EP4018098A1 - Systèmes de propulsion et poussée-portance améliorées - Google Patents

Systèmes de propulsion et poussée-portance améliorées

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Publication number
EP4018098A1
EP4018098A1 EP20855060.8A EP20855060A EP4018098A1 EP 4018098 A1 EP4018098 A1 EP 4018098A1 EP 20855060 A EP20855060 A EP 20855060A EP 4018098 A1 EP4018098 A1 EP 4018098A1
Authority
EP
European Patent Office
Prior art keywords
duct
outlet
inlet
stream
propeller
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
Application number
EP20855060.8A
Other languages
German (de)
English (en)
Other versions
EP4018098A4 (fr
Inventor
Mark Holtzapple
Jeff BREEDLOVE
Scott BRAUER
Michael Van Steenburg
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority claimed from PCT/US2020/046716 external-priority patent/WO2021034783A1/fr
Publication of EP4018098A1 publication Critical patent/EP4018098A1/fr
Publication of EP4018098A4 publication Critical patent/EP4018098A4/fr
Pending legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H11/00—Marine propulsion by water jets
    • B63H11/02—Marine propulsion by water jets the propulsive medium being ambient water
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B64C39/026—Aircraft not otherwise provided for characterised by special use for use as personal propulsion unit

Definitions

  • TECHNICAL FIELD [002] Aspects of the present disclosure relate to vehicles and, in particular, to an enhanced-thrust lift and propulsion system.
  • BACKGROUND [003] Propellers are often used to provide motive propulsion for vehicles moving through fluids, such as propellers used to propel boats over the water, or those used to propel airplanes through the air, or those used to lift helicopters into the air.
  • the performance of propellers is often assessed using Actuator Disc Theory, which is also commonly known as Momentum Theory.
  • actuator disc theory is a mathematical model in which the propeller is modeled as an infinitely thin disc that overcomes a pressure difference across the two disc faces and induces a constant fluid velocity perpendicular to the disc faces.
  • a propulsion system includes a duct and a fluid flow generator.
  • the duct has an elongated cavity with an inlet portion and an outlet portion.
  • the fluid flow generator is disposed in the duct.
  • the fluid flow generator is configured to receive a fluid to generate an inlet stream through the inlet portion and generate an outlet stream through the outlet portion.
  • the outlet stream is configured to generate thrust for a vehicle on which the fluid flow generator and the duct are mounted, and at least one of the inlet portion or the outlet portion is bent in a circular shape to alter a direction of a corresponding either one of the input stream or the output stream.
  • Figure 1 illustrates an example Actuator Disc Theory model involving a linearly oriented input flow and outlet flow according to one embodiment of the present disclosure.
  • Figure 2 illustrates another example Actuator Disc Theory model involving multiple actuator discs that increase the pressure in a duct having a 90-degree radial bend according to one embodiment of the present disclosure.
  • Figure 3 illustrates another example Actuator Disc Theory model involving multiple actuator discs that increase the pressure in a duct having a 180-degree radial bend according to one embodiment of the present disclosure.
  • Figure 4 illustrates another example Actuator Disc Theory model involving an actuator disc that increases the pressure in a duct having a 180-degree radial bend, while having a varied fan position according to one embodiment of the present disclosure.
  • Figure 5 illustrates another embodiment of an Actuator Disc Theory model involving an actuator disc located in a 180-degree duct according to one embodiment of the present disclosure.
  • Figures 6A, 6B, and 6C show the two-dimensional (x, y) flow fields determined by computational fluid dynamics (CFD) analysis for a simulated circular-profile 180-degree duct.
  • CFD computational fluid dynamics
  • Figure 7 shows the two-dimensional (x, y) flow fields determined by computational fluid dynamics (CFD) analysis for a low-profile 180-degree duct.
  • Figure 8 report the upward thrust (N) per meter of depth in the z direction.
  • Figures 9a, 9b, 10a, and 10b show the flow fields and pressure fields, respectively, for circular and low-profile ducts in open space.
  • Figures 11a and 11b illustrate cross-sectional views of example propulsion systems incorporating linear circular ducting according to one embodiment of the present disclosure.
  • Figures 12a and 12b illustrate example fan arrangements that that may be used to blow air through the duct of Figures 11a and 11b according to embodiments of the present disclosure.
  • Figures 13a and 13b illustrate an example flying car according to one embodiment of the present disclosure.
  • Figure 14a and 14b illustrate cross-sectional views of example propulsion devices incorporating linear low-profile ducting according to one embodiment of the present disclosure.
  • Figures 15a and 15b illustrate example vertical-lift flying motorcycles with low- profile ducts with unequally sized inlet and outlet areas according to one embodiment of the present disclosure.
  • Figures 16a and 16b illustrate specific fuel consumption rates at various output powers of gas engines according to one embodiment of the present disclosure.
  • Figure 17 illustrates one embodiment of a propulsion device having a duct with a short, straight outlet portion.
  • Figure 18 illustrates another embodiment of a propulsion device having a duct with a long, straight outlet portion and an external turning vane at the inlet portion.
  • Figure 19 illustrates another embodiment of a propulsion device having a duct with external turning vanes configured at the bottom end of the outlet duct portion of the duct.
  • Figure 20 illustrates another embodiment of a propulsion device having a duct with an extra-long, straight outlet portion.
  • Figure 21 illustrates another embodiment of a propulsion device having a duct with an extra-long, straight outlet portion and a restricted outlet.
  • Figure 22 illustrates another embodiment of a propulsion device having a duct with an extra-long, straight outlet portion and a flared outlet.
  • Figure 23 illustrates an example squirrel cage propeller assembly that may be implemented with the propulsion system according to one embodiment of the present disclosure.
  • Figure 24a and 24b illustrate an example squirrel cage propeller that may be implemented with the flying car according to one embodiment of the present disclosure
  • Figure 25a illustrates an external view of flying car with no inlet ducts.
  • Figure 25b illustrates an external view of a flying car with inlet ducts.
  • Figures 26a, 26b, and 26c illustrates example various propeller types that may be implemented with a circular duct according to embodiments of the present disclosure.
  • Figure 27 illustrates an example turbo propeller as shown and described with reference to Figure 26c.
  • Figure 28 illustrates multiple clustered circular ducts that combine their thrust to increase lift capability.
  • Figure 29 illustrates shows an example hybrid lifting system that employs the Coanda Effect to provide additional lift.
  • Figure 30 illustrates a schematic diagram of a conventional axial jet engine.
  • Figure 31 illustrates a schematic of a radial jet engine.
  • Figure 32 illustrates a reverse-flow jet engine.
  • Figure 33 shows the flow around a conventional torpedo.
  • Figures 34a through 34d show various options for torpedoes with axial propellers.
  • Figures 35a through 35e illustrate several embodiments of squirrel-cage propellers that may be used with a torpedo according to embodiments of the present disclosure.
  • Figure 36a through 36ed illustrate other embodiments of the squirrel-cage propeller, which are similar to the embodiments of Figures 35a through 35e, except that turning vanes are employed.
  • Figure 37a through 37e illustrate other embodiments of the squirrel-cage propeller, which are similar to the embodiments of Figures 36a through 36e except that a reduction nozzle is employed at the outlet.
  • Figures 38a and 38b are cut-away views showing the interior and exterior cone of a turbo propeller.
  • Figure 39 illustrates a jet boat in which the propeller is located in the interior of the boat.
  • Figure 40a and 40b illustrate various bottom and frontal views of a traditional monohull boat hull, a catamaran boat hull, and a Small Waterplane Area Twin Hull (SWATH) hull.
  • Figures 41a to 41d show the submerged portion of SWATH boat.
  • Figure 42a and 42b illustrate bottom and side views, respectively, of a monohull boat in “travel mode” meaning it is traveling with a significant forward velocity.
  • Figure 43a and 43b illustrate bottom and side views, respectively, showing the monohull boat in “thrust mode” meaning it is traveling with a nearly zero velocity, but has tremendous thrust.
  • Figure 44 is a schematic diagram illustrating an example jet pack according to one embodiment of the present disclosure.
  • Figure 45 illustrates a schematic diagram of another example jet pack according to one embodiment of the present disclosure.
  • Figure 46 illustrates a schematic diagram of another example jet pack according to one embodiment of the present disclosure.
  • Figure 47 illustrates a top view of an example jet ejector according to one embodiment of the present disclosure.
  • Figure 48 illustrates a top view of a linear jet ejector assembly according to one embodiment of the present disclosure.
  • Figure 49 is a schematic diagram of an example jet pack according to one embodiment of the present disclosure.
  • Figures 50a and 50b illustrate an example jet pack according to one embodiment of the present disclosure.
  • Figures 51a and 51b illustrate other example jet packs according to one embodiment of the present disclosure.
  • Figures 52a and 52b illustrate other example jet packs according to one embodiment of the present disclosure.
  • Figure 53 shows the jet pack of Figures 52a and 52b mounted to the back of a passenger.
  • Figures 54a and 54b illustrate a front view and a side view, respectively, of an example lift platform according to one embodiment of the present disclosure.
  • Figures 55a and 55b illustrates other example lift platforms according to one embodiment of the present disclosure.
  • Figures 56a and 56b illustrates other lift platforms according to one embodiment of the present disclosure.
  • Figure 57 shows an example measured value of drag on a ship hull as a function of speed.
  • Figures 58 and 59 show the flow streams around an example ship hull.
  • Figures 60 and 61 illustrate how the dominant residual drag is caused by the generation of waves.
  • Figure 62 shows an example hydrodynamic pressure acting on a boat hull.
  • Figure 63 illustrates a conventional propeller model according to one embodiment of the present disclosure.
  • Figure 64 shows how propulsive efficiency approaches 1.0 as V A /V C approaches 1.0.
  • Figure 65 shows that the efficiency of a conventional propeller increases with size, although the efficiency is relatively low.
  • Figure 66 shows propeller efficiency as a function of velocity and propeller pitch. Pitch is the distance a propeller would travel in a soft material using a single rotation.
  • Figure 67 shows the efficiency of a variable-pitch two-blade propeller that extends the range of efficient velocities.
  • Figure 68 shows the efficiency of a variable-pitch four-blade propeller ranges from 0.49 to 0.77.
  • Figures 69a to 69b illustrate example maritime propulsion systems that are mounted on a ship according to various embodiments of the present disclosure.
  • Figure 70 illustrates another example propulsion system according to one embodiment of the present disclosure.
  • Figure 71 illustrates a schematic representation of another maritime propulsion system according to one embodiment of the present disclosure.
  • Figure 72 illustrates multiple example rudders that can be incorporated into the duct to allow for vectored thrust and enhanced maneuverability according to one embodiment of the present disclosure.
  • Figures 73 and 73a illustrate centrifugal and squirrel cage propellers that may be used as a fluid flow generator according to embodiments of the present disclosure.
  • Figure 74 illustrates how, at particular speeds, the peak of the wave at the stern will be above the inlet to the duct of Figure 71 according to one embodiment of the present disclosure.
  • Figures 75a to 75c show how a reversing duct may be used to reverse flow according to one embodiment of the present disclosure.
  • Figure 76 illustrates another example propulsion system according to one embodiment of the present disclosure.
  • Figure 77 illustrates another example propulsion system according to one embodiment of the present disclosure.
  • Figures 78 and 79 show the propulsive efficiency and factor in the square bracket, respectively for the propulsion system of Figure 77 according to one embodiment of the present disclosure.
  • Figure 80 illustrates another example propulsion system according to one embodiment of the present disclosure.
  • Figures 81 and 82 show the propulsive efficiency and factor in the square bracket, respectively for the propulsion system of Figure 80 according to one embodiment of the present disclosure.
  • Figure 84 illustrates an example hardware implementation of the propulsion system of Figure 77.
  • Figure 85 shows example maritime propulsion system using a centrifugal pump according to one embodiment of the present disclosure.
  • Figure 86 illustrates an example centrifugal pump that may be used with embodiments of the present disclosure.
  • Figure 87 illustrates an efficiency that may be obtained via use of the centrifugal pump of Figure 86.
  • Figure 88 shows the temperature, pressure, and velocity at various points in a turbojet engine.
  • Figure 89 shows the propulsive efficiency for aircraft engines as a function of airspeed.
  • Figures 90 and 91 show embodiments where the propulsion system is placed behind the fuselage of an aircraft.
  • DETAILED DESCRIPTION [0092]
  • Embodiments of the present disclosure relate to systems and methods for enhancing the thrust of vehicles (e.g., vertical-lift aircraft, fixed-wing aircraft, boats, ships, etc.) while minimizing power consumption. Thrust enhancement occurs by replacing conventional propeller designs typically having linearly oriented (e.g., 0-degree bend) input fluid flow and output fluid flows with fluid-moving devices that direct the fluid along a radial direction (e.g., 90-degree bend) or a reverse direction (e.g., 180-degree bend).
  • a radial direction e.g., 90-degree bend
  • a reverse direction e.g., 180-degree bend
  • Figure 1 illustrates an example Actuator Disc Theory model involving a linearly oriented input flow and outlet flow according to one embodiment of the present disclosure.
  • the actuator disc theory involves a propeller disc 104 that moves through a medium to develop a thrust T.
  • the velocity V B at the actuator disc is the arithmetic average of upstream velocity V A and the downstream velocity V C .
  • the energy content (J/m 3 ) contains a pressure component (N/m 2 or J/m 3 ) and a kinetic energy component (J/m 3 ), as determined by the Bernoulli equation.
  • the Bernoulli equation is applied to the fluid upstream of the actuator disc: [0096]
  • the Bernoulli equation can also be applied to the fluid downstream of the actuator disc: [0097]
  • the pressure difference across the actuator disc follows: [0098]
  • the thrust acting on the actuator disc is [0099]
  • the rate that kinetic energy is imparted to the flowing fluid follows: [00100] It is desirable to have the maximum amount of thrust per unit of kinetic power, which is determined by the following metric: [00101]
  • a conventional propeller having linearly oriented inlet flow and outlet flow would have a thrust per unit of kinetic power factor of 2.
  • Figure 2 illustrates another example Actuator Disc Theory model involving multiple actuator discs 200 that flows the fluid through a duct 202 having a 90-degree radial bend according to one embodiment of the present disclosure.
  • the area at the inlet and outlet are variable and can be specified by the design engineer. In this case, the total area of the inlet and outlet are specified so that the relationship between V B and V C is the same as the propeller, which allows the impact of the directional change to be determined.
  • This velocity ratio is obtained by specifying the area of the inlet and outlet as follows: [00104]
  • the pressure at the inlet to the actuator discs can be obtained by applying the Bernoulli equation [00105]
  • the pressure at the outlet of the actuator discs is determined by applying the Bernoulli equation to the outlet stream.
  • the net thrust on the duct results from the pressure difference on the duct area A C plus the momentum of the mass leaving the duct.
  • the rate that kinetic energy is imparted to the flowing fluid follows: [00108]
  • the thrust per unit of kinetic power follows: [00109]
  • actuator discs 200 configured in a duct 202 having a 90-degree bend in its inlet flow would have a thrust per unit of kinetic power factor of 2.75.
  • Figure 3 illustrates another example Actuator Disc Theory model involving multiple actuator discs 300 that flow the fluid through a duct 302 having a 180-degree radial bend according to one embodiment of the present disclosure.
  • the total area of the inlet and outlet are specified so that the relationship between V B and V C is the same as the actuator discs 300 (e.g., propellers), which allows the impact of the directional change to be determined.
  • actuator discs 300 configured in a duct 302 having a 180-degree bend in its inlet flow would have a thrust per unit of kinetic power factor of 2.5.
  • the actuator discs 300 configured in a duct 302 having a 180-bend is better than a conventional propeller design (e.g., 2.5 > 2.0) as described above with reference to Figure 1, but not as good as actuator discs 200 configured in a duct 202 having a 90-degree bend as described above with reference to Figure 2 (e.g., 2.5 ⁇ 2.75).
  • V B V C
  • This velocity ratio is obtained by specifying the area of the inlet and outlet as follows: [00119] Applying the Bernoulli equation at the inlet allows the suction pressure ⁇ P to be calculated [00120] The net thrust on the duct results from the pressure difference on the inlet duct plus the momentum of the mass entering and leaving the duct.
  • This particular case is an improvement over the conventional propeller design (2.0) as described above with reference to Figure 1, and the case where the actuator discs 200 are configured in a duct 202 having a 90-degree bend as described above with reference to Figure 2 (2.5).
  • Figure 5 illustrates another example Actuator Disc Theory model involving an actuator disc 500 that increases the pressure in a duct 502 having a 180-degree radial bend, while having a varied fan position according to one embodiment of the present disclosure.
  • This velocity ratio is obtained by specifying the area of the inlet and outlet as follows: [00126] Applying the Bernoulli equation at the inlet allows the suction pressure ⁇ P to be calculated [00127] The net thrust on the duct results from the pressure difference on the duct and fan, plus the momentum of the mass entering and leaving the duct.
  • FIGS. 6A, 6B, and 6C illustrate two-dimensional (x, y) flow fields determined by computational fluid dynamics (CFD) analysis for a simulated circular 180-degree duct according to one embodiment of the present disclosure.
  • CFD computational fluid dynamics
  • the width of the simulated duct inlet in Figure 6A is 1.0 meter
  • the width of the simulated duct inlet in Figure 6B is 0.75 meters
  • the width of the simulated duct inlet in Figure 6C is 0.5 meters.
  • the pressure difference that induces the flow is 1000 Pa.
  • Table 1 reports the upward thrust (N) per meter of depth in the z direction.
  • Table 1 [00131] As shown, the CFD results confirm that decreasing the inlet area relative to the outlet area increases thrust.
  • Figure 7 shows the two-dimensional (x, y) flow fields determined by computational fluid dynamics (CFD) analysis for a simulated low-profile 180-degree duct.
  • CFD computational fluid dynamics
  • FIG. 9a, 9b, 10a, and 10b show the flow fields and pressure fields, respectively, for circular and low-profile ducts in open space. More particularly, Figure 9a shows the flow field and Figure 9b show the pressure field for a circular 180-degree duct in an open space.
  • Figure 10a shows the flow field and Figure 10b shows the pressure field for a low- profile 180-degree duct in an open space.
  • the z direction emanates perpendicularly from the xy- plane.
  • Table 3 summarizes the data gathered from the CFD analysis. In both cases, the thrust per kinetic power is very similar; however, it should be emphasized that meaningful comparison is only possible at the same duct size and pressure difference. Table 3
  • FIGS 11a and 11b illustrate cross-sectional views of example propulsion systems 1100, 1102 incorporating linear circular ducting according to one embodiment of the present disclosure.
  • Each propulsion system 1100, 1102 includes a duct 1104, 1106 having an inlet portion 1108, 1110 and outlet portion 1112, 1114 with a fluid flow generator, such as one or more propellers 1120 configured inside. While a propeller is shown in this configuration, other fluid flow generators may be show in other configurations including, but not limited to, squirrel-cage fans, turbo fans, impellers, jet engines, propellers, and the like.
  • Figure 11a shows the inlet portion 1108 and outlet portion 1112 having equally sized cross-sectional areas
  • Figure 11b shows the inlet portion 1110 and outlet portion 1114 with unequally sized cross-sectional areas.
  • Figures 12a and 12b illustrate example fan arrangements (e.g., fluid flow generators) that that may be used to blow air through the duct 1104, 1106 of Figures 11a and 11b according to embodiments of the present disclosure.
  • axial fans are shown here, it is possible to use any suitable type of fluid flow generator, such as squirrel-cage fans, turbo fans, impellers, jet engines, propellers, and the like.
  • FIG. 12a shows multiple fans with unequally sized areas
  • FIG. 12b shows fans with equally sized areas.
  • Figures 13a and 13b illustrate an example flying car 1300 according to one embodiment of the present disclosure.
  • the flying car 1300 employs equal-area circular ducts similar to that shown and described above with reference to Figure 11a.
  • the ducts 1302 are selectively movable from a deployed position (flying mode) in which the ducts 1302 are fully extended as shown in Figure 13a to a retracted position (driving mode) as shown in Figure 13b.
  • the flying car 1300 includes a passenger compartment 1304 that may be used to seat a user, such as a driver of the flying car 1300. Although the passenger compartment 1304 is shown as an open cockpit, other embodiments contemplate that the passenger compartment can be covered to allow the passenger to fly in a closed cockpit. [00138] In one embodiment, the flying car 1300 includes an upper section 1306 and a lower section 1308.
  • Figures 14a and 14b illustrate cross-sectional views of example propulsion devices 1400, 1402 incorporating linear low-profile ducting according to one embodiment of the present disclosure.
  • Figure 14a shows the inlets 1404 and outlet 1406 to the ducts with equally sized cross-sectional areas
  • Figure 14b shows the inlets 1408 and outlet 1410 to the ducts with unequally sized cross-sectional areas.
  • the duct may include one or more bulbs 1412 to assist the fluid turn the tight corner, and/or a scoop mechanism 1414 to help fluid enter with less loss.
  • a variety of different fluid flow generators such as propellers (or other devices) may be utilized.
  • Figures 15a and 15b illustrate example vertical-lift flying motorcycles 1500, 1502 with low-profile ducts with unequally sized inlet and outlet areas according to one embodiment of the present disclosure.
  • the flying motorcycle 1500 of Figure 15a shows a ducting arrangement in which the passenger faces parallel to the ducts of the flying motorcycle
  • the flying motorcycle 1502 of Figure 15b shows a ducting arrangement in which the passenger faces perpendicular to the ducts of the flying motorcycle.
  • Design example [00141] Perpendicular orientation, low-profile duct – Table 3 shows the CFD data for the ducts in free space.
  • the low-profile duct has a width of 2.6 m.
  • two adjacent ducts have a width of 5.2 m, which are oriented as shown in Figure 15b.
  • the circular duct has a width of 2.6 m.
  • two adjacent ducts When placed side-by-side, two adjacent ducts have a width of 5.2 m, which are oriented as shown in Figure 15b.
  • a 65-hp Rotax Type 582 engine can power the lighter aircraft [00164] At an output power of 20 kW, the specific fuel consumption is 590 g/kWh (see Figure 16a); therefore, the fuel consumption rate is [00165]
  • a 100-hp Rotax Type 912 engine can power the heavier aircraft [00166] At an output power of 70 kW, the fuel consumption rate is 24 L/h (see Figure 16b). The density of fuel is about 0.77 kg/L, so the fuel consumption rate is 18.5 kg/h.
  • Duct options [00167] Figures 17 through 22 show various optional arrangements for the duct of the propulsion device, which address various means to improve efficiency or lift according to one or more embodiments of the present disclosure.
  • Figure 17 illustrates one embodiment of a propulsion device 1700 having a duct 1702 with a long, straight outlet portion 1704.
  • Figure 18 illustrates another embodiment of a propulsion device 1800 having a duct 1802 with a long, straight profile. Additionally included are external turning vanes 1804 that help improve efficiency.
  • Figure 19 illustrates another embodiment of a propulsion device 1900 having duct 1902 a short, straight profile. Additionally included are external turning vanes 1904 that help improve efficiency.
  • Figure 20 illustrates another embodiment of a propulsion device 2000 having a duct 2002 with an extra-long, straight outlet portion 2004.
  • Figure 21 illustrates another embodiment of a propulsion device 2100 having a duct 2102 with an extra-long, straight outlet portion 2104.
  • FIG. 22 illustrates another embodiment of a propulsion device 2200 having a duct 2202 with an extra-long, straight outlet portion 2204. Additionally included are diverging vanes 2206 configured at the bottom end of the outlet portion to provide enhanced efficiency.
  • Squirrel cage fans [00170]
  • Figures 23 through 25 illustrate another example propulsion system utilizing squirrel cages assemblies 2300, 2400 that may be implemented on a flying car 2500 according to embodiments of the present disclosure.
  • the propulsion system 2300 includes a duct 2306 having an inlet portion 2304 and outlet portion 2308 that are configured on a flying car 2500.
  • Figures 24a and 24b show cones 2420 in the center of the squirrel cage propeller.
  • FIG 25a shows the flying car 2500 with the inlet portion 2304 of the duct 2410 removed in order to reveal the inlet 2304 of the propeller
  • Figure 25b shows the inlet portion 2402 of the duct 2410 in operative engagement on the flying car 2500.
  • Figure 23 illustrates an example squirrel cage propeller assembly 2300 that may be implemented with the propulsion system according to one embodiment of the present disclosure.
  • the squirrel cage assembly 2300 includes two pair of squirrel cage propellers 2302, each having an inlet 2304 that receives fluid from the inlet portion of the duct 2306 to generate an outlet stream for providing lift for the flying car 2500 of Figures 25a and 25b.
  • each pair of squirrel cage propellers 2302 is configured to turn in opposite directions to balance angular momentum.
  • one or both pair of propellers are driven by a single motor located proximate the center of the flying car 2500.
  • a bulb 2312 helps direct the flow out of the squirrel cage.
  • FIG 24a and 24b illustrate an example squirrel cage propeller 2400 that may be implemented with the flying car 2500 according to one embodiment of the present disclosure.
  • the squirrel cage assembly 2400 has an inlet 2402 that receives fluid from the inlet portion of the duct 2410 to generate an outlet stream for providing lift for the flying car 2500.
  • Figure 24a shows the assembly 2400 with the inlet portion 2410 of the duct 2306 removed, whereas Figure 24b shows the inlet portion 2410 of the duct 2306 in operative engagement on the assembly 2400.
  • An optional cone 2420 helps direct inlet flow in the radial direction.
  • two vertical gyroscopes (not shown), each rotating in opposite directions may be provided. These gyroscopes stabilize the flying vehicle from gusts of wind. Also, if one gyroscope spins slightly faster than the other, the flying car can rotate and adjust yaw.
  • horizontal thrust can be obtained by tilting the vehicle so that a portion of the lifting thrust becomes horizontal thrust.
  • Figure 25a illustrates an external view of the flying car with no inlet ducts 2410 whereas Figure 25b illustrates an external view of a flying car with inlet ducts 2410.
  • Circular Ducts [00176]
  • Figures 26a, 26b, and 26c illustrates example various propeller types that may be implemented with a circular duct according to embodiments of the present disclosure.
  • Figure 26a shows a ducted axial propeller 2604
  • Figure 26b shows a squirrel-cage propeller 2606
  • Figure 26c shows a turbo propeller 2608.
  • Figure 27 shows an example turbo propeller as shown and described with reference to Figure 26c.
  • the “turning duct” produces thrust as the flow reverses.
  • the propellers can be nested in some embodiments.
  • Figure 28 illustrates multiple clustered circular ducts that combine their thrust to increase lift capability. By rotating half the fans clockwise and the other half counter-clockwise, net torque on the aircraft may be reduced or eliminated.
  • Coanda Effect [00178]
  • Figure 29 illustrates an example hybrid lifting system that employs the Coanda Effect to provide additional lift. As shown, the duct includes multiple, nested vanes that direct outlet stream generated by the propeller through a directional turn.
  • FIGs 30 through 32 illustrate example jet engines 3000, 3100, and 3200 that may be implemented with the propulsion system according to embodiments of the present disclosure.
  • Figure 30 illustrates a schematic diagram of a conventional axial jet engine, so named because most or all the fluids flow generally in an axial direction.
  • the jet engine 3000 would be immersed in air (e.g., airplane) or water (e.g., ship).
  • FIG. 31 illustrates a schematic of a radial jet engine 3100, so named because the inlet fluid has a radial component to its velocity. Fluid enters along the circumferential opening with area A 1 and exits from the axial opening with area A 2. A conical plate redirects the radial flow into the axial direction resulting in axial thrust acting on the conical plate.
  • Figure 32 illustrates a reverse-flow jet engine 3200. Flow enters from the bottom and encounters a thrust plate that reverses the flow through a 180-degree duct. As shown previously, when fluid enters through a 180-degree duct, thrust is greater than a conventional propeller.
  • WATER VEHICLES Torpedo [00182] Figures 33 through 38 illustrate example torpedoes that may be implemented with the propulsion system according to embodiments of the present disclosure. In particular, Figure 33 shows the flow around a conventional torpedo whereas Figures 34a through 34d show various options for torpedoes with axial propellers.
  • Figure 34a describes two counter-rotating propellers, which are often used in torpedoes.
  • Figure 34b describes a single rotating propeller with a stationary stator to remove the rotation from the exiting fluid. Both Figures 34a and 34b employ a shallow-angle inlet cone leading to the propeller.
  • Figures 34c and 34d are comparable to Figures 34a and 34b, except that a steep-angle inlet cone leads to the propeller, which shortens the length of the torpedo.
  • an undesirable feature of this approach is that there may be flow separation between the fluid and the inlet cone. In torpedoes, a shallow angle is employed to prevent flow separation, which would increase form drag.
  • Figures 35a through 35e illustrate several embodiments of squirrel-cage propellers that may be used with a torpedo according to embodiments of the present disclosure.
  • Figure 35a shows a single squirrel-cage propeller
  • Figure 35b shows a double squirrel-cage propeller with counter rotation
  • Figure 35c shows a single squirrel-cage propeller with a stationary stator to remove rotation from the exiting fluid
  • Figure 35d shows the blade design for a counter- clockwise rotation
  • Figure 35e shows the blade design for a clockwise rotation.
  • Figures 36a through 36ed illustrate other embodiments of the squirrel-cage propeller, which are similar to the embodiments of Figures 35a through 35e, except that turning vanes are employed.
  • Figure 37a through 37e illustrate other embodiments of the squirrel-cage propeller, which are similar to the embodiments of Figures 36a through 36e except that a reduction nozzle is employed at the outlet. This embodiment would be used if the propeller diameter were small, but high thrust is required. Because of the nozzle, the interior pressure of the squirrel-cage propeller is large, which applies a large force to the interior cone of the propeller and thereby produces a large thrust.
  • Figures 38a and 38b are cut-away views showing the interior and exterior cone of a turbo propeller.
  • Figure 38a does not include a stator.
  • Figure 38b includes a stator to remove rotation from the fluid exiting the propeller.
  • FIG 39 illustrates a jet boat 3900 in which the propeller 3902 (e.g., a ducted axial propeller) is located in the interior of the boat.
  • the inlet water feeding the interior propeller comes from opposite sides of the boat; therefore, the inlet momentum is canceled.
  • forward thrust is imparted.
  • Additional forward thrust is imparted from the momentum of the fluid ejected from the rear of the boat.
  • SWATH Small Waterplane Area Twin Hull
  • Figures 40a and 40b illustrate various bottom and frontal views of a traditional monohull boat hull, a catamaran boat hull, and a Small Waterplane Area Twin Hull (SWATH) hull.
  • FIG. 40b shows an artist’s concept for a SWATH employing a steep-angle inlet cone ducted axial propeller. Alternatively, the squirrel-cage propeller or turbo propeller could be used.
  • Figure 41 shows the submerged portion of SWATH boat.
  • Figure 41a shows the circular cross section, as illustrated in Figure 40b.
  • Figure 41b shows a semi-circular cross section, which is open on the bottom and filled with air.
  • Figures 41c and 41d show an option for reducing viscous drag. A porous membrane surrounds the hull.
  • the membrane could be a variety of materials; however, Teflon is envisioned because of its low surface energy, which will reduce adhesion of fouling materials.
  • the membrane could be made from expanded Teflon (i.e., Gore Tex), woven Teflon fibers, non-woven Teflon fibers, Teflon felt, or sintered Teflon particles.
  • the membrane could be sintered metal.
  • the sintered metal could be coated with Teflon or electroless nickel/Teflon. Compressed air is forced between the membrane and the solid surface so that small bubbles of air are trapped in the membrane pores. Primarily, the water interfaces with air rather than a solid surface, which reduces friction.
  • FIGS 42a and 42b illustrate bottom and side views, respectively, of a monohull boat in “travel mode” meaning it is traveling with a significant forward velocity.
  • Figure 43a and 43b illustrate bottom and side views, respectively, showing another monohull boat in “thrust mode” meaning it is traveling with a nearly zero velocity, but has tremendous thrust.
  • thrust mode would be useful for icebreakers. While in thrust mode, because of the 180-degree bend, the boat will produce significantly more thrust than a conventional propeller.
  • Thrust mode is achieved by placing the turning duct just forward of the radial jet engine. While in travel mode, the turning ducts could be removed and stored elsewhere on the boat.
  • FIG. 44 is a schematic diagram illustrating an example jet pack 4400 according to one embodiment of the present disclosure.
  • the jet pack 4400 generally includes two engines, each having two nested jet ejectors 4412a, 4412b that are powered by high-pressure propellant fuel stored a storage tank 4404. Two valves 4406 are provided that independently control the flow of fuel to nozzles 4414 configured on each engine.
  • high-pressure propellant fuel delivered to each engine is provided by catalyst beds 4408 that decomposes the propellant fuel from the storage tank 4404 to produce high-velocity gases .
  • the storage tank 4404 may store the propellant fuel at high pressure (as shown), or alternatively, the storage tank 4404 may store the propellant fuel at a relatively low pressure in which the propellant fuel is delivered to the catalyst bed 4408 via a pump (not shown).
  • the propellant fuel used by jet packs is high-concentration ( ⁇ 90%) hydrogen peroxide dissolved in water.
  • the following reaction occurs: 2 H 2 O 2 ® 2 H 2 O + O 2
  • a catalyst bed e.g., silver, manganese dioxide
  • the reaction is exothermic so the product water is steam.
  • the energy density of the propellant fuel mixture can be increased by adding a reducing component, such as alcohol, sugar, or a hydrocarbon.
  • counter-rotating flywheels 4416 can be located on the jet pack 4400 to enhance stability. Furthermore, if the rotation rate of one flywheel 4416 is greater than the other, it allows the jet pack to rotate about the vertical z-axis, thus providing an element of control. In another embodiment, two pairs of counter-rotating flywheels can be oriented with the rotation axes at right angles with respect to each other, thus allowing stable control in both the x-axis and z-axis.
  • FIG. 45 illustrates a schematic diagram of another example jet pack 4500 according to one embodiment of the present disclosure.
  • the jet pack 4500 is similar in design and construction to the jet pack 4400 shown and described above with reference to Figure 44, except that electricity-powered ducted fans 4502 replace the ejectors 4412a, rocket nozzle 4414 combination.
  • a hollow annulus may be configured in the jet ejector 4412b to store batteries.
  • Figure 46 illustrates a schematic diagram of another example jet pack 4600 according to one embodiment of the present disclosure.
  • FIG. 47 illustrates a top view of an example jet ejector 4700 according to one embodiment of the present disclosure.
  • the jet ejector 4700 includes opposing ducts 4702 that are disposed on both sides of four engines 4704 that are arranged in a linear fashion relative to one another.
  • each engine 4704 may include an engine 4402, 4502, 4602, such as described above with reference to Figures 44, 45, and 46.
  • the engines 4704 are configured to receive a fluid (e.g., air) to generate an inlet fluid flow through an inlet portion 4706 of the duct 4702 and generate an outlet fluid flow through an outlet portion of the duct 4702, which in this particular example, would be downward beneath the engines 4704.
  • the inlet portion 4706 is bent in a circular shape to alter a direction of a corresponding either one of the input stream or the output stream generated by the engines 4704.
  • Figure 48 illustrates a top view of a linear jet ejector assembly 4800 according to one embodiment of the present disclosure.
  • the linear jet ejector assembly 4800 generally includes three jet ejectors 4700 arranged as shown.
  • a passenger 4802 is shown in operative position with regard to the jet ejector assembly 4800 such that, when thrust is applied by the assembly 4800, the passenger 4802 may be lifted from the ground.
  • Figure 49 is a schematic diagram of an example jet pack 4900 according to one embodiment of the present disclosure.
  • the jet pack 4900 includes an electricity-powered blower 4902 that provides pressurized air to a combustor 4904. Fuel is added to the combustor 4904 from a pressurized fuel tank 4906. In other embodiments, a pump could provide fuel from an atmospheric-pressure tank (not shown).
  • FIGs 50a and 50b illustrate an example jet ejector 5000a, 5000b according to one embodiment of the present disclosure.
  • the jet ejector 5000a of Figure 50a includes a duct with an inlet portion that is bent at a 180-degree angle
  • the jet ejector 5000b of Figure 50b includes a duct with an inlet portion that is bent at a 90-degree angle.
  • the jet ejector 5000 includes an electricity-powered blower 5002 that pressurizes a reservoir 5004 denoted by the gray-shaded area.
  • the pressurized air flows through a nozzle that induces air flow through a jet ejector 5008 with turning vanes 5010. The change in flow direction from the turning vanes enhances lift.
  • a hollow region inside the ejector 5008 may be used to hold batteries.
  • the geometry of the jet ejector 5008 can be circular or linear.
  • the inlet portion 5012 of the turning vanes can be greater than or less than the outlet area from the jet ejector 5008.
  • the blower 5002 can be any desired type (e.g., axial, centrifugal, or squirrel cage).
  • the compressor inlet can be configured with a muffler 5020 in some embodiments.
  • the reservoir 5004 can be heated by burning a fuel, which increases the velocity through the nozzle and thereby reduces the required power input from the blower.
  • FIGS 51a and 51b illustrate other example jet packs 5100a, 5100b according to one embodiment of the present disclosure.
  • the jet pack 5100a, 5100b are similar to the jet packs 5000a, 5000b of Figures 50a and 50b, except that the exhaust from a jet engine 5102 pressurizes the reservoir 5104. Additionally, a hollow cavity in the jet ejectors 5106 can be used to house the fuel.
  • the air exiting the nozzle is blended with turning-vane air in stages, which minimizes velocity differences upon mixing and thereby improving efficiency.
  • FIGs 52a and 52b illustrate other example jet packs 5200a, 5200b according to one embodiment of the present disclosure.
  • the jet packs 5200a, 5200b are similar to jet packs 5100a, 5100b, except that a rocket 5202 is implemented to induce flow through the jet ejector 5204.
  • the air exiting the nozzle is blended with turning-vane air in stages, which minimizes velocity differences upon mixing and thereby improves efficiency. That is, the end of each vane is configured at different positions along the duct so that air exiting each vane may be introduced at different positions in the duct. Additionally, a hollow region configured in the ejector 5204 may be used to hold the rocket propellant.
  • Figure 53 shows the jet packs illustrated in Figures 50a, 50b, 51a, 51b, 52a, and 52b mounted to the back of a passenger 5302.
  • Figures 54a and 54b illustrate a front view and a side view, respectively, of an example lift platform 5400 according to one embodiment of the present disclosure.
  • the lift platform 5400 includes one or more gas-moving devices 5402 (e.g., electricity-powered fan, jet engine, propeller, rocket), a duct inlet 5404, and a duct outlet 5406.
  • the air is drawn in from the bottom, which gives additional lift when the air turns direction.
  • the duct inlet 5404 may include a muffler to reduce noise.
  • FIG. 55a and 55b illustrates other example lift platforms 5500a, 5500b according to one embodiment of the present disclosure.
  • the lift platform 5500 includes a single-propeller 5502 for providing lift.
  • a gyroscope 5504 is included, which rotates opposite the propeller to prevent the platform from rotating due to torque imparted by the propeller 5502. If a passenger 5506 wishes to rotate the platform about its vertical axis, he or she can cause the gyroscope 5504 to rotate slightly faster or slower.
  • the lift platform can be implemented in a circular or linear geometry.
  • FIGs 56a and 56b illustrates other lift platforms 5600a, 5600b according to one embodiment of the present disclosure.
  • Each lift platform 5600a, 5600b includes a double-propeller assembly including two propellers 5602, 5604.
  • Each propeller 5602, 5604 rotates in an opposite direction to prevent the platform from rotating. If a passenger 5606 wishes to rotate the platform about the vertical axis, he or she can rotate one propeller slightly faster and the other slightly slower. The platform will rotate in the direction opposite of the faster propeller.
  • the lift platform can be implemented in a circular or linear geometry.
  • Figure 57 shows an example measured value of drag on a ship hull as a function of speed.
  • Figure 58 shows the flow streams around a ship hull.
  • the turbulent eddies behind the ship are responsible for about 3 to 5% of the total drag (see Table 4 and Figure 59).
  • Table 4 [00222]
  • the dominant residual drag is caused by the generation of waves ( Figures 60 and 61).
  • the impact of waves is minor at low speeds and becomes dominant at high speeds. Depending upon the length of the ship and its speed, the waves have particular resonances that can impact drag significantly.
  • Figure 62 shows an example hydrodynamic pressure acting on a boat hull.
  • FIG. 63 illustrates a conventional propeller model according to one embodiment of the present disclosure. According the Actuator Disc Theory, the velocity V B at the actuator disc is the arithmetic average of upstream velocity V A and the downstream velocity V C .
  • Mass continuity allows the relationship between the areas to be calculated [00227]
  • the energy content (J/m 3 ) contains a pressure component (N/m 2 or J/m 3 ) and a kinetic energy component (J/m 3 ), as determined by the Bernoulli equation.
  • the Bernoulli equation is applied to the fluid upstream of the actuator disc: [00228]
  • the Bernoulli equation can also be applied to the fluid downstream of the actuator disc: [00229]
  • the pressure difference across the actuator disc follows: [00230]
  • the thrust is [00231]
  • the rate that kinetic energy is imparted to the flowing fluid follows: [00232] It is desirable to have the maximum amount of thrust per unit of kinetic power, which is determined by the following metric: [00233]
  • the efficiency is
  • Figure 67 shows the efficiency of a variable-pitch two-blade propeller that extends the range of efficient velocities. At its peak, the efficiency can be as high as 0.87; however, at low velocities, the efficiencies are low (about 0.60).
  • Figure 68 shows the efficiency of a variable-pitch four-blade propeller ranges from 0.49 to 0.77.
  • FIG. 69a illustrates an example maritime propulsion system 6900 that is mounted on a ship 6902 according to one embodiment of the present disclosure.
  • the maritime propulsion system 6900 includes a duct 6906 that provides a technique for increasing a propulsive area created by a driving force, such as a propeller 6904.
  • the duct 6906 may be configured on the ship 6902 in any suitable manner.
  • a bank of axial or screw propellers 6904 located on the front of the duct 6906 draws water from the underside of the ship and ejects it from the rear, thus providing thrust.
  • the cross sectional size of the submerged duct 6906 can be approximately similar to, less than, or greater than the cross sectional size of the submerged portion of the hull.
  • Figures 69b and 69c show an embodiment that has a pivoting extended flap 6908. Depending on the weight of cargo in a ship, the draft of the ship can vary dramatically. The angle of the pivoting extended flap can vary to ensure the fluid discharge is always below the water line.
  • Figure 69d shows an embodiment in which the propulsor 6905 draws fluid from the underside of the duct.
  • FIG. 70 illustrates another example maritime propulsion system 7000 according to one embodiment of the present disclosure.
  • the maritime propulsion system 7000 includes a structure 7002 configured with a hole for placement of a disc actuator (propeller) 7004 inside.
  • the structure 7002 may be envisioned as a stationary dock, or the symmetrical portion of a ship or aircraft.
  • the disc actuator 7004 draws fluid (water) from the adjacent free stream beside the structure 7002.
  • this analysis is performed in the context of a maritime propulsion system, it may be applied to aircraft propulsion as well.
  • Figure 71 illustrates a schematic representation of a maritime propulsion system 7100 according to one embodiment of the present disclosure.
  • the propulsion system 7100 described in Figure 70 is configured at the stern of a ship 7102.
  • a duct 7108 is placed at the stern 7106 of the ship 7102 that has essentially the same cross section as the submerged section of the hull.
  • Fluid is drawn from the sides and possibly bottom by one or more disc actuators (propellers) 7110, which fills the duct and pushes fluid towards the rear.
  • the duct 7108 can have inlet turning vanes (not shown) that help change the fluid direction efficiently.
  • the advantages of this technology include, but are not necessarily limited to the following ⁇
  • the size of the propeller device is decoupled from the size of the propulsion cross section, thus providing added design flexibility.
  • multiple small-diameter propellers could line the wall of the duct and thereby replace one large propeller.
  • multiple small rudders can be incorporated into the duct, which allows for vectored thrust and enhanced maneuverability.
  • the type of propeller may include not only traditional axial propellers, but also centrifugal and squirrel cage propellers among others (see Figure 73).
  • the entrance is rounded to provide a smooth flow path.
  • the center of the squirrel cage can contain a central cone that ensures the velocity is approximately constant along the axis.
  • the squirrel cage propeller can incorporate stationary stators that convert rotational kinetic energy into translational kinetic energy, thus improving efficiency. Furthermore, the stators can be actuated giving the ability to change the angle relative to the rotating hydrofoils of the squirrel cage propeller, thus allowing high efficiency at a variety of rotational speeds.
  • Inlet guide vanes regulate the angle of attack of the fluid relative to the rotating hydrofoils of the squirrel cage propeller. Similarly, the inlet guide vanes can be rotated to change the angle of attack, thus allowing high efficiency at a variety of rotational speeds.
