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(12) United States Patent (10) Patent No.: US 6,948,910 B2 Polacsek (45) Date of Patent: Sep

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(12) United States Patent (10) Patent No.: US 6,948,910 B2 Polacsek (45) Date of Patent: Sep USOO694891 OB2 (12) United States Patent (10) Patent No.: US 6,948,910 B2 PolacSek (45) Date of Patent: Sep. 27, 2005 (54) SPIRAL-BASED AXIAL FLOW DEVICES William C. Elmore, Mark A. Heald- “Physics of Waves” (C) 1969 PP 5–35, 203–205, 234-235, ISBN-0486 64926–1, (76) Inventor: Ronald R. Polacsek, 73373 Joshua Dover Publ., Canada. Tree St., Palm Desert, CA (US) 92260 A.A. Andronov, AA. Viti, “Theory of Oscillators.” (C) 1966, (*) Notice: Subject to any disclaimer, the term of this pp. 56–58, 199-200, ISBDN-0486-65508–3, Dover Pub patent is extended or adjusted under 35 lishing, Canada. U.S.C. 154(b) by 375 days. Erik Anderson et al., Journal of Experimental Biology, “The Boundary Layer of Swimming Fish' pp 81-102 (C) Dec. 5, (21) Appl. No.: 10/194,386 2000, (C) The Company of Biologists, Great Britain. Stephen Strogatz, “Nonlinear Dynamics and Chaos” (C) 1994 (22) Filed: Jul. 12, 2002 pp. 262-279, ISBDN 0-7382-0453–6 (C) Perseus Books, (65) Prior Publication Data USA. US 2004/0009063 A1 Jan. 15, 2004 (Continued) (51) Int. Cl. ................................................ B64C 11/18 (52) U.S. Cl. ........................................ 416/1; 416/227 R Primary Examiner Edward K. Look (58) Field of Search ................................. 416/1, 227 R, Assistant Examiner Richard Edgar 416/227A, 223 R, 223 A (57) ABSTRACT (56) References Cited Axial flow devices using rigid spiral band profiled blade U.S. PATENT DOCUMENTS catenaries attached variably along and around an axially elongated profiled hub, of axially oriented profile Section 547,210 A 10/1895 Haussmann 1864,848 A 6/1932 Munk ..................... 416/132 R Sequences 75 mapped relative to truncated cones-of 1868,113 A 7/1932 Ljungstrom generation. Upon rotation and lubricity-masked progression 2,552,651 A 5/1951 Skold through axial planes-of-shear, this time-domain Sequence 3,504,990 A 4/1970 Sugden travels in 2-dimensional axial-datum-plane-relative path 3,514,215 A * 5/1970 Williams ................ 416/200 R excursions and ejects frictional adhesions via anguillar 4,445,817 A 5/1984 Wethern reverse Vortex Street thrust due to an after-body accelerating 4,610,601 A 9/1986 Gerfast wave shape-Sequence 48. This guides bound Vortex pres 4,813,633 A * 3/1989 Werle et al. ................ 244/130 Sures at linear path-velocity Substantially parallel to the 4,830,315 A * 5/1989 Presz et al. ................. 244/200 collective plane-of-Shear, conferring higher differential pres 4,830,574 A 5/1989 Wainauski Sures through path-vector-addition, improved force-vector 5,075,964. A 12/1991 Galliet 5,890,875 A 4/1999 Silvano orientation, extended laminar flows, lower form drag and tip 5,961,289 A 10/1999 Lohmann Vorticity. As a wind turbine, path-vectors are added to 2003/001265.6 A1 1/2003 Cho et al. ................... 416/235 inflow, ducting an increased mass flow inward for increased 2004/OO67138 A1 4/2004 Yoshida .................. 416/223 R power extraction per diameter. As a propeller, path-vector Subtraction guides the wave front flight-path-transverse, OTHER PUBLICATIONS allowing higher flight Velocities and improving thrust-per Harry F. Olsen-“Music, Physics and Engineering” pp torque through enhanced force vectors and mass flow rates. 208-215 (C) 1967, Book No 486-21769-8, Dover Publish ing, Canada. 7 Claims, 17 Drawing Sheets axial plane movement US 6,948,910 B2 Page 2 OTHER PUBLICATIONS C. A. Marchaj, “Aero-Hydrodynamics of Sailing”, (C) 1979 L. Prandtl, O.G. Tietjens, “ Applied Hydro-and Aerome pp. 131-140, 205–214,253–254.291, 353–381 ISBDN chanics'C) 1934 pp 166-167, 190-191, 200-209, 300-308, 0-87742-993–6, Intnt Marine Publ., USA. ISBDN 486-60375-X (C) 1957, Dover Books, USA. H.H. Hurt Jr., “Aerodynamics for Naval Aviators” (C) US Uriel Frisch, “Turbulence” (C) 1995, pp. 242, 21–26, Navy 1960 pp 67, 64, 57, 53,48, 19/46,227:232,205 Navair 103-106, 184-188, ISBDN 0-521-45103–5 (C) 1995 Cam 00–80T-80 (C) Office & Chief of Naval Operation. bridge Press, USA. Kalus Hinecke,"Jet Engines” (C) 1997, pp 34–48 ISBDN 0-7603–0459–9 C) Airlife Publishing, Great Britain. Georgi Tolstov, “Fourier Series” (C) 1962, pp 1–39, 80-91, Hunter Rouse “Elementary Mechanics of Fluids” (C) 1946 pp ISBDN 0-486-63317-9 C) 1962 Dover Press, USA. 170–171, 254-255, 288-294 ISBDN 0-486-63699-2 (C) Dover Books, (C) 1978, USA. * cited by examiner U.S. Patent Sep. 27, 2005 Sheet 1 of 17 US 6,948,910 B2 downwash with tip vortex ... ... N- tip vortex - 15 - BOUND VORTEX WAVELENGTH -- Prior Art tip vortex loss U.S. Patent Sep. 27, 2005 Sheet 2 of 17 US 6,948,910 B2 @"º"??.No. pºôl No.No. SONINA>-]\/TITANN\/ U.S. Patent Sep. 27, 2005 Sheet 3 of 17 US 6,948,910 B2 7Cs) t Ss of Revolution SSC) logarithmic spiral Citi 2 is equal amplitude expansion Curves has U.S. Patent Sep. 27, 2005 Sheet 4 of 17 US 6,948,910 B2 A r of diffusion 38 U.S. Patent Sep. 27, 2005 Sheet 5 of 17 US 6,948,910 B2 FIG 7a axial retrogression 54 angular velocity wave path progression -storia original element S. U.S. Patent Sep. 27, 2005 Sheet 6 of 17 US 6,948,910 B2 Karman Vortex StreetS sC) 1. g e 56 Y n S - \ , <2. 59 N9) 9) | 60 U.S. Patent Sep. 27, 2005 Sheet 7 of 17 US 6,948,910 B2 2.7. (7 lea U.S. Patent Sep. 27, 2005 Sheet 8 of 17 US 6,948,910 B2 65 4N Q (2)W.6 (N) U.S. Patent Sep. 27, 2005 Sheet 9 of 17 US 6,948,910 B2 U.S. Patent Sep. 27, 2005 Sheet 10 of 17 US 6,948,910 B2 FIG12 determine feedback parameters from dissipation kog decrement deterine wake rotatioin determine effective plane Meta-Element actuation choose operating foil parameters from known foi Initialize System of oscillation establ. design Meta-Element determine phase state Major cycle & Minor cle W2Logarithmic Starting reversal SS inflow dependencies friction decrement Translate sequences into feedback parameter design new foil series Helical coordinates Equation of motion for each phase state calulate dynamic forces Fourier orbit integral correct for surface tilt from phase plane spiral determine pressure 8 local sweep angles distributions calculate downwash - force coefficients Superimpose on phase wake inflow vectors determine wake rotation determine actuator plane O adjust actuation plane design stability parameters U.S. Patent Sep. 27, 2005 Sheet 11 Of 17 US 6,948,910 B2 later divergence potential E s 61 low pessure ----rrel-re-rel- - N -- NS vortex shee of discontrality FG13b propeller force decomposition conventional turtline forces 90 \ ---, -- J.-- prior art re. tangential velocity N Meta Element Conventional Turbine N Spiral axial advance downwind force downwind force Stream Tube velocity vector addition Meta Element torque for equal downwind force U.S. Patent Sep. 27, 2005 Sheet 12 0f 17 US 6,948,910 B2 axial plane movement ^ v U.S. Patent Sep. 27, 2005 Sheet 13 Of 17 US 6,948,910 B2 V S U.S. Patent Sep. 27, 2005 Sheet 14 Of 17 US 6,948,910 B2 U.S. Patent Sep. 27, 2005 Sheet 15 0f 17 US 6,948,910 B2 U.S. Patent Sep. 27, 2005 Sheet 16 0f 17 US 6,948,910 B2 U.S. Patent Sep. 27, 2005 Sheet 17 Of 17 US 6,948,910 B2 US 6,948,910 B2 1 2 SPIRAL-BASED AXAL FLOW DEVICES shaped along their length in order to compensate for these differences in velocity and resultant vector 10 of the oncom ing flow. BACKGROUND The top illustration of FIG. 2 demonstrates that since the resulting fluid force on the blade at a given location is 1. Field of Invention approximately perpendicular to the direction of incoming This invention relates to the field of acceleration or flow, this twisting results in physical forces whose directions deceleration of fluids using rotation of impulsive or propul vary in their usefulneSS in providing the intended axial Sive means to impart or extract kinetic energy. It also relates change of momentum of this fluid. to the Study of animal modes of locomotion using oscillation As shown in the middle of FIG. 3, since in addition to of, or wavelike deformation of propulsive Surfaces. It thus orientation, the force on any blade Section varies as the has application to prior art in the field of propellers, impel Square of the local Velocity as well, most purely axial thrust lers and turbines using annular, Spiral or ring type impulsive of fluid in the Swept disc occurs in a relatively Small annulus elements. Of particular interest is the following prior art of close to the blade tips 12 where fluid dynamicS recognizes Sugden, U.S. Pat. No. 3,504,990; Haussmann, U.S. Pat. No. 15 unavoidable flows that result in loss of thrust and formation 547,210, axially elongated helical propulsive and Sustaining of tip vortices 14 that due to their high transverse velocities, devices as in Butow, U.S. Pat. No. 1,015,540; Clark, U.S. continuously dissipate kinetic energy and physically drag Pat. No. 3,221,702 discloses means of generating thrust along Vortex Structures. through wave-like deformations of a vehicle body; As shown in the lower illustration of FIG. 2, since drag Ljungstrom, U.S. Pat. No. 1,868,113 describing blade ele due to-and induced by-lift in any tipped foil results in an ments deployed along a curve that is Substantially a cen increase of fluid acceleration-called induced downwash trifugal catenary.
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