WO2004070169A1 - Moteur rotatif - Google Patents

Moteur rotatif Download PDF

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Publication number
WO2004070169A1
WO2004070169A1 PCT/CA2003/000176 CA0300176W WO2004070169A1 WO 2004070169 A1 WO2004070169 A1 WO 2004070169A1 CA 0300176 W CA0300176 W CA 0300176W WO 2004070169 A1 WO2004070169 A1 WO 2004070169A1
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WO
WIPO (PCT)
Prior art keywords
rotor
engine
pivoting
annular
power
Prior art date
Application number
PCT/CA2003/000176
Other languages
English (en)
Inventor
Gilles Saint-Hilaire
Roxan Saint-Hilaire
Ylian Saint-Hilaire
Françoise SAINT-HILAIRE
Original Assignee
Gilles Saint-Hilaire
Roxan Saint-Hilaire
Ylian Saint-Hilaire
Saint-Hilaire Francoise
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Gilles Saint-Hilaire, Roxan Saint-Hilaire, Ylian Saint-Hilaire, Saint-Hilaire Francoise filed Critical Gilles Saint-Hilaire
Priority to PCT/CA2003/000176 priority Critical patent/WO2004070169A1/fr
Priority to AU2003303875A priority patent/AU2003303875B2/en
Priority to CA002511267A priority patent/CA2511267C/fr
Priority to JP2004567670A priority patent/JP2006517273A/ja
Priority to CN03826218A priority patent/CN100587230C/zh
Priority to MXPA05009639A priority patent/MXPA05009639A/es
Priority to EP03815671A priority patent/EP1592866A1/fr
Publication of WO2004070169A1 publication Critical patent/WO2004070169A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01C—ROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C1/00—Rotary-piston machines or engines
    • F01C1/30—Rotary-piston machines or engines having the characteristics covered by two or more groups F01C1/02, F01C1/08, F01C1/22, F01C1/24 or having the characteristics covered by one of these groups together with some other type of movement between co-operating members
    • F01C1/40—Rotary-piston machines or engines having the characteristics covered by two or more groups F01C1/02, F01C1/08, F01C1/22, F01C1/24 or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in group F01C1/08 or F01C1/22 and having a hinged member
    • F01C1/44—Rotary-piston machines or engines having the characteristics covered by two or more groups F01C1/02, F01C1/08, F01C1/22, F01C1/24 or having the characteristics covered by one of these groups together with some other type of movement between co-operating members having the movement defined in group F01C1/08 or F01C1/22 and having a hinged member with vanes hinged to the inner member

Definitions

  • This invention relates generally to a perfectly balanced, zero vibration, rotary device, and specifically to rotary engines, compressors, and pressure or vacuum pumps.
  • the patent USA 6,164,263 discloses a general rotary device called the Quasiturbine (Qurbine in short), which uses four pivoting blades and four rolling carriages to make a rotor of variable diamond-shaped geometry, the rotor mounted within a contoured housing wall formed along a Saint-Hilaire confinement profile shaped somewhat like a skating rink, the sides of the housing wall closed by lateral side covers. That Quasiturbine device uses four peripheral rolling carriages to hold the rotor in place within the housing wall and to transfer the pivoting blade radial load-pressure to the opposite part of the housing wall, in such a manner as to remove all load pressure from the center, making the Quasiturbine a center-free engine.
  • Quasiturbine Quadrbine in short
  • That Quasiturbine device uses four peripheral rolling carriages to hold the rotor in place within the housing wall and to transfer the pivoting blade radial load-pressure to the opposite part of the housing wall, in such a manner as to remove
  • USA 6,164,263 also discloses an effective but simple rotor-to-shaft differential linking mechanism and further provides a general method for the precise calculation of the Saint-Hilaire confinement profile family of curves for the housing wall.
  • the sealing at the pivot connection or apex between two adjacent blades must be done simultaneously with the contoured housing wall and also with the two lateral side covers which is a critical and difficult five-bodies sealing problem.
  • This sealing problem was satisfactorily solved in patent USA 6,164,263 through a male-female pivot design overlapped by the carriage. Results of theoretical simulation and some experimental data revealed exceptional engine characteristics for the Quasiturbine device, and in particular the possibility of a shorter pressure pulse with a linear ramp compression-pressure raising-falling slope near top dead center.
  • this invention is not an improvement of the Quasiturbine device in USA 6,164,263, but instead discloses a "central, annular, rotor support" applicable to all the family of Quasiturbine rotor arrangements for similar or other applications, where pivoting blades, wheel-bearings, and annular tracks are located within the rotor, while maintaining a center-free engine characteristic for direct power takeoff.
  • a central, annular, rotor support an embodiment of the Quasiturbine has been used which employs a rotor made up of four blades incorporating simple cylindrical pivoting joints between adjacent blades without rolling carriages.
  • the pivoting joint includes an underneath holding finger at die male end, and efficiently solves the five bodies sealing problem.
  • the device of the present invention includes wheel-bearings and lateral side covers carrying the annular tracks to take the pressure-load applied by the blades.
  • the invention also provides a precise parametric calculation method and criteria for unique selection of the appropriate Saint-Hilaire confinement profile so as to satisfy the optimum engine efficiency of the PV (Pressure- Volume) diagram; and this geometry permits the Quasiturbine to be scaled-up to provide power in excess of 100 MW and more.
  • This new rotor arrangement further allows the insertion of annular power sleeves each linking each pair of two opposite blades with or without centrifuge clutch weights, on the external surface of the sleeves.
  • a Modulated Inner Rotor Volume allows pumping-ventilating action and is particularly useful to cool the interior of the rotor in an internal combustion engine mode.
  • the MIRV is also generally applicable to the Quasiturbine design disclosed in patent USA 6,164,263.
  • differential washers make a large diameter tangential mechanical differential coupling with the power disk and shaft. Due to a shorter confinement time and a faster linear ramp compression-pressure raising-falling slope, a new combined Otto and Diesel QTIC-cycle mode is made possible, and is photo-detonation compatible.
  • the object of this invention is to provide a Quasiturbine central, annular, rotor support using pivoting blades, wheel-bearings, and lateral side covers carrying annular tracks (or alternatively the canceling out of the pressure-load in the fluid energy converter mode through the annular power sleeves) generally applicable to all the family of Quasiturbine rotor arrangements and other rotary engines, compressors or pumps, and particularly to an embodiment of the Quasiturbine which employs four blades incorporating simple cylindrical pivoting joints between adjacent blades without carriages, all this while maintaining a large empty area in the center of the engine for direct power takeoff and preserving most previously claimed Quasiturbine characteristics.
  • Another object of this invention is to provide a "Saint-Hilaire confinement profile calculation method" of the contoured housing wall appropriate to the chosen Quasiturbine design arrangement, minimizing the surface to volume ratio in the compression chambers and reducing the flow turbulence.
  • This calculation method includes criteria for engine optimum confinement profile selection from the family of curves to generate the contoured housing wall.
  • a further object of this invention is to provide a low friction, pivoting blade, joint design which is particularly suitable for non-metallic material like plastic, ceramic or glass, the joint allowing for maximum air-tightness; space for gate-type, near zero in-groove movement with single or multiple contour seals; higher maximum RPM; and suitable for very high-pressure 80 applications with the seals designed accordingly.
  • a compression ratio tuner can replace the sparkplug in high compression ratio photo-detonation combustion engine mode.
  • Another further object of this invention is to provide a Modulated Inner Rotor Volume (MIRV) producing annular pumping-ventilating action between the inner surfaces of the moving pivoting blades and the outer surfaces of the annular power sleeves, with or without centrifuge clutch weights.
  • the Modulated Inner Rotor Volume (MIRV) is particularly useful to cool the interior of the rotor in an internal combustion engine mode, while allowing for the insertion of the differential washers on the inner surface of the annular power sleeves, to be able to make a large diameter tangential mechanical differential coupling with the power disk 90 and shaft.
  • Yet another further object of this invention is to provide a new combined Otto and Diesel Quasiturbine operation in an Internal Combustion QTIC-cycle mode, this due to the possible shorter confinement time and the faster linear ramp compression-pressure raising-falling slope, which is photo detonation compatible.
  • the Quasiturbine rotor arrangement makes use of an appropriate contoured housing wall calculated to receive the present, pivoting blades, rotor geometry, with a set of contour and lateral seals (linear gate type and pellets) engineered for 100 the selected rotor arrangement.
  • FIG. 1 is a perspective exploded view of the Quasiturbine device with a contoured housing wall and the four interconnected pivoting blades shown in a square configuration.
  • FIG. 2 is a top view with the lateral side covers removed, the four interconnected pivoting blades shown in a diamond configuration.
  • FIG. 3 is a detail perspective exploded view of the Quasiturbine showing interior details, where the contoured housing wall and two of the pivoting blades have been removed for better viewing.
  • the USA 6,164,263 patent disclosed a Quasiturbine rotor arrangement using four rolling 120 carriages to take the pivoting blade pressure-load and transfer it to the opposite contoured housing wall.
  • the present invention discloses a Quasiturbine rotor arrangement without carriages, where the pressure-load on each pivoting blade is taken by its own set of wheelbearings located in a power transfer slot in the inner side of blade, the wheel-bearings rolling on annular tracks, one track attached to the central area of each lateral side cover.
  • This rotor supporting configuration can apply to all the Quasiturbine family of designs, and is here illustrated on a specific Quasiturbine embodiment without rolling carriages.
  • This Quasiturbine rotor arrangement reduces the number of components, reduces the friction surface, reduces the total wall surface in the compression chambers, and is particularly suitable for non- metallic pivoting blades, the blades being made instead from material such as plastic, ceramic 130 or glass. Furthermore, this rotor arrangement allows for single or multiple contour seals with a near zero in-groove movement, and eliminates the need of a cooling system for carriages.
  • This invention applies generally to rotary engines, compressors, or pressured or vacuum pumps.
  • the present Quasiturbine invention is generally referred on FIG. 1 as number 10, and comprises a stator casing 12- made of a contoured housing wall 14 and two lateral side covers 16, one on each side of the housing wall 14,, and a rotor 18 of four or more pivoting blades 20 confined within this casing.
  • Each pivoting blade 20 carries a power transfer slot 22 on its inner surface 24 in which wheel-bearings 26 are located.
  • the lateral side covers 16 each have 140 an annular track 28, not necessarily circular, on their inner surface 30 to support the wheelbearings 26 carried by the pivoting blades 20, the wheel-bearings rolling on the tracks.
  • Multiple notches 32 are provided on the external perimeter of the covers 16 where cooling fins 34 can be inserted.
  • Liquid cooling is also easily feasible.
  • Radial intake 36 and exhaust 38 ports are located in the housing wall 14 or axially (not shown) in the lateral side covers 16.
  • a check-valve port 40 can be located through each pivoting blade 20 to benefit from the centrifuge intake pressure.
  • a compression ratio tuner 42 can replace the sparkplug 44 at high compression ratio photo-detonation mode.
  • One end of each pivoting blade 20 carries a male connector 46 and the other end carries a 150 complementary female connector 48, the male and female connectors of adjacent blades connected to provide a low friction pivot joint 50 as shown in FIG. 2.
  • the cylindrical male connector 46 carries a contour seal groove 52 and has a rounded outer portion that acts as a guiding-rubbing pad 54 with the contoured housing wall 14, with provision for a hard metal or ceramic insert in that guiding-rubbing area.
  • the pivoting blades 20 also have a lateral pellet hole 56 in the male connector 46 at the joints 50, and lateral seal grooves 58 along their sides extending between the connectors 46 48.
  • the set of seals used in the pivoting blades is made up of contour seals 60; lateral arched side cover seals 62 (which can be made continuous when located in a groove within the lateral side covers 16), and small pellet seals 64 in the male connector 46 at the pivoting blade joint 50. All the seals have a back spring, and in 160 addition the contour seal 60 sits on a contour seal damper made of a rubber band lying in the bottom of its groove to help extend the seal life from hammering against the housing wall.
  • annular power sleeves 66, 68 are provided, as shown in FIG. 3, each linked to the axels 70 of the wheel-bearings 26 in two opposed pivoting blade power transfer slots 22 by opposed rings 72 on each sleeve.
  • the sleeves 66, 68 leave a large circular hole in the engine center for the shaft power disk, a direct power takeoff or other uses.
  • the annular power sleeves 66, 68 can carry their own set of lateral side cover seals (not shown) to insulate their inward central area from their outward area.
  • the inner surface 74 of the annular power sleeves 66, 68 carries several grooves 76 from which any mechanism enclosed by the sleeves can be 170 driven.
  • Centrifuge clutch weights 78 are located between the inner surface 24 of the pivoting blades 20 and the outer surface 80 of the annular power sleeves 66, 68, a clutch weight 78 located adjacent each side of each of the power transfer slots 22.
  • a tangential mechanical differential is located on the inner surface 74 of the annular power sleeves 66, 68, and is made of several (from two to twelve or more) differential washers 82 linking the annular power sleeves 66, 68 to the central power disk 84 and the shaft 86.
  • a calculation method for the stator Saint-Hilaire confinement profile of the contoured housing wall 14 is disclosed for the chosen Quasiturbine rotor arrangement, with a set of optimum engine contoured housing wall 14 selection criteria.
  • FIG. 1 shows the four interconnected pivoting blades 20 in a square configuration within the housing wall 14, guided by the solid guiding-rubbing pads 54 provided by the male connectors 46 at the joints 50 between adjacent blades.
  • the wheel-bearings 26 of the blades 20 roll on the annular tracks 26 carried by the lateral side covers 16.
  • the port locations 36, 38 shown are the ones used when the Quasiturbine is operated as a fluid energy converter or compressor.
  • the spark plug 44 is positioned as for the internal combustion mode.
  • the centrifuge weights 78 are not shown on FIG. 1.
  • FIG. 2 shows the four interconnected pivoting blades 20 in a diamond configuration.
  • FIG. 2 also shows details of the interconnecting pivot joint 50 including details of the male 46 and
  • FIG. 2 also shows the Modulated Inner Rotor Volumes (MIRV) 90.
  • MIRV Modulated Inner Rotor Volumes
  • Annular pumping action is provided by the varying size of the volumes 90, each located in between the inner surface 24 of the pivoting blades 20 and the outer surface 80 of the annular power sleeves 66, 68. It will be seen that the centrifuge clutch weights 78 are located within the volumes 90 and move along
  • FIG. 3 shows details of the Quasiturbine with the contoured housing wall 14 and two of the pivoting blades 20 removed. It also shows details of the centrifugal clutch weights 78, which weights could possibly pivot around the closest wheel-bearings, the annular power sleeves 66, 68 and the differential washers 82 making a large diameter tangential mechanical differential coupling with the power disk 84 and shaft 86.
  • the four pivoting blades 20 are attached to one another as a chain in forming the rotor 18 and show a variable diamond-shaped geometry while moving in a Saint-Hilaire-like confinement
  • the expansion or combustion chamber 92 is defined by the volume in-between the outer surface 94 of a pivoting blade 20 and the inner surface 96 of the contoured housing wall 14 and extends from one pivot joint contour seal 60 to the next. Referring to FIG. 2, as the rotor 18 turns, it does make minimum combustion chamber 92 volumes at the top and bottom (TDC), and maximum volumes at left and right (BTC). During one rotation, each pivoting blade 20 goes through four complete engine strokes, so that a total of sixteen strokes are completed in every rotation. Furthermore, as an expansion stroke starts from a horizontal pivoting blade 20 and ends when it gets vertical, the next following pivoting
  • the Quasiturbine is a quasi-continuous flow engine at intake and exhaust, both of which can be located either radially in the contoured housing wall 14 or axially in the lateral side covers 16.
  • Several removable intake and exhaust plugs 98 may be used to convert the two parallel compression and expansion circuits into a sole serial circuit.
  • the two quasi- independent circuits are used in parallel with all plugs removed, for operation as a two stroke internal combustion engine, fluid energy converter, compressor, vacuum pump and flow meter.
  • the two quasi-independent circuits are used in serial by plugging intermediate ports, to make a four stroke internal combustion engine as shown in the port arrangement of FIG. 2. Notice that the intake and exhaust ports have different locations for different applications and
  • the stator 12 and the lateral side covers 16 are centered on the engine rotor axis.
  • the lateral side covers 16 have annular tracks 28 receiving the wheel-bearings 26 carried by the blades 20, which tracks are not necessarily circular.
  • FIG. 1 shows a central hole 100 in the lateral side covers 16 that can be made large enough so that the power disk 84 and the differential washers 82 can be slide in-and-out without having to dismantle the engine.
  • a cap bearing- holder can be inserted in the large side cover hole 100.
  • Intake and exhaust ports 36, 38 are located either radially in the stator 12 or axially (not shown) in the lateral side covers 16.
  • the lateral side covers 16 carry a set of ventilation ports 102 for cooling the rotor 18.
  • a sparkplug 44 can be located at a variable
  • compression ratio tuner 42 250 angle on the top of the stator 12, and also at bottom (not shown) in the two stroke engine mode, and replaced, when in a very high compression ratio photo-detonation mode by a small threaded piston called a "compression ratio tuner" 42, which can be feedback controlled to optimize combustion chamber conditions for different fuels or running operation.
  • the surface of contact between the stator 12 and the lateral side covers 16 carry a fix gasket 104.
  • the annular tracks 28 are circular only if the wheel-bearings 26 are on the line joining the axis of two successive blade pivots.
  • the central opening in the rotor 18 could be made smaller or larger by moving the wheel-bearings 26 towards or away of the outer surface 94 of the pivoting blades 20, out of alignment with pivot joints 50, but then the annular track 28 in the 260 side covers 16 will no longer be a perfect circle, but be elliptical-like in shape.
  • the wheelbearings 26 are located on each side of the pivoting blade 20 and carry roller or needle bearings 106.
  • the blade rubbing pads 54 located in the vicinity of the contour seals 60, can be formed by the pivoting blade male connector 46 itself, or it can be formed by a little insert (not shown) containing the contour seal 60 so as to prevent the hardening of the whole pivoting blade 20. In this arrangement, hard inserts can, alternatively, be used to make the complete pivoting blade joint 50. Pressure in the combustion chamber 92 does not generate a significant torque around the wheel-bearings axles 70 carried by the pivoting blades 20 and consequently the combustion chamber pressure has little effect on the rubbing pad 54 pressure against the housing contour wall 14. The rubbing pad pressure is essentially due to the small 270 rotor deformation, which is quite independent of the pressure-load.
  • the combustion chamber 92 can be enlarged by cutting the pivoting blade 20 and the very high compression ratio photo-detonation mode makes use of a "compression ratio tuner" 42 instead of a sparkplug 44.
  • the manufacturing method allows for the entire stator and rotor to be made out of a cylindrical disk, the housing contour wall being formed in the interior of the disk and the pivoting blades being formed in the outer periphery.
  • the contoured housing wall 14 can be shaped by precision forging and the pivoting blades 20 can be metal cast or metal powder pressed. Similar techniques and molds will also work for plastic or ceramic.
  • the pivoting blades 20 can be made all alike with a male connector 46 and a female connector 48 to form the pivot joints 50. Alternatively, half the blades 20 can have two female connectors and the other half two male connectors. A good "five-bodies" sealed joint design is quite important and must satisfy an extensive force vector analysis.
  • the blade pivot joint 50 of the present invention must be strong enough to take some load-pressure and all the tangential push-and-pull forces of the torque, while allowing independent low-friction rotational movement of the two connected pivoting blades 20. Simultaneously, the joint must be leak proof within itself, the contoured housing wall 14 and with the two lateral side covers 16. This pivot joint 50 has space, if needed, to enclose a bearing to further reduce the required rotor energy deformation. Extensive research has led to a double chisel joint pivot concept
  • the male connector 46 has two different radii 106, 108 on its main body 110 and a finger 112 spaced from the main body 110 for use in holding the pivoting blades together.
  • the female connector 48 has also two different radii 114, 116 located on an extending arm 118, the radii 114 116 cooperating with the radii 106, 108 on the male connector 46 when the arm 118 is mounted between the main body 110 and the finger 1 12, and preventing the connectors 46, 48 from opening up.
  • the joints 50 get tighter and tighter, and still more leak proof.
  • contour seals 60 are single or multi-pieces drawer type seals located in the axial direction along the pivoting blade male connector 46 and have a near zero in-groove displacement
  • Consecutive multiple pieces contour seals can be used to prevent two successive chambers to be in contact with one another at the time the joint 50 passes in front of the ports 36, 38. This multi-seals configuration would also insure that at least one of the seals is at all times moving inward in its groove, while the others may be moving outward.
  • the contour seal sits on a contour seal damper made of a rubber band lying in the bottom of its groove 52 or between the springs to help extend the seal life from hammering against the housing contour wall.
  • the pivoting blades 20 seal with the lateral side covers 16, on each side, by a linear or slightly curved gate-type lateral seal 62 and. a pellet type seal 64 at the end of the male
  • the seal grooves are at different depth levels, so that the pressure gas behind the seals cannot propagate.
  • a non-mandatory linear intra-pivot seal can be incorporated in the female connector 48 from one lateral side cover to the other, if required.
  • the pivoting blades 20 are made of smooth or fragile material like plastic, ceramic or glass, there is room for a metal insert to be placed at each pivoting blade joint 50 for proper movement and friction control.
  • the pivoting blade lateral seal grooves 58 are easy to make on a lathe.
  • This arched seal positioned near the edge of the outer surface of the pivoting blade 20 traps a minimum volume in combustion mode, and being at the far reach of the rotor, it keeps the high-pressure in the outer area of the covers 16, which reduces the total pressure- force on them.
  • Quasiturbines may benefit in having some type of centrifuge clutches.
  • the Quasiturbine geometry permits it to have the centrifuge clutch weights 78 within the rotor 18, each weight located between the wheel-bearings 26 and a blade end, in-between the pivoting 330 blades 20 and the outer surface 80 of the annular power sleeves 66, 68 within the volumes 90 well ventilated by the Modulated Inner Rotor Volume (MIRV) annular central pump effect.
  • MIRV Modulated Inner Rotor Volume
  • the centrifuge clutch weights 78 can pivot around the wheel-bearings axis 70. As with any centrifuge clutches, the weights 78 will contribute slightly to increase the rotor inertia.
  • the centrifuge clutch weights 78 can be used to drive clutch friction pads (not shown) located either on the outer surface 80 of the annular power sleeves 66, 68; or within the power disk 84 where the angular rotational speed is uniform; or externally to the Quasiturbine. Notice that with such a centrifuge clutch in place, a conventional starter must be used to drive the Quasiturbine rotor and not the power shaft 86, unless some kind of clutch-locking is provided.
  • each pair of opposed wheel-bearings 26 does not rotate at constant angular velocity, two distinct but identical central annular power sleeves 66, 68 are used side-by-side along the engine axis as shown on FIG. 3, each one linking two different opposite wheel-bearings axis 70 by opposed rings 72.
  • Each annular power sleeve 66, 68 is in the form of an annular ring with the two outer opposed rings 72 on the outer surface 80 taking the torque from the opposite pivoting blades 20 via the wheel-bearings axis 70.
  • the maximum relative angular variation of the annular power sleeves 66, 68 is 6.35 degrees ahead and behind their respective average angular position, for a maximum differential angle of 12.7 degrees, which produces a +/- 15 degrees oscillation of the differential washers 82.
  • the annular power sleeves 66, 68 can take and cancel out the mutual pressure-load of the two opposite pivoting blades 20, possibly suppressing in this case the need to use the wheel-bearings 26 and the lateral side cover annular tracks 28.
  • the shaft power disk 84 or the large diameter shaft have multiple radial extending disk pins 120 on which sits the set of differential washers 82.
  • Each washer 82 has two opposite radially extending washer pins 118, each one fitting into its own internal groove 76 on power sleeve 66, 68 respectively.
  • the numbers of differential washers 82, the number of power disk pins 370 120 and the corresponding grooves 76 in the power sleeves 66, 68 can vary from two to twelve or more.
  • the differential washers 82 angular oscillation around the disk pin 120 is +/- 15 degrees, which requires a little play between the power disk 84 and the internal surface 74 of the annular power sleeves 66, 68 to account for the washer being slightly off shaft axis during oscillation.
  • the differential washer 82 can sit perfectly on it if also shaped accordingly and furthermore, since the washer pins 118 on the differential washers 82 need to be cylindrical only on a 15 degree arc, the two pins shape can be elongated toward the washer center for better strength.
  • Each radially extending disk pin 120 can be part of the differential washer itself, and can carry a bearing.
  • the power disk can hold a conventional feed-through shaft, or can carry, or be part of, a very large diameter thin wall tube shaft.
  • This tube shaft may enclose a propeller screw for a water jet or pumping, or an electrical generator or else. It can also carry an axial thrust bearing at least at one end, and an engine crank starting device at either ends.
  • Each Modulated Inner Rotor Volume (MIRV) 90 is generally triangular in shape, each volume formed by the inner surfaces 24 of adjacent pivoting blades 20 extending from their common pivot 50 to their respective transfer slots 22 and the outer surface 80 of the annular power sleeves 66, 68.
  • the volumes 90 vary as the rotor 18 rotates.
  • the volumes 90 are forty five degrees out of phase with the outer combustion chambers 92, and make an integrated 400 efficient annular pump or ventilating device, displacing a total of 8 times its volume in every rotation.
  • Ventilating ports 102 are located in the lateral side covers 16 near the external surface of the annular track 28 in the vicinity of the wheel-bearings 26 when the rotor is in its maximum diamond length configuration.
  • the geometry permits pulsing ventilation if all the ventilating ports, 102 in the lateral side covers 16 are open, or two different one-way ventilation circuits in the same or opposed axial direction, if proper ventilation ports 102 are selected on both sides of the engine.
  • the side covers 16 have only a crossed- symmetrical-through-center set of ventilation ports 102, as shown in FIG. 1, entrances occur only from one engine side and exits to the other, while consecutive ports on the same side covers would make the entrances and exits on the same engine side. Using a radial check
  • the Modulated Inner Rotor Volumes (MIRV) 90 forms a well-integrated annular pump and can be used as such in many applications, or to venti late and cool the rotor in engine mode. They can also form a second stage low flow high-pressure device when in compressor mode, or to provide the pressure fluctuation required by a standard carburetor diaphragm fuel pump. Furthermore, a very high-pressure can be obtained from the scissor-pivoting-blade effect at the joint 50 when the guiding male finger 112 moves in and out of position. Similarly, other piston-like devices can be incorporated in this scissor
  • Modulated Inner Rotor Volumes (MIRV) 90 can also be made to work as an Inward Rotor Engine Quasiturbine (IREQ), while the Quasiturbine outward rotor is used as a compressor, a pump, or for other applications.
  • IREQ Inward Rotor Engine Quasiturbine
  • a new Quasiturbine Internal Combustion QTIC-cycle mode is made possible, combining Otto, Diesel and eventually photo-detonation mode.
  • Otto engine cycle intakes and compresses a sub-atmospheric manifold pressure air-mixture for uniform combustion, while the Diesel engine cycle always intakes and compresses atmospheric pressure air-only, which gives a non-uniform injected fuel combustion. Due to the possibility of a shorter confinement time
  • the new Quasiturbine Internal Combustion QTIC-cycle mode consists of intaking, at atmospheric pressure, a continuous air-fuel mixture for uniform combustion, thereby combining Otto and Diesel modes.
  • This mode is not possible with a piston engine, because the sine-wave shape of the maximum compression ratio poorly defines the top dead center by making an unnecessary long confinement time, consequently requiring a reliable external trigger source such as a sparkplug or a fuel injector.
  • the Quasiturbine Internal Combustion QTIC-cycle can work at a moderate compression ratio with a sparkplug 44, or without it at a very high compression ratio for almost any fuel, the photo-detonation being auto-synchronized by its very short linear ramp pressure pulse tip.
  • a regular piston cannot stand photo-detonation because it
  • This QTIC-cycle mode only requires a non- synchronized fuel pulverization and vaporization in the Quasiturbine atmospheric intake continuous airflow, suppressing the need of conventional vacuum carburetor or synchronized fuel injector and sparkplug timing in photo-detonation mode, and allows for a much higher RPM than the conventional mode due to continuous intake flow without valve obstruction and faster photo-detonation chemistry combustion.
  • the photo-detonation being a fast radiative
  • the Quasiturbine can provide continuous combustion by using an ignition transfer slot-cavity 88 cut into the housing wall 14 for flame transfer from one chamber to the following one.
  • This ignition flame transfer slot-cavity 88 also allows the injection of high-pressure hot burning gas into the following, ready-to-fire, chamber, producing a dynamically enhanced compression ratio, since near top dead center, a little volume change in the combustion chamber makes a large
  • a compression ratio tuner 42 made of a simple small threaded piston in a tube is used in place of the sparkplug 44, and allows compression ratio fine-tuning as needed, and can be dynamically feedback controlled.
  • the Quasiturbine can be generally used as an engine, compressor or pump, and sometimes in a dual mode. To name a few applications, it is suitable for small or very large units in steam, pneumatic and hydraulic mode (including use in reversible waterfall hydro-electric stations), and in a combined engine-turbo-pump mode where one intake port and its corresponding exhaust port are used in a compressed fluid energy converter engine mode while the other intake and exhaust ports can be used as a positive or vacuum pump or compressor.
  • Quasiturbine can be used as an internal combustion engine in Otto or Diesel in two or four stroke mode.
  • the Quasiturbine engines in photo-detonation mode with a high compression ratio (20 to 30: 1) are particularly suitable for natural gas and other fuels that are hard to burn to environmental standards like jet fuel or low specific energy gases, in which case the fuel is simply mixed to the atmospheric pressure intake without any synchronization means. It can be further used in a continuous combustion mode with a flame transfer cavity 88 at the forward contour seal 60 near top dead center.
  • the Quasiturbine can also be used as an engine to drive a turbo-jet engine-compressor, allowing the suppression of the hot- power-turbine and its associated limitations in temperature, efficiency and speed.
  • a cold Quasiturbine can act as compressor while a second hot Quasiturbine possibly on the same shaft can produce power in a pneumatic mode, in order to make a jet engine without jet (no gas kinetic energy intermediary transformation is involved, which makes it almost insensitive to dust particles).
  • the second hot Quasiturbine can be
  • the empty center of the Quasiturbine is particularly suitable to locate a propeller therein and makes a self-integrated marine jet propulsion system, or a liquid or gas turbine-like pump, where the complete engine can be submerged. This empty center is also suitable to locate electrical components for a lightweight compact electrical generator or electrical motor for a compressor or pump.
  • the contoured housing wall 14 is derivate from an empirical generating equation of the variable diamond geometry of the rotor for all rotation angles.
  • the housing wall 14 is not unique but part of a family of curves, and selection must be done according to an engine efficiency criteria. Before calculating the Saint-Hilaire confinement profile for the housing wall 14, one must calculate the blade pivots 44 profile curve. Since this profile does require only symmetry across the central engine axis, any initial arbitrary pivot movement from 0 to 45 degrees (or 1/8 of a turn in a non-orthogonal axis situation) does determine the complete pivot point curve.
  • This empirical 0 to 45 degree curve must meet three constraints: be parallel ( to the y- axis at 0 degree angle x- crossing; be matching at the diamond-square configuration corners; and furthermore, the slope at those corners must be continuous.
  • Rx the pivot profile radius on the x- axis
  • Ry the pivot profile radius on y- axis
  • R45 the pivot profile radius at 45 degrees where the rotor is in square configuration
  • the modified M( ⁇ ) linear radius variation between 0 and 45 degree could be empirically of the form (pivot profile, not the actual housing contour wall 14):
  • the pivot profile in the 45 (R45) to 90 (Ry) degrees interval is simply given by the Pythagoras diamond-lozenge formula.
  • the two constants A and P provide a parametric adjustment of the radius variation where +/- A controls the amplitude and affects mostly the axis areas, and +/- P controls the angular maximum variation position and affects the wideness of the overlap zone near 45 degree from the x- axis.
  • This empirical representation has been found adequate to explore most of the family of pivot profiles of interest, including the very high eccentricities leading to two lobes confinement profiles.
  • the housing wall 14 presented in Figs. 1 and 2 is obtained from the pivot concave eccentricity limit profile curve, enlarge by the rubbing pad radius 106 all around.
  • the final expansion volume of the engine chamber must be equal to the volume generated by the variable surface of tangential push, which is proportional to the radius difference of two successive contour seal 60 positions during rotation.
  • increasing the radius of the joint-rubbing pad centered on each pivot tends to attenuate the high curvature in the corners of the Saint-Hilaire "skating rink" confinement profile, but contributes to increase the maximum torque, with no net penalty on the specific power and weight density of the Quasiturbine, without however achieving as stiff a linear ramp pressure that the rolling carriages design permits.
  • the rotor can be made of strong
  • the pivot pad radius 106 can be made relatively small and lead to the selected housing wall 14 shown, which is a near optimum Quasiturbine specific power and weight density. It is hard to notice by looking at the housing wall 14 that the radius of curvature fluctuates along the profile. Inside the rotor 18, one notices a generally triangular Modulated Inner Rotor Volume (MIRV) 90 in-between the inner surface 24 of the pivoting blades 20 and the outer surface 80 of the annular power sleeves 66, 68 at every rotor pivot 50 location.
  • MIRV Modulated Inner Rotor Volume
  • Changing the shape of the rotor 18 for the purpose of producing internal central volume variation for an annular pumping application would need no rotor rotation, but only a steady on-site "oscillating rotor deformation", possibly driven by a rotating external confinement profile, or by a x- or y- axes movement.
  • the rotor deformation could also be
  • Modulated Inner Rotor Volumes MIRV
  • IREQ Internal Rotor Engine Quasiturbine
  • This calculation method does not require profile symmetry through x- and y- axes, but only through the central point, which means that the axes may not be orthogonal with this same calculation method, in which case the confinement profile could be asymmetrical, producing an interesting Quasiturbine with different intake and exhaust volume characteristics, and with only minor rotor change.
  • QUASITURBINE QURBINE

Abstract

L'invention concerne une Quasiturbine (abrégé en Qurbine) qui fait intervenir un dispositif de rotor supporté sur sa périphérie par quatre chariots roulants, ces chariots supportant la charge de pressurisation de la lame pivotante des lames qui forment le rotor et transférant la charge sur la paroi profilée opposée du logement. L'invention décrit une embase de rotor centrale annulaire pour la configuration géométrique définie par les lames pivotantes et les roulements de roues associés, tout en conservant la caractéristique importante d'un moteur exempt de centre. La charge de pressurisation sur chaque lame pivotante est soit supportée par l'ensemble de roulements de roues respectif de chaque lame pivotante roulant sur des pistes annulaires fixées sur la zone centrale de couvercles latéraux faisant partie du carter, soit neutralisée dans un mode de conversion de l'énergie du fluide pressurisé symétriquement sous l'action centrale de retenue de manchons de puissance annulaires. Cette embase de rotor centrale annulaire peut généralement être appliquée à toute la famille des dispositifs de rotor Quasiturbine, et particulièrement au cas limite considéré ici, dans lequel la conception antérieure de chariot est remplacée par une lame pivotante cylindrique développée dans le présent brevet, et pour lequel une solution efficace est apportée au problème du scellement du moteur rotatif à cinq corps.
PCT/CA2003/000176 2003-02-10 2003-02-10 Moteur rotatif WO2004070169A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
PCT/CA2003/000176 WO2004070169A1 (fr) 2003-02-10 2003-02-10 Moteur rotatif
AU2003303875A AU2003303875B2 (en) 2003-02-10 2003-02-10 Rotary engine
CA002511267A CA2511267C (fr) 2003-02-10 2003-02-10 Moteur rotatif avec lames pivotantes
JP2004567670A JP2006517273A (ja) 2003-02-10 2003-02-10 （翻訳文に記載なし）
CN03826218A CN100587230C (zh) 2003-02-10 2003-02-10 旋转装置
MXPA05009639A MXPA05009639A (es) 2003-02-10 2003-02-10 Motor rotativo.
EP03815671A EP1592866A1 (fr) 2003-02-10 2003-02-10 Moteur rotatif

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CA2003/000176 WO2004070169A1 (fr) 2003-02-10 2003-02-10 Moteur rotatif

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WO2004070169A1 true WO2004070169A1 (fr) 2004-08-19

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EP (1) EP1592866A1 (fr)
JP (1) JP2006517273A (fr)
CN (1) CN100587230C (fr)
AU (1) AU2003303875B2 (fr)
CA (1) CA2511267C (fr)
MX (1) MXPA05009639A (fr)
WO (1) WO2004070169A1 (fr)

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WO2010018325A2 (fr) * 2008-08-14 2010-02-18 Roustaei Alex Hr Source d'alimentation optimisee et unite de stockage d'assistance en puissance cryogenique ou nanohydrures utilisant le photovoltaique pour des systemes de production de l'energie a la demande
WO2010031927A1 (fr) 2008-09-22 2010-03-25 Vincent Genissieux Machine rotative a losange deformable multifonctions
WO2010040919A1 (fr) * 2008-10-10 2010-04-15 Vincent Genissieux Machine rotative a losange deformable a dispositif electromagnetique
FR2938291A1 (fr) * 2008-11-12 2010-05-14 Vincent Genissieux Machine rotative a losange deformable comportant un mecanisme de transmission perfectionne.
FR2950926A1 (fr) * 2009-10-05 2011-04-08 Pk Enr Moteur a pistons rotatifs
US9127563B2 (en) 2011-04-05 2015-09-08 General Electric Company Locking device arrangement for a rotating bladed stage
US9599252B2 (en) 2012-02-16 2017-03-21 Politecnico Di Milano Energy recovering flow control valve
US9926927B2 (en) 2011-10-14 2018-03-27 Gullivert Technologies Inc. Belt and support for a rotor mechanism in a rotary apparatus and rotary apparatus comprising same
CN108571397A (zh) * 2017-03-11 2018-09-25 王闯业 一种空气能奎西结构转子式热气发动机
WO2020113109A1 (fr) * 2018-11-27 2020-06-04 Lumenium Llc Moteur rotatif à transfert de puissance par rouleau à arc de recirculation
CN113530669A (zh) * 2021-07-21 2021-10-22 北京工业大学 一种用于转子发动机的悬臂式径向密封装置
CN117145704A (zh) * 2023-10-27 2023-12-01 南通启电新能源科技有限公司 一种自适应转速调节的海上风力发电机
US11920476B2 (en) 2015-04-13 2024-03-05 Lumenium Llc Rotary machine
US11927128B2 (en) 2020-05-15 2024-03-12 Lumenium Llc Rotary machine with hub driven transmission articulating a four bar linkage

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US8037863B2 (en) * 2007-03-05 2011-10-18 Hartfield Jr Roy J Positive displacement rotary vane engine
BRPI0704879B1 (pt) * 2007-10-17 2012-10-16 motor de combustão interna, do tipo motor rotativo, provido de diferenciada concepção, durabilidade e desempenho, aplicado em toda sorte de veìculos automotores ou equipamentos industriais.
CN101994566B (zh) * 2009-08-11 2012-12-05 天津职业技术师范大学 双叶片式转子发动机
KR101155036B1 (ko) 2011-11-25 2012-06-11 김종문 회전클랩 흡압장치
KR101155035B1 (ko) * 2011-11-14 2012-06-11 김종문 회전클랩 흡압장치
CN102393230B (zh) * 2011-10-24 2012-10-03 浙江沁园水处理科技有限公司 一种自供电带电子显示的转子流量计装置
CN103133131A (zh) * 2011-11-25 2013-06-05 罗帅 转子发动机的半封闭气缸的结构方法
CN103628977B (zh) * 2013-12-12 2016-01-20 曹明建 一种双菱转子发动机
CN104314812B (zh) * 2014-10-11 2016-04-27 山东润国机电设备股份有限公司 陶瓷全无油空气压缩机
IT201600123578A1 (it) * 2016-12-06 2018-06-06 Ruggero Libralato Motore a vapore, con statore e pistone a doppio centro di rotazione