  • Both the stators and guide vanes can be segmented along the axial length of the squirrel cage.
  • each segment can be individually rotated for optimal angles both along the axis and the circumference.
  • the optimal position of each segment can be adjusted to reduce energy consumption for each condition (e.g., speed, water density, water viscosity).
  • Traditional propellers have a cross-sectional area only a fraction – typically 10 to 50% – of the submerged cross-sectional area of the hull.
  • the duct fills the entire cross section, which has the following benefits: o The wake eddies behind the boat are eliminated, which reduces drag by about 3 to 5%.
  • FIG. 75a shows a reversing duct that slides vertically downward to reverse flow.
  • Figure 75b shows a reversing duct that pivots to reverse flow.
  • Figure 75c shows a reversing duct with two pivot points. One rotates the entire duct into position and the other rotates nested duct segments into a fully deployed position.
  • Figure 76 illustrates another example ducted propulsion system according to one embodiment of the present disclosure. Although this analysis is performed in the context of a maritime propulsion system, it may be applied to aircraft propulsion as well. [00257] Define f [00258] Account for mass [00259] Account for y momentum [00260] Substituting [00261] The power is [00262] The thrust-to-power ratio is [00263] Flip sign so thrust is in forward direction [00264] This is the same as a conventional propeller. [00265] The efficiency is [00266] The propulsive efficiency approaches 1.0 as V A /V C approaches 1.0.
  • Figure 77 illustrates another example ducted propulsion system 7900 according to one embodiment of the present disclosure.
  • This analysis is performed in the context of a maritime propulsion system, it may be applied to aircraft propulsion as well.
  • the power is [00278]
  • the thrust-to-power ratio is [00279] Flip sign so thrust is in forward direction [00280]
  • the efficiency is
  • Figures 78 and 79 show the propulsive efficiency and factor in the square bracket, respectively. [00282] It should be emphasized that these equations may only be valid to the degree that the boundary conditions can be achieved.
  • Option 4 [00283]
  • Figure 80 illustrates another example ducted propulsion system 8000 according to one embodiment of the present disclosure. Although this analysis is performed in the context of a maritime propulsion system, it may be applied to aircraft propulsion as well. The ducted propulsion system 8000 is similar to the ducted propulsion system of Figure 77, except areas A 1 and A 2 are not identical.
  • the thrust-to-power ratio is [00293] Flip sign so thrust is in forward direction [00294]
  • the efficiency is [00295]
  • Figures 81 and 82 show the propulsive efficiency and factor in the square bracket, respectively of the propulsion system 7800 described above.
  • Figure 84 illustrates an example hardware implementation 8400 of the ducted propulsion system of Figure 77.
  • the hardware implementation 8400 includes a squirrel cage fluid mover 8402 having a squirrel cage 8404 concentrically aligned with stators 8406 that remove spin from the fluid.
  • Turning vanes 8410 direct the radial flow toward the rear.
  • the angle of attack of the hydrodynamic foils can be varied using a mechanical pivot mechanism in some embodiments.
  • Figure 85 illustrates an example hardware implementation of the maritime propulsion system 8000 according to one embodiment of the present disclosure.
  • the system 8000 is configured at the rear of a ship 8002. A portion of the fluid flows through a propeller 8004 and is directed rearward.
  • the propeller 8004 can be a squirrel cage ( Figure 84) or a centrifugal pump (Figure 86). At its optimal operating condition, a centrifugal pump is about 85% efficient ( Figure 87). Variable-angle inlet guide vanes can extend the efficiency over a wider operating range. Furthermore, during operation, the area ratio (A 1 /A 2 ) can be adjusted to maintain optimal performance at a variety of ship velocities.
  • Aircraft [00300] It should be emphasized that although these ducted propulsion systems have have been described in the context of ship propulsion, the concepts can be applied equally well to aircraft. For example, the propulsion system illustrated in Figure 84 could be mounted on a conventional aircraft and has the advantage that it is not affected by bird strikes.
  • Figure 88 shows the temperature, pressure, and velocity at various points in a turbojet engine.
  • the inlet velocity V A is 450 ft/s (307 mi/h) and the outlet velocity V C is 1600 ft/s (1090 mi/h).
  • the propulsive efficiency is [00302]
  • Figure 89 shows the propulsive efficiency for aircraft engines as a function of airspeed. (Note: The data point in the figure is the above calculated efficiency for a turbojet.) In the range of typical commercial aircraft (460 to 575 miles per hour), the propulsive efficiency of high bypass turbofan engines is 74–83%; therefore, efficiency gains are possible by increasing the area through which air flows.
  • Figures 90 and 91 show embodiments where the propulsion system 9000, 9100 is placed behind the fuselage 9002, 9102 of an aircraft 9004, 9104.
  • Figure 90 shows axial fans 9006 on the faces of the duct
  • Figure 91 shows squirrel cage fans 9106 (see Figure 73a).

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Ocean & Marine Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supports For Pipes And Cables (AREA)

Abstract

La présente invention concerne un système de propulsion qui comprend un conduit et un générateur d'écoulement de fluide. Le conduit a une cavité allongée ayant une partie d'entrée et une partie de sortie. Le générateur d'écoulement de fluide est disposé dans le conduit. Le générateur d'écoulement de fluide est conçu pour recevoir un fluide pour générer un courant d'entrée à travers la partie d'entrée et générer un courant de sortie à travers la partie de sortie. Le courant de sortie est conçu pour générer une poussée pour un véhicule sur lequel sont montés le générateur d'écoulement de fluide et le conduit et la partie d'entrée et/ou la partie de sortie est(sont) courbée(s) selon une forme circulaire pour modifier une direction soit du courant d'entrée, soit du courant de sortie.
EP20855060.8A 2019-08-19 2020-08-17 Systèmes de propulsion et poussée-portance améliorées Pending EP4018098A4 (fr)

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US202062962144P 2020-01-16 2020-01-16
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US2008464A (en) * 1933-08-22 1935-07-16 Nishi Hirohisa Arrangement for starting flight requiring no gliding
US2972455A (en) * 1955-12-21 1961-02-21 Borchers Ariel George Induced-lift aircraft
US2990137A (en) * 1957-04-11 1961-06-27 George L Lentz Aircraft and lift-propulsion means therefor
BE758184A (fr) * 1969-10-31 1971-04-01 Silvester Richard Multiplicateur de poussee
US3785592A (en) * 1971-10-04 1974-01-15 K Kerruish Vtol aircraft
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