured infills enclosing an unswept area between the outer baffle and the collective sweep areas of the propeller elements, the contoured infills surrounding the collective sweep areas of the propeller elements and being tapered on opposing sides of the propeller elements towards the outer baffle;
a central infill spanning a central unswept area surrounded by the collective sweep areas of the propeller elements, the central infill being tapered towards the main axis on opposing sides of the propeller elements;
a cylindrical central baffle concentrically spaced between the central infill and the outer baffle, the propeller axes being located at spaced positions about the central baffle; and a plurality of radial baffles extending in a radial direction of the main axis between the central infill and outer baffles and supporting the central baffle.
contoured infills enclosing an unswept area between the outer baffle and the collective sweep areas of the propeller elements, the contoured infills surrounding the collective sweep areas of the propeller elements and being tapered on opposing sides of the propeller elements towards the outer baffle;
a central infill spanning a central unswept area surrounded by the collective sweep areas of the propeller elements, the central infill being tapered towards the main axis on opposing sides of the propeller elements;
a cylindrical central baffle concentrically spaced between the central infill and the outer baffle, the propeller axes being located at spaced positions about the central baffle; and a plurality of radial baffles extending in a radial direction of the main axis between the central infill and outer baffles and supporting the central baffle.
33. The mechanism according to claim 32 wherein each propeller element comprises a plurality of pairs of diametrically opposed blades which are stacked along the propeller axis at various angles relative to one another in a helical configuration, each blade having an equal angle pitch of no more than 45 degrees.
34. The mechanism according to claim 33 wherein the blades of each propeller element lie in a common plane with corresponding blades of adjacent propeller elements, the propeller elements being rotated together at a predetermined timing relative to one another to avoid collision of adjacent propeller elements having overlapping sweep areas.
35. The mechanism according to claim 1 in a polarizing unit configuration for production of plasma by low temperature gas fusion, the mechanism further comprising:
a generally cylindrical inner baffle inscribed within an inner periphery of the collective sweep areas of the respective propeller elements;
a generally cylindrical central baffle concentrically spaced between the inner and outer baffles; and a plurality of radial baffles extending in a radial direction of the main axis between the inner and outer baffles and supporting the central baffle;
at least one of the baffles including a passage for receiving a cooling fluid to be circulated therethrough.
a generally cylindrical inner baffle inscribed within an inner periphery of the collective sweep areas of the respective propeller elements;
a generally cylindrical central baffle concentrically spaced between the inner and outer baffles; and a plurality of radial baffles extending in a radial direction of the main axis between the inner and outer baffles and supporting the central baffle;
at least one of the baffles including a passage for receiving a cooling fluid to be circulated therethrough.
36. The mechanism according to claim 35 wherein each propeller element comprises a pair of diametrically opposed blades, each having a pitch angle of less than 45 degrees, the sweep area of each propeller element overlapping the sweep area of adjacent propeller elements by approximately 50% of a length of the blades of the propeller elements.
37. The mechanism according to claim 35 wherein there is provided six propeller elements which are supported for rotation within a generally common plane, rotation of each propeller element being fixed in timing with rotation of adjacent propeller elements to avoid collision of the propeller elements at the overlapping sweep areas.
38. The mechanism according to claim 35 in combination with a sealed spherical vessel into which gases are pulsed at intermittent intervals and plasma is extracted.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US30978101P | 2001-08-06 | 2001-08-06 | |
| US60/309,781 | 2001-08-06 | ||
| PCT/CA2002/001224 WO2003014853A1 (en) | 2001-08-06 | 2002-08-06 | Fluid flow control mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2455075A1 true CA2455075A1 (en) | 2003-02-20 |
| CA2455075C CA2455075C (en) | 2010-07-20 |
Family
ID=23199654
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2455075A Expired - Fee Related CA2455075C (en) | 2001-08-06 | 2002-08-06 | Propulsion linearizing mechanism |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US6988868B2 (en) |
| JP (1) | JP2004537680A (en) |
| CA (1) | CA2455075C (en) |
| DE (1) | DE10297109T5 (en) |
| WO (1) | WO2003014853A1 (en) |
Families Citing this family (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7137775B2 (en) | 2003-03-20 | 2006-11-21 | Huntair Inc. | Fan array fan section in air-handling systems |
| US7597534B2 (en) | 2003-03-20 | 2009-10-06 | Huntair, Inc. | Fan array fan section in air-handling systems |
| US11255332B2 (en) | 2003-03-20 | 2022-02-22 | Nortek Air Solutions, Llc | Modular fan housing with multiple modular units having sound attenuation for a fan array for an air-handling system |
| EP2118469B1 (en) * | 2007-02-05 | 2016-03-30 | BorgWarner, Inc. | Combustion engine |
| WO2009102227A2 (en) * | 2008-02-12 | 2009-08-20 | Dumitru Ionescu | The direction acceleration principle, the direction acceleration devices and the direction acceleration devices systems |
| JP2011046355A (en) * | 2009-08-28 | 2011-03-10 | Kitakyushu Foundation For The Advancement Of Industry Science & Technology | Flying body |
| CN103552679A (en) * | 2013-11-18 | 2014-02-05 | 北京理工大学 | Small four-axle autonomous underwater robot based on vector thrust |
| US20190023397A1 (en) * | 2015-11-02 | 2019-01-24 | Byeong-Chae GANG | Drones with Self-Generating Function |
| KR101627680B1 (en) * | 2015-11-05 | 2016-06-07 | 남양우 | Airplane structure |
| US10981649B2 (en) | 2018-09-17 | 2021-04-20 | Amazon Technologies, Inc. | Six degree of freedom aerial vehicle having reconfigurable wings |
| US11249477B2 (en) | 2018-09-17 | 2022-02-15 | Amazon Technologies, Inc. | Six degree of freedom aerial vehicle having reconfigurable propellers |
| US11136119B2 (en) * | 2018-09-17 | 2021-10-05 | Amazon Technologies, Inc. | Six degree of freedom aerial vehicle having reconfigurable motors |
| US11130568B2 (en) * | 2018-11-08 | 2021-09-28 | Textron Innovations Inc. | Autonomous thrust vectoring ring wing pod |
| TWI763447B (en) * | 2021-04-20 | 2022-05-01 | 林瑤章 | Flying device with double wings |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1845561A (en) * | 1931-03-19 | 1932-02-16 | Runge Fred George | Aeroplane lifting device |
| US2729389A (en) * | 1954-09-10 | 1956-01-03 | Westinghouse Electric Corp | Air translating apparatus |
| GB1331497A (en) | 1971-09-29 | 1973-09-26 | Stone Manganese Marine Ltd | Propulsion systems for ships |
| US6139439A (en) * | 1994-05-11 | 2000-10-31 | Nicholas M. Kavouklis | Means for linearizing an open air flow |
| US5810289A (en) | 1997-09-19 | 1998-09-22 | Sager Innovations Inc. | High velocity propeller |
-
2002
- 2002-08-06 WO PCT/CA2002/001224 patent/WO2003014853A1/en active Application Filing
- 2002-08-06 CA CA2455075A patent/CA2455075C/en not_active Expired - Fee Related
- 2002-08-06 JP JP2003519721A patent/JP2004537680A/en active Pending
- 2002-08-06 DE DE10297109T patent/DE10297109T5/en not_active Withdrawn
- 2002-08-06 US US10/485,208 patent/US6988868B2/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| WO2003014853A1 (en) | 2003-02-20 |
| US20040240998A1 (en) | 2004-12-02 |
| CA2455075C (en) | 2010-07-20 |
| US6988868B2 (en) | 2006-01-24 |
| JP2004537680A (en) | 2004-12-16 |
| DE10297109T5 (en) | 2004-08-05 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| MKLA | Lapsed |
Effective date: 20180806 |