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US6164263A (en) * 1997-12-02 2000-12-26 Saint-Hilaire; Roxan Quasiturbine zero vibration-continuous combustion rotary engine compressor or pump
EP1092838A2 (fr) * 1999-09-08 2001-04-18 John Alejandro Sanchez Talero Moteur à combustion interne rotatif
US20020029756A1 (en) * 1999-01-14 2002-03-14 Herbert Huttlin Oscillating-piston engine

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US4181481A (en) * 1976-12-15 1980-01-01 Alfred Jordan Rotary internal combustion engine
US6164263A (en) * 1997-12-02 2000-12-26 Saint-Hilaire; Roxan Quasiturbine zero vibration-continuous combustion rotary engine compressor or pump
US20020029756A1 (en) * 1999-01-14 2002-03-14 Herbert Huttlin Oscillating-piston engine
EP1092838A2 (fr) * 1999-09-08 2001-04-18 John Alejandro Sanchez Talero Moteur à combustion interne rotatif

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010018325A3 (fr) * 2008-08-14 2010-06-10 Roustaei Alex Hr Source d'alimentation optimisee et unite de stockage d'assistance en puissance cryogenique ou nanohydrures utilisant le photovoltaique pour des systemes de production de l'energie a la demande
WO2010018325A2 (fr) * 2008-08-14 2010-02-18 Roustaei Alex Hr Source d'alimentation optimisee et unite de stockage d'assistance en puissance cryogenique ou nanohydrures utilisant le photovoltaique pour des systemes de production de l'energie a la demande
US9523276B2 (en) 2008-09-22 2016-12-20 Vincent Genissieux Multifunction rotary machine with deformable rhomb
EP3045656A1 (fr) 2008-09-22 2016-07-20 Vincent Genissieux Machine rotative a losange deformable multifonctions
WO2010031927A1 (fr) 2008-09-22 2010-03-25 Vincent Genissieux Machine rotative a losange deformable multifonctions
WO2010040919A1 (fr) * 2008-10-10 2010-04-15 Vincent Genissieux Machine rotative a losange deformable a dispositif electromagnetique
FR2937093A1 (fr) * 2008-10-10 2010-04-16 Vincent Genissieux Machine rotative a losange deformable a dispositif electromagnetique
WO2010055223A1 (fr) * 2008-11-12 2010-05-20 Vincent Genissieux Machine rotative a losange deformable comportant un mecanisme de transmission perfectionne
FR2938291A1 (fr) * 2008-11-12 2010-05-14 Vincent Genissieux Machine rotative a losange deformable comportant un mecanisme de transmission perfectionne.
US8951028B2 (en) 2008-11-12 2015-02-10 Vincent Genissieux Rotary machine of the deformable rhombus type comprising an improved transmission mechanism
WO2011042648A3 (fr) * 2009-10-05 2012-04-05 Pk-Enr Moteur à pistons rotatifs
FR2950926A1 (fr) * 2009-10-05 2011-04-08 Pk Enr Moteur a pistons rotatifs
US9127563B2 (en) 2011-04-05 2015-09-08 General Electric Company Locking device arrangement for a rotating bladed stage
US9926927B2 (en) 2011-10-14 2018-03-27 Gullivert Technologies Inc. Belt and support for a rotor mechanism in a rotary apparatus and rotary apparatus comprising same
US9599252B2 (en) 2012-02-16 2017-03-21 Politecnico Di Milano Energy recovering flow control valve
US11920476B2 (en) 2015-04-13 2024-03-05 Lumenium Llc Rotary machine
CN108571397A (zh) * 2017-03-11 2018-09-25 王闯业 一种空气能奎西结构转子式热气发动机
WO2020113109A1 (fr) * 2018-11-27 2020-06-04 Lumenium Llc Moteur rotatif à transfert de puissance par rouleau à arc de recirculation
US11725515B2 (en) 2018-11-27 2023-08-15 Lumenium Llc Rotary engine with recirculating arc roller power transfer
US11927128B2 (en) 2020-05-15 2024-03-12 Lumenium Llc Rotary machine with hub driven transmission articulating a four bar linkage
CN113530669A (zh) * 2021-07-21 2021-10-22 北京工业大学 一种用于转子发动机的悬臂式径向密封装置
CN113530669B (zh) * 2021-07-21 2022-07-05 北京工业大学 一种用于转子发动机的悬臂式径向密封装置
CN117145704B (zh) * 2023-10-27 2023-12-26 南通启电新能源科技有限公司 一种自适应转速调节的海上风力发电机
CN117145704A (zh) * 2023-10-27 2023-12-01 南通启电新能源科技有限公司 一种自适应转速调节的海上风力发电机

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AU2003303875B2 (en) 2007-04-19
MXPA05009639A (es) 2006-02-08
CA2511267A1 (fr) 2004-08-19
CA2511267C (fr) 2008-07-08
CN100587230C (zh) 2010-02-03
AU2003303875A1 (en) 2004-08-30
EP1592866A1 (fr) 2005-11-09
JP2006517273A (ja) 2006-07-20
CN1759230A (zh) 2006-04-12

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