U.S. patent application number 14/095737 was filed with the patent office on 2015-08-13 for rotational ducted fan (rdf) propulsion system.
The applicant listed for this patent is Devin Glenn Samuelson. Invention is credited to Devin Glenn Samuelson.
Application Number | 20150226086 14/095737 |
Document ID | / |
Family ID | 53774518 |
Filed Date | 2015-08-13 |
United States Patent
Application |
20150226086 |
Kind Code |
A1 |
Samuelson; Devin Glenn |
August 13, 2015 |
ROTATIONAL DUCTED FAN (RDF) PROPULSION SYSTEM
Abstract
In accordance with the present invention, an embodiment of a
rotational ducted fan motor comprises a monolithic rotational
ducted fan rotor, an electric propulsion system, a static
aft-shroud comprising electrochemical-energy-storage, and an
engagement system. The rotational ducted fan rotor is the portion
of a ducted fan motor comprising a propeller, a duct, and a center
hub, and having the effect of increasing the pressure difference
from upstream to downstream of the propeller. The electric
propulsion system comprises permanent magnets affixed to the
rotational ducted fan rotor, repelling magnetic coils affixed to
the static aft-shroud and electrical power provided by the
electrochemical-energy-storage comprised within the aft-shroud.
Inventors: |
Samuelson; Devin Glenn;
(Greenacres, WA) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Samuelson; Devin Glenn |
Greenacres |
WA |
US |
|
|
Family ID: |
53774518 |
Appl. No.: |
14/095737 |
Filed: |
February 3, 2014 |
Current U.S.
Class: |
415/121.3 |
Current CPC
Class: |
B64D 29/02 20130101;
Y02T 50/64 20130101; Y02T 50/60 20130101; Y02T 50/40 20130101; B64C
11/001 20130101; B64D 27/24 20130101; B64D 29/04 20130101; Y02T
50/44 20130101 |
International
Class: |
F01D 25/16 20060101
F01D025/16; F01D 15/10 20060101 F01D015/10; F01D 25/24 20060101
F01D025/24; F01D 25/00 20060101 F01D025/00; F01D 25/28 20060101
F01D025/28 |
Claims
1. A rotational ducted fan (rdf) propulsion system for converting
stored electrical energy into aircraft thrust propulsion,
comprising: means for generally providing propulsion thrust to
power aircraft; means for providing an accelerated fluid flow
across inlet control surface to decrease fluid pressure, accelerate
fluid, and decrease upstream fluid pressure, creating lift; means
for creating thrust by converting rotational potential energy into
linear thrust, creating a pressure difference of the fluid upstream
of the propeller to the fluid downstream of the propeller, rigidly
connected to said means for providing an accelerated fluid flow
across inlet control surface to decrease fluid pressure, accelerate
fluid, and decrease upstream fluid pressure, creating lift; means
for providing an aerodynamic control surface for low velocity fluid
flow, with varying cord lengths of exterior aerodynamic design,
comprising of housing core to store electrochemical energy, and
providing the rigid static bearing housing that contains magnetic
levitation coils; means for converting rotational potential energy
into thrust energy by accelerating intake fluids such as air across
its dynamic intake control surface, creating a low pressure region
that results in forward lift, rigidly connected to said means for
creating thrust by converting rotational potential energy into
linear thrust, creating a pressure difference of the fluid upstream
of the propeller to the fluid downstream of the propeller, and
rigidly connected to said means for providing an accelerated fluid
flow across inlet control surface to decrease fluid pressure,
accelerate fluid, and decrease upstream fluid pressure, creating
lift; means for providing a repelling thrust bearing to enable 304
to levitate, and to have frictionless bearing rotation; means for
providing a controlled drag surface of external static air-foil of
propulsion motor, functionally constructed to said means for
providing an aerodynamic control surface for low velocity fluid
flow, with varying cord lengths of exterior aerodynamic design,
comprising of housing core to store electrochemical energy, and
providing the rigid static bearing housing that contains magnetic
levitation coils; means for providing magnetic thrust levitation
between the rotational ducted fan rotor and the static aft shroud;
means for providing an opposing magnetic force whereby the axial
rotation of the rotational ducted fan is generated,
circumferentially embedded to said means for providing an
aerodynamic control surface for low velocity fluid flow, with
varying cord lengths of exterior aerodynamic design, comprising of
housing core to store electrochemical energy, and providing the
rigid static bearing housing that contains magnetic levitation
coils; means for converting electrical energy into magnetic field
energy, insertably coupled to said means for providing an
aerodynamic control surface for low velocity fluid flow, with
varying cord lengths of exterior aerodynamic design, comprising of
housing core to store electrochemical energy, and providing the
rigid static bearing housing that contains magnetic levitation
coils; means for providing a magnetic field that acts against the
410 pulsor coil creating a levitating frictionless bearing; means
for providing a magnetic force field for the regenerative power
clutch; means for providing for electrochemical storage of
electrical power, stoichiometrically housed to said means for
providing an aerodynamic control surface for low velocity fluid
flow, with varying cord lengths of exterior aerodynamic design,
comprising of housing core to store electrochemical energy, and
providing the rigid static bearing housing that contains magnetic
levitation coils; means for providing a method for servicing the
electric coils and battery shroud segments, actively delineated to
said means for generally providing propulsion thrust to power
aircraft; means for providing for the storage of electrochemical
energy, converting electrical energy to magnetic fields, and
contributing to the directionally laminar thrust of downstream
fluid pressure; means for provide an adjoining mounting structure
that couples the top aft duct shroud 512 to an aircraft wing or
aircraft fuselage to provide propulsion power for the aircraft;
means for providing a solid hinge for hanging exactly two shroud
segments, replaceably connected to said means for providing for the
storage of electrochemical energy, converting electrical energy to
magnetic fields, and contributing to the directionally laminar
thrust of downstream fluid pressure; means for providing interface
mount that completes the containment of the fluid-flow, provides
aircraft mounting embodiment, provides hanger hinges or connections
for removable shroud segments, substantially connected to said
means for providing a solid hinge for hanging exactly two shroud
segments, substantially connected to said means for provide an
adjoining mounting structure that couples the top aft duct shroud
512 to an aircraft wing or aircraft fuselage to provide propulsion
power for the aircraft, and alternately constructed to said means
for providing an aerodynamic control surface for low velocity fluid
flow, with varying cord lengths of exterior aerodynamic design,
comprising of housing core to store electrochemical energy, and
providing the rigid static bearing housing that contains magnetic
levitation coils; means for providing a hanger clasp arrangement to
allow for installation and segment removal of the aft shroud
electrical storage segments from the aft shroud aircraft mount; and
means for providing the subsystems that comprise the rotational
ducted fan propulsion system, operationally encompassing to said
means for providing a method for servicing the electric coils and
battery shroud segments.
2. The rotational ducted fan (rdf) propulsion system in accordance
with claim 1, wherein said means for generally providing propulsion
thrust to power aircraft comprises an assembly of rotational ducted
fan rotor and shroud, made of nonferrous materials, aerodynamic for
airflow bi-pass 102 rotational ducted fan motor.
3. The rotational ducted fan (rdf) propulsion system in accordance
with claim 1, wherein said means for providing an accelerated fluid
flow across inlet control surface to decrease fluid pressure,
accelerate fluid, and decrease upstream fluid pressure, creating
lift comprises a dynamic airfoil, composite material, fluid
accelerating control surface, convex control surface 104 rotational
ducted fan inlet surface.
4. The rotational ducted fan (rdf) propulsion system in accordance
with claim 1, wherein said means for creating thrust by converting
rotational potential energy into linear thrust, creating a pressure
difference of the fluid upstream of the propeller to the fluid
downstream of the propeller comprises an airfoil with varying pitch
cord lengths, made of composite material, lightweight and strong,
affixed to inlet control surface of duct, a plurality of blades,
airfoil forward lift control surfaces 106 rotor propeller
blades.
5. The rotational ducted fan (rdf) propulsion system in accordance
with claim 1, wherein said means for providing an aerodynamic
control surface for low velocity fluid flow, with varying cord
lengths of exterior aerodynamic design, comprising of housing core
to store electrochemical energy, and providing the rigid static
bearing housing that contains magnetic levitation coils comprises
an aerodynamic exterior shape, smooth surfaces, alumina silica and
composite construction, adiabatic design considerations, varying
cord lengths for aerodynamic exterior to induce drag and increase
pressure aft of system, at least a partially hollow core, solid and
structurally rigid supporting magnetic repulsive field bearings 110
static aft shroud.
6. The rotational ducted fan (rdf) propulsion system in accordance
with claim 1, wherein said means for converting rotational
potential energy into thrust energy by accelerating intake fluids
such as air across its dynamic intake control surface, creating a
low pressure region that results in forward lift comprises an
aero-foil inlet 202 rotational ducted fan rotor inlet.
7. The rotational ducted fan (rdf) propulsion system in accordance
with claim 1, wherein said means for providing a repelling thrust
bearing to enable 304 to levitate, and to have frictionless bearing
rotation comprises a gap between rotational ducted fan rotor and
static aft shroud, frictionless 302 thrust magnetic field gap.
8. The rotational ducted fan (rdf) propulsion system in accordance
with claim 1, wherein said means for providing a controlled drag
surface of external static air-foil of propulsion motor comprises a
convex exterior, generally round, without voids or uncontrolled
wind-breaks 312 static aft shroud airfoil.
9. The rotational ducted fan (rdf) propulsion system in accordance
with claim 1, wherein said means for providing magnetic thrust
levitation between the rotational ducted fan rotor and the static
aft shroud comprises a plurality of neodymium magnets, arranged
circumferentially around axis 208 406 permanent thrust magnet.
10. The rotational ducted fan (rdf) propulsion system in accordance
with claim 1, wherein said means for providing an opposing magnetic
force whereby the axial rotation of the rotational ducted fan is
generated comprises a plurality of magnetic coils 410 levitation
magnetic coil.
11. The rotational ducted fan (rdf) propulsion system in accordance
with claim 1, wherein said means for converting electrical energy
into magnetic field energy comprises an electrical coil 412
magnetic thrust field control coil.
12. The rotational ducted fan (rdf) propulsion system in accordance
with claim 1, wherein said means for providing a magnetic field
that acts against the 410 pulsor coil creating a levitating
frictionless bearing comprises a plurality of neodymium magnets 414
permanent levitation bearing magnet.
13. The rotational ducted fan (rdf) propulsion system in accordance
with claim 1, wherein said means for providing a magnetic force
field for the regenerative power clutch comprises a neodymium
permanent magnets 416 regenerative clutch permanent magnet.
14. The rotational ducted fan (rdf) propulsion system in accordance
with claim 1, wherein said means for providing for electrochemical
storage of electrical power comprises an alumina silica shell,
battery chemistry 418 electrochemical conversion chamber.
15. The rotational ducted fan (rdf) propulsion system in accordance
with claim 1, wherein said means for providing a method for
servicing the electric coils and battery shroud segments comprises
a removable rotational ducted rotor, removable shroud batteries,
fixed top shroud mount, permanent hanger hinges 502 systemic
servicing detail.
16. The rotational ducted fan (rdf) propulsion system in accordance
with claim 1, wherein said means for providing for the storage of
electrochemical energy, converting electrical energy to magnetic
fields, and contributing to the directionally laminar thrust of
downstream fluid pressure comprises a removable, convex outer
exterior, comprising a number of magnetic coils 504 static aft
shroud electrochemical storage segment, having electrochemical
storage cavity.
17. The rotational ducted fan (rdf) propulsion system in accordance
with claim 1, wherein said means for provide an adjoining mounting
structure that couples the top aft duct shroud 512 to an aircraft
wing or aircraft fuselage to provide propulsion power for the
aircraft comprises a 508 aircraft mount, having aerodynamic
exterior shape.
18. The rotational ducted fan (rdf) propulsion system in accordance
with claim 1, wherein said means for providing a solid hinge for
hanging exactly two shroud segments comprises a solid high strength
bar, affixed to 508 mount segment 512 aft shroud segment hinge
rack.
19. The rotational ducted fan (rdf) propulsion system in accordance
with claim 1, wherein said means for providing interface mount that
completes the containment of the fluid-flow, provides aircraft
mounting embodiment, provides hanger hinges or connections for
removable shroud segments comprises a 514 upper aft shroud duct
segment.
20. The rotational ducted fan (rdf) propulsion system in accordance
with claim 1, wherein said means for providing a hanger clasp
arrangement to allow for installation and segment removal of the
aft shroud electrical storage segments from the aft shroud aircraft
mount comprises a cavity containing electrochemical materials for
storing electrical current in its core, comprising a composite hook
on the exterior of the shroud shell 606 aft serviceable shroud
segment.
21. The rotational ducted fan (rdf) propulsion system in accordance
with claim 1, wherein said means for providing the subsystems that
comprise the rotational ducted fan propulsion system comprises a
902 rdf propulsion system.
22. A rotational ducted fan (rdf) propulsion system for converting
stored electrical energy into aircraft thrust propulsion,
comprising: an assembly of rotational ducted fan rotor and shroud,
made of nonferrous materials, aerodynamic for airflow bi-pass 102
rotational ducted fan motor, for generally providing propulsion
thrust to power aircraft; a dynamic airfoil, composite material,
fluid accelerating control surface, convex control surface 104
rotational ducted fan inlet surface, for providing an accelerated
fluid flow across inlet control surface to decrease fluid pressure,
accelerate fluid, and decrease upstream fluid pressure, creating
lift; an airfoil with varying pitch cord lengths, made of composite
material, lightweight and strong, affixed to inlet control surface
of duct, a plurality of blades, airfoil forward lift control
surfaces 106 rotor propeller blades, for creating thrust by
converting rotational potential energy into linear thrust, creating
a pressure difference of the fluid upstream of the propeller to the
fluid downstream of the propeller, rigidly connected to said 104
rotational ducted fan inlet surface; an aerodynamic exterior shape,
smooth surfaces, alumina silica and composite construction,
adiabatic design considerations, varying cord lengths for
aerodynamic exterior to induce drag and increase pressure aft of
system, at least a partially hollow core, solid and structurally
rigid supporting magnetic repulsive field bearings 110 static aft
shroud, for providing an aerodynamic control surface for low
velocity fluid flow, with varying cord lengths of exterior
aerodynamic design, comprising of housing core to store
electrochemical energy, and providing the rigid static bearing
housing that contains magnetic levitation coils; an aero-foil inlet
202 rotational ducted fan rotor inlet, for converting rotational
potential energy into thrust energy by accelerating intake fluids
such as air across its dynamic intake control surface, creating a
low pressure region that results in forward lift, rigidly connected
to said 106 rotor propeller blades, and rigidly connected to said
104 rotational ducted fan inlet surface; a gap between rotational
ducted fan rotor and static aft shroud, frictionless 302 thrust
magnetic field gap, for providing a repelling thrust bearing to
enable 304 to levitate, and to have frictionless bearing rotation;
a convex exterior, generally round, without voids or uncontrolled
wind-breaks 312 static aft shroud airfoil, for providing a
controlled drag surface of external static air-foil of propulsion
motor, functionally constructed to said 110 static aft shroud; a
plurality of neodymium magnets, arranged circumferentially around
axis 208 406 permanent thrust magnet, for providing magnetic thrust
levitation between the rotational ducted fan rotor and the static
aft shroud; a plurality of magnetic coils 410 levitation magnetic
coil, for providing an opposing magnetic force whereby the axial
rotation of the rotational ducted fan is generated,
circumferentially embedded to said 110 static aft shroud; an
electrical coil 412 magnetic thrust field control coil, for
converting electrical energy into magnetic field energy, insertably
coupled to said 110 static aft shroud; a plurality of neodymium
magnets 414 permanent levitation bearing magnet, for providing a
magnetic field that acts against the 410 pulsor coil creating a
levitating frictionless bearing; a neodymium permanent magnets 416
regenerative clutch permanent magnet, for providing a magnetic
force field for the regenerative power clutch; an alumina silica
shell, battery chemistry 418 electrochemical conversion chamber,
for providing for electrochemical storage of electrical power,
stoichiometrically housed to said 110 static aft shroud; a
removable rotational ducted rotor, removable shroud batteries,
fixed top shroud mount, permanent hanger hinges 502 systemic
servicing detail, for providing a method for servicing the electric
coils and battery shroud segments, actively delineated to said 102
rotational ducted fan motor; a removable, convex outer exterior,
comprising a number of magnetic coils 504 static aft shroud
electrochemical storage segment, having electrochemical storage
cavity, for providing for the storage of electrochemical energy,
converting electrical energy to magnetic fields, and contributing
to the directionally laminar thrust of downstream fluid pressure; a
508 aircraft mount, having aerodynamic exterior shape, for provide
an adjoining mounting structure that couples the top aft duct
shroud 512 to an aircraft wing or aircraft fuselage to provide
propulsion power for the aircraft; a solid high strength bar,
affixed to 508 mount segment 512 aft shroud segment hinge rack, for
providing a solid hinge for hanging exactly two shroud segments,
replaceably connected to said 504 static aft shroud electrochemical
storage segment; a 514 upper aft shroud duct segment, for providing
interface mount that completes the containment of the fluid-flow,
provides aircraft mounting embodiment, provides hanger hinges or
connections for removable shroud segments, substantially connected
to said 512 aft shroud segment hinge rack, substantially connected
to said 508 aircraft mount, and alternately constructed to said 110
static aft shroud; a cavity containing electrochemical materials
for storing electrical current in its core, comprising a composite
hook on the exterior of the shroud shell 606 aft serviceable shroud
segment, for providing a hanger clasp arrangement to allow for
installation and segment removal of the aft shroud electrical
storage segments from the aft shroud aircraft mount; and a 902 rdf
propulsion system, for providing the subsystems that comprise the
rotational ducted fan propulsion system, operationally encompassing
to said 502 systemic servicing detail.
23. A rotational ducted fan (rdf) propulsion system for converting
stored electrical energy into aircraft thrust propulsion,
comprising: an assembly of rotational ducted fan rotor and shroud,
made of nonferrous materials, aerodynamic for airflow bi-pass 102
rotational ducted fan motor, for generally providing propulsion
thrust to power aircraft; a dynamic airfoil, composite material,
fluid accelerating control surface, convex control surface 104
rotational ducted fan inlet surface, for providing an accelerated
fluid flow across inlet control surface to decrease fluid pressure,
accelerate fluid, and decrease upstream fluid pressure, creating
lift; an airfoil with varying pitch cord lengths, made of composite
material, lightweight and strong, affixed to inlet control surface
of duct, a plurality of blades, airfoil forward lift control
surfaces 106 rotor propeller blades, for creating thrust by
converting rotational potential energy into linear thrust, creating
a pressure difference of the fluid upstream of the propeller to the
fluid downstream of the propeller, rigidly connected to said 104
rotational ducted fan inlet surface; a composite or generally
non-ferrous alloys, affixed to rotor propeller blade root inclusive
of both leading and trailing edge, cylindrical, axis of rotation is
parallel to cylindricity 108 center hub, for providing a monolithic
connection for all propeller blades, and comprising permanent
magnets to create magnetic field for coupling with regenerative
power clutch, rigidly connected to said 106 rotor propeller blades;
an aerodynamic exterior shape, smooth surfaces, alumina silica and
composite construction, adiabatic design considerations, varying
cord lengths for aerodynamic exterior to induce drag and increase
pressure aft of system, at least a partially hollow core, solid and
structurally rigid supporting magnetic repulsive field bearings 110
static aft shroud, for providing an aerodynamic control surface for
low velocity fluid flow, with varying cord lengths of exterior
aerodynamic design, comprising of housing core to store
electrochemical energy, and providing the rigid static bearing
housing that contains magnetic levitation coils; an aero-foil inlet
202 rotational ducted fan rotor inlet, for converting rotational
potential energy into thrust energy by accelerating intake fluids
such as air across its dynamic intake control surface, creating a
low pressure region that results in forward lift, rigidly connected
to said 106 rotor propeller blades, and rigidly connected to said
104 rotational ducted fan inlet surface; a gap between rotational
ducted fan rotor and static aft shroud, frictionless 302 thrust
magnetic field gap, for providing a repelling thrust bearing to
enable 304 to levitate, and to have frictionless bearing rotation;
a concave surface of airfoil 304 rotational ducted fan rotor, for
providing a concave airfoil surface to create drag for the forward
thrust, rigidly connected to said 202 rotational ducted fan rotor
inlet, rotationally connected to said 110 static aft shroud, and
magnetically housed to said 102 rotational ducted fan motor; a
textured surface, smooth, without disruptions, made of composite
material, lightweight and rigid 308 rotational leading edge, for
providing a forward control surface comprised at the leading edge
of the rotational ducted fan rotor 202 at its forward most edge,
and acting as a fluidic gate that creates an orbital low pressure
surface causing forward (upstream) lift, rigidly connected to said
202 rotational ducted fan rotor inlet, and rigidly connected to
said 104 rotational ducted fan inlet surface; a smooth surface,
parallel inner control surface to axis of rotation 208 310 aft
shroud exit surface, for contributing to laminar flow of exit fluid
pressure with no eddie current disruptions; a convex exterior,
generally round, without voids or uncontrolled wind-breaks 312
static aft shroud airfoil, for providing a controlled drag surface
of external static air-foil of propulsion motor, functionally
constructed to said 110 static aft shroud; a solid, composite 402
static duct bi-directional thrust bearing. structure, for provide a
strong and light weight structure to mount magnetic coils and
connectors, structurally constructed to said 110 static aft shroud;
a plurality of neodymium magnets, arranged circumferentially around
axis 208 406 permanent thrust magnet, for providing magnetic thrust
levitation between the rotational ducted fan rotor and the static
aft shroud, circumferentially fastened to said 304 rotational
ducted fan rotor; a plurality of magnetic coils 410 levitation
magnetic coil, for providing an opposing magnetic force whereby the
axial rotation of the rotational ducted fan is generated,
circumferentially embedded to said 110 static aft shroud; an
electrical coil 412 magnetic thrust field control coil, for
converting electrical energy into magnetic field energy, insertably
coupled to said 110 static aft shroud; a plurality of neodymium
magnets 414 permanent levitation bearing magnet, for providing a
magnetic field that acts against the 410 pulsor coil creating a
levitating frictionless bearing, rigidly embedded to said 304
rotational ducted fan rotor; a neodymium permanent magnets 416
regenerative clutch permanent magnet, for providing a magnetic
force field for the regenerative power clutch, rigidly embedded to
said 108 center hub; an alumina silica shell, battery chemistry 418
electrochemical conversion chamber, for providing for
electrochemical storage of electrical power, stoichiometrically
housed to said 110 static aft shroud; a removable rotational ducted
rotor, removable shroud batteries, fixed top shroud mount,
permanent hanger hinges 502 systemic servicing detail, for
providing a method for servicing the electric coils and battery
shroud segments, actively delineated to said 102 rotational ducted
fan motor; a removable, convex outer exterior, comprising a number
of magnetic coils 504 static aft shroud electrochemical storage
segment, having electrochemical storage cavity, for providing for
the storage of electrochemical energy, converting electrical energy
to magnetic fields, and contributing to the directionally laminar
thrust of downstream fluid pressure; a 508 aircraft mount, having
aerodynamic exterior shape, for provide an adjoining mounting
structure that couples the top aft duct shroud 512 to an aircraft
wing or aircraft fuselage to provide propulsion power for the
aircraft; a solid high strength bar, affixed to 508 mount segment
512 aft shroud segment hinge rack, for providing a solid hinge for
hanging exactly two shroud segments, replaceably connected to said
504 static aft shroud electrochemical storage segment; a 514 upper
aft shroud duct segment, for providing interface mount that
completes the containment of the fluid-flow, provides aircraft
mounting embodiment, provides hanger hinges or connections for
removable shroud segments, substantially connected to said 512 aft
shroud segment hinge rack, substantially connected to said 508
aircraft mount, and alternately constructed to said 110 static aft
shroud; a cavity containing electrochemical materials for storing
electrical current in its core, comprising a composite hook on the
exterior of the shroud shell 606 aft serviceable shroud segment,
for providing a hanger clasp arrangement to allow for installation
and segment removal of the aft shroud electrical storage segments
from the aft shroud aircraft mount; a 612 aft shroud mounting
hooks, for provided for connecting serviceable shroud segments to
upper shroud segment enabling serviceable motion and removal,
rigidly connected to said 606 aft serviceable shroud segment, and
removably connected to said 512 aft shroud segment hinge rack; a
702 rotational ducted fan propulsion systems application drawing,
for providing an example for a variety of propulsion mounting
locations on aircraft; a 710 fuselage, for providing for cargo,
persons, or equipment occupation; a 902 rdf propulsion system, for
providing the subsystems that comprise the rotational ducted fan
propulsion system, operationally encompassing to said 502 systemic
servicing detail; and a 906 iterative current control module
(iccm), for providing the electro-magnetic field cycle on-off
switching between coils, actively encompassing to said 902 RDF
Propulsion System, electrically connected to said 412 magnetic
thrust field control coil, and electrically connected to said 410
levitation magnetic coil.
Description
RELATED APPLICATIONS
[0001] The present application is a continuation application of
U.S. patent application Ser. No. 14/095,737, filed Dec. 3, 2013,
for ROTATIONAL DUCTED FAN, OR RDF FAN MOTOR, by Devin Glenn
Samuelson, included by reference herein and for which benefit of
the priority date is hereby claimed.
FIELD OF THE INVENTION
[0002] The present invention relates to an aircraft propulsion
system, and more particularly to a novel rotational inlet shroud,
and additionally to an energy storage and maintenance system.
BACKGROUND OF THE INVENTION
[0003] For each barrel of crude oil refined, approximately only 4
gallons of jet fuel are realized. Specific to aircraft fuel, there
is a limited global supply of the natural resource of carbon based
fuels such as oil. In consideration of other hybrid systems or
alternative biofuel systems, the problem of supply and dependence
on these types of natural resources creates new economic challenges
such as increased consumable costs due to competing markets,
consumable shortages, or even climate disruptions. Given the
current path as the global economy increases the supply and demand
of oil creates significant risks for economic stability
internationally. This strain stems from an imbalanced use of
natural resources and too high of dependence on non-renewable
energy sources. The carbon footprint of aircraft is negatively
impacting the environment from both an atmospheric output of
propulsion exhaust, and the extraction and refinery processes of
petroleum or biofuels. A typical 150 passenger aircraft consumes an
average of about 100 lbs of carbon based fuel per minute, or
otherwise stated, nearly 15 gallons per minute. This realization
has set in motion the quest for improved efficiency and technology
for the development of electrical propulsion systems which use
electrical energy that may be derived and stored from a number of
other alternative or renewable methods. In addition to the type of
energy resource to use, consideration must be given to the
supporting infrastructure that will be necessary to support the
operation of such new machines in a commercial transportation
industry. Other problems that exist with combustion type systems
include design restrictions to accommodate a safe combustible
containment structure that facilitates the need for only using
static fluid containment systems, thus limiting efficiency to be
achieved primarily through focused attention to fluid density,
achieved through compressors, entropy, and static nozzle designs
historically.
[0004] Other aircraft propulsion systems currently include
carbon-fueled combustion methods of propulsion such as combustion
jet engines, turbo-fan engines, turbo-prop engines, and liquid or
solid rocket fuel systems. Additionally, electric ducted fan motors
are used in the model radio controlled airplane industry.
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[0044] No other solutions in existence today address the three
problems that the rotational ducted fan propulsion motor addresses.
The use of a static inlet shroud of traditional gas or electric
ducted fan motors does not allow the maximum pressure differentials
to be achieved between the inlet and the aft exhaust of the system.
Additionally, it is common for traditional gas or electric ducted
fan motors and propeller propulsion systems to experience
efficiency losses at the outer blade tips which results in axial
propulsive thrust losses. The operational costs for current carbon
fueled combustive propulsion systems are extravagant, for example,
with 150 passenger aircraft consuming nearly 15 gallons per minute
of a non-renewable fuel source will have economic consequences to
future generations, combustive propulsion systems generate noise
that creates weight inefficiencies since noise reduction becomes an
integral part of the design, and reverse thrust systems are
required.
[0045] Electric ducted fan systems have shortcomings too.
Traditional electric ducted fan motors rely on a separate battery
source which results in energy losses through wire resistance
caused from separating batteries or stored energy some distance
away from its point of use. Traditional electric fan motors have a
static shroud and a dynamic hub which the aero foil blades are
attached, which contributes to airflow energy losses at the blade
tips, similarly to those losses experienced by combustive
propulsion systems.
SUMMARY OF THE INVENTION
[0046] In accordance with the present invention, an embodiment of a
rotational ducted fan motor comprises a monolithic rotational
ducted fan rotor, an electric propulsion system, a static
aft-shroud comprising electrochemical-energy-storage, and an
engagement system. The rotational ducted fan rotor is the portion
of a ducted fan motor comprising a propeller, a duct, and a center
hub, and having the effect of increasing the pressure difference
from upstream to downstream of the propeller. The electric
propulsion system comprises permanent magnets affixed to the
rotational ducted fan rotor, repelling magnetic coils affixed to
the static aft-shroud and electrical power provided by the
electrochemical-energy-storage comprised within the aft-shroud.
[0047] In another advantageous embodiment, an aft-shroud comprises
one mounting section that houses electrical controls and has
mounting hanger bars for a hook and latch connection and engagement
system of the two replaceable electrochemical storage aft-shroud
segments, wherein the electrochemical storage segments of the
aft-shroud having the effect of heat exchangers and electrical
supply systems for the propulsion system.
[0048] It would be advantageous to provide a machine to convert
electrical energy to thrust.
[0049] It would also be advantageous to provide an object to create
a fluid pressure difference, decreases pressure at the inlet and
increases pressure aft of the system.
[0050] It would further be advantageous to provide an object that
converts electrical power into mechanical rotational work with
magnetic fields.
[0051] It would further be advantageous to provide a machine that
utilizes heat energy created from electrochemical activation into
enthalpy with laminar fluid flow at the aft-duct exit nozzle.
[0052] It would be an object of the invention to provide a method
for reducing the aircraft non-operational down-times with
interchangeable rechargeable electrochemical storage duct
segments.
BRIEF DESCRIPTION OF THE DRAWINGS
[0053] A complete understanding of the present invention may be
obtained by reference to the accompanying drawings, when considered
in conjunction with the subsequent, detailed description, in
which:
[0054] FIG. 1 is a perspective view of a rotational ducted fan
motor;
[0055] FIG. 2 is a front view of a rotational ducted fan motor;
[0056] FIG. 3 is a left view of a rotational ducted fan motor;
[0057] FIG. 4 is a right sectional view of a rotational ducted fan
motor;
[0058] FIG. 5 is a perspective view of a method of assembly for the
rotational ducted fan motor;
[0059] FIG. 6 is a rear section view of an embodiment of a
serviceable aft duct shroud;
[0060] FIG. 7 is a perspective view of an example aircraft and its
applicable rotational ducted fan motor installation
arrangements;
[0061] FIG. 8 is a plan view of a flow diagram for producing a
commercial rotational ducted fan propulsion system; and
[0062] FIG. 9 is a plan view of a rotational ducted fan system with
interactions to other associated systems.
[0063] For purposes of clarity and brevity, like elements and
components will bear the same designations and numbering throughout
the Figures.
DESCRIPTION OF THE PREFERRED EMBODIMENT
[0064] FIG. 1 is a perspective view of a rotational ducted fan
motor. Referring more particularly to the drawings, embodiments of
the disclosure may be described in the context of an aircraft
propulsion system. The embodiment shown in FIG. 1 comprises a
static non-rotating aft duct 110, and a rotational ducted fan 202.
The rotational ducted fan is described as a dynamic rotor that
rotates about an axis parallels to its thrust, and is comprised of
an outer shroud or duct that is dynamic and rotates orbitally about
a center axis that is parallel to its generally cylindrical shape,
and concentric to a center hub and an arrangement of a plurality of
propeller blades or airfoils axially perpendicular to the axis of
rotation. The rotational ducted fan or orbital fan duct is
comprised of a cylinder that has a plurality of propeller blades
affixed axially at their substantially larger diameter or blade tip
to the inner surface of an approximately cylindrically shaped duct.
There may be a center hub that enables its outside diameter to be
attached to the least significant diameter of a plurality of
axially arranged propeller blades to adjoin essentially two rings,
an outer and an inner ring by a plurality of blades between these
two rings concentrically about a shared axis. At the least
significant or smallest diameter, an airfoil entry lip 104 rotates
tangentially to incoming fluid flow to create forward lift, while
its affixed propeller blades are creating a forward vacuum and aft
thrust pressure 106 as they rotate about axis 108.
[0065] FIG. 2 is a front view of a rotational ducted fan motor.
Referring to the rotational ducted fan motor, FIG. 2 illustrates
the forward component of the system, the rotational ducted fan
monolithic rotor. With reference to FIG. 2, the control surfaces
are of an aerodynamic nature and designed to create forward lift at
104 and the plurality of 106 as these surfaces both rotate
coaxially about the axis 208, while circumferentially creating aft
thrust pressure delta.
[0066] FIG. 3 is a left view of a rotational ducted fan motor.
Referring to the drawing embodiment of FIG. 3, the advantageous
embodiment of the rotational ducted fan inlet lip 308 creates a
fluidic accelerant for bypass with a drag component airfoil
convexly situated generally outside the rotational duct 104. The
dynamic rotor 202 and static shroud 110 are independent of each
other, whereby they are separated by a magnetic force field gap
302. Pursuant to the repulsion of the magnetic fields, FIG. 4
provides details of the novel energy conversion machine.
[0067] FIG. 4 is a right sectional view of a rotational ducted fan
motor. Referring to FIG. 4, comprising an aft static duct 110, an
orbiting rotational ducted fan rotor 202, and various arrangements
of neodymium permanent magnets 406 and 414, and various
arrangements of magnetic coils 410 and 412 that work as a system to
create kinetic energy from magnetic fields. Further, FIG. 4 shows
the electrochemical current storage cell cavity 418 as comprised in
the static aft duct.
[0068] FIG. 5 is a perspective view of a method of assembly for the
rotational ducted fan motor. More particularly, FIG. 5 shows the
assembly of how a rotational ducted fan rotor 202 is housed by its
static aft shroud or duct housing. In another embodiment 502, the
static aft shroud or duct is segmented into at least two parts,
whereby one of the segments mounts to an aircraft 514 and 508, and
comprises a hinge, such as is shown in example element 512, that
allows servicing or removal of at least one other static aft shroud
or duct housing segment 504.
[0069] FIG. 6 is a rear section view of an embodiment of a
serviceable aft shroud or aft duct. Referring to FIG. 6. the two
rear aft shroud duct segments area shown in as an embodiment
section 606 with an integrated crook hook 612 that assembles onto a
hinge hanger 512. This method of design embodiment allows for
servicing by lifting the panels to an open or removable position,
and enables the release of the magnetically suspended rotational
ducted fan rotor 202 for removal or replacement as shown in FIG.
5.
[0070] FIG. 7 is a perspective view of an example aircraft and its
applicable rotational ducted fan motor installation arrangements.
In an embodiment shown, an aircraft refers to any aerial form of
cargo transportation whereby there is a fuselage or hull 710. In
the embodiment example shown in FIG. 7, a fixed wing aircraft 702
receives propulsion rotational ducted fan (RDF) motors 102 mounted
to fixed wings 708, or to fuselage 710. In another embodiment, a
vertical take-off aircraft will also benefit from the advantageous
electrical thrust energy to propel the vehicle.
[0071] FIG. 8 is a plan view of a flow diagram for producing a
commercial rotational ducted fan propulsion system. Referring to
FIG. 8, the seven steps of the process necessary to producing the
rotational ducted fan propulsion system and implementing it into
service, beginning with the design phase 804 whereby Electrijet
Flight Systems holds the design authority and design rights for use
of the rotational ducted fan rotor in conjunction with an aft duct
assembly 102 or any rotational monolithic shrouded propeller with
inserted permanent magnets and electrical coils for use in creating
resistant magnetic fields to create tangential rotational energy.
All materials are procured or manufactured within the production
authority of Electrijet Flight Systems 806 and 808 respectively.
Systems integration of the rotational ducted fan propulsion system
810 comprises input from airframe manufacturers or retrofit
companies, and whereby Electrijet Flight Systems customizes design
and application to create required thrust, weight, size, mounting,
requirements for said users. Federal Aviation Authority application
for Title 14 CFR requirements may be conformed to and certified to
support commercial use of the said rotational ducted fan motor for
aircraft propulsion 812. While there is a constant need for rapid
travel for longer ranges, some flight paths require intermittent
stopping points for servicing. The in-service capabilities of an
embodiment of a rotational ducted fan motor lends itself to the
removal and replacement of the rotational ducted fan motor 110 and
its static aft duct 310 segments 606 to enable cool-down periods
for permanent magnets and magnetic coils as well as replacement of
static duct segments which are fully electrically charged with
stored current in the electrochemical storage cavity 418. This
advantageous embodiment provides for easy maintenance access for
servicing and periodic reviews, maintenance manuals, operating
manuals, service bulletins, airworthiness advisories, and RF
disturbance protections 816.
[0072] FIG. 9 is a plan view of a rotational ducted fan system with
interactions to other associated systems. Referring to FIG. 9, the
three primary systems comprising the rotational ducted fan
propulsion system are shown 902. Comprising the embodiment of 902,
a rotational ducted fan rotor 304 comprised of a composite inlet
lip, thrust propeller 106, and permanent magnets 406 and 414. An
aft shroud housing duct 110 comprised of composite may also wrap an
alumina core housing of an electrochemcial current storage and
transfer device enables use of a regenerative magnetic speed clutch
shaft supported on a laminar airfoil blade that is affixed in an
advantageous embodiment that enables a rigid connection to exactly
one segment of the aft shroud 508. The magnetic coils 412 and 410
receive their systems energy from the electro-chemical storage and
dispersement of 418, and are replaceable in the embodiment 606. The
controls for the release of the energy to the coils is governed by
an electrical distribution system 906.
[0073] Since other modifications and changes varied to fit
particular operating requirements and environments will be apparent
to those skilled in the art, the invention is not considered
limited to the example chosen for purposes of disclosure, and
covers all changes and modifications which do not constitute
departures from the true spirit and scope of this invention.
[0074] Having thus described the invention, what is desired to be
protected by Letters Patent is presented in the subsequently
appended claims.
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