AERIAL CENTRIFUGAL IMPELLER

Abstract

An impeller includes a lower dome having a curved outer surface. Disposed on the curved outer surface of the lower dome is a plurality of blade. The blades are formed to define an inner curved surface and an outer curved surface, each blade having a leading edge and a terminal edge. The impeller comprises an an upper dome, the inner surface of which is mounted on the outer curved surfaces of the blades; The upper dome has an annular opening formed therethrough. The annular opening of the upper dome is coaxially positioned with an annular bore in the lower dome. The annular bore is sized for receiving a rotary shaft. A plurality of flow compartments or chambers are defined in the conjunction of the lower dome, the plurality of blades, and the upper dome. An embodiment of the impeller comprises a rotary shaft in connection between at least the annular bore of the lower dome on one end and a motor on the other.

Description

The present invention relates to an impeller for efficient production of thrust.

A centrifugal impeller—a device similar to a rotor quickly draws a flow of mass into a small housing. As the flow (e.g. gaseous material) is drawn in at the hub of the impeller, centrifugal force causes it to radiate outward. The flow leaves the impeller at high speed, and high pressure.

At its most basic, a centrifugal air impeller is driven off a shaft connected to a motor. Impellers ideally achieve a pressure rise by adding kinetic energy/velocity to a generate a continuous flow of mass through the rotor or impeller. This kinetic energy is then converted to an increase in potential energy/static pressure.

It is the impeller's rotating set of vanes (or blades) that gradually raises the energy of the working gas. This is identical to an axial compressor with the exception that the gases can reach higher velocities and energy levels through the impeller's increasing radius. Impellers are designed in many configurations including “open” (visible blades), “covered or shrouded”, “with splitters” (every other inducer removed) and “w/o splitters” (all full blades). Most modern high efficiency impellers use “backsweep” in the blade shape.

Traditional rotor blade technology produces thrust by pushing the flow. In contrast, the ACI accelerates the mass of the flow via centrifugal forces. Note: As the rotor spins, centrifugal forces act on the mass of the flow subsequently accelerating it. This creates a vacuum drawing more flow mass through the hub intake hole on top of the rotor outward toward the bottom of the device generating lift. As the flow releases below the rotor, lift is enhanced.

SUMMARY

The present invention comprises an impeller. The structure of the impeller includes a lower dome having a curved outer surface. Disposed on the curved outer surface of the lower dome is a plurality of blade. The blades are formed to define an inner curved surface and an outer curved surface, each blade having a leading edge and a terminal edge.

The impeller comprises an an upper dome, the inner surface of which is mounted on the outer curved surfaces of the blades; The upper dome has an annular opening formed therethrough. The annular opening of the upper dome is coaxially positioned with an annular bore in the lower dome. The annular bore is sized for receiving a rotary shaft.

A plurality of flow compartments or chambers are defined in the conjunction of the lower dome, the plurality of blades, and the upper dome.

Accordingly, an embodiment of the impeller comprises a rotary shaft in connection between at least the annular bore of the lower dome on one end and a motor on the other.

In an embodiment of the device, blades are not exposed. This bladeless configuration provides a consistent surface during rotation which eliminates energy lost as turbulence. Significantly less energy is lost in the form of sound energy thus enabling relatively silent operation.

Objectives of General Structure and Function

The structural elements of the device generate centrifugal forces to generate thrust. As the device spins, the inlet flow accelerates into a radially disposed set of flow compartments defined by blades which are essentially flow compartment walls. The flow compartments guide the flow toward the exhaust vent, the exhaust flow acting as thrust generated by the operation of the device.

As the rotor spins, centrifugal forces act on the mass of the flow subsequently accelerating it. This creates a vacuum drawing more mass through the intake hole on top of the rotor, accelerating the flow vis a vis the flow compartments outward and toward the bottom of the device generating lift. The flow released below the device enhances lift.

In one embodiment, the rotor can be constructed primarily from low-weight high-strength fabrics including but not limited to Kevlar™, Spectra™, Nylon, and Carbon Nano Tubes. As the rotor spins, the intake flow mass expands the walls made of such fabric, the form and shape of the compartments as described herein.

The device of the invention relies primarily on centrifugal forces to generate thrust, and not exposed blades which “chop” the air resulting in energy lost as turbulence and sound energy.

In rotor blade technology, the present invention has applications that replace the props on airplanes, multirotor vehicles, helicopters, and watercraft; further uses involve replacement of traditional fan blades for ultra silent applications.

BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS

The foregoing summary, as well as the detailed description of the preferred embodiments of the present invention, will be better understood when read in conjunction with the appended drawings. For the purpose of illustrating the invention, there is shown in the drawings, which are diagrammatic, embodiments that are presently preferred. It should be understood, however, that the present invention is not limited to the precise arrangements and instrumentalities shown. In the drawings:

FIG. 1 is a perspective top view of the invention.

FIG. 2 is a perspective bottom view of the invention.

FIG. 3 is a perspective top lateral view of the invention.

FIG. 4 is a perspective side view of the invention.

FIG. 5 is a cross section view taken through line Y-Y of FIG. 4.

FIG. 6 is a bottom lateral view of the invention.

FIG. 7 is a bottom lateral view of the invention illustrating the ACI mounted on a portion of an impeller shaft.

FIG. 8 is a schema of the present invention.

DETAILED DESCRIPTION OF THE INVENTION

Certain terminology is used in the following description for convenience only and is not limiting. The words “inner”, “inwardly” and “outer”, “outwardly” refer to directions toward and away from, respectively, a designated centerline or a geometric center of an element being described, the particular meaning being readily apparent from the context of the description.

Referring now to the drawings and diagrams in detail, wherein like numbers are used to indicate like elements throughout, there is shown in FIGS. 1-7 the device of the invention, i.e. an impeller for accelerating flows of gas or liquid media.

Referring to FIGS. 1, 2, 3, 4, and 6 the impeller assembly basically comprises a first, main, upper dome 15 and a second lower dome 20 spaced apart and attached to upper or outer 30 and lower or inner 35 mounting surfaces of integrally formed compartment walls (blades) 25 to substantially form an impeller. The dimensions of the domes comply with formulae as described below.

The Main (Upper) Dome

The main dome 15 has a central axis 40, upper and lower axial ends 45, 50, a rim surface 51 of a central opening 9 which its diameter is depicted by an imaginary line 52 at a position defined by an intersecting plane (flat disk plane) 55 through the upper surface of the main dome. Accordingly, the upper dome represents a domed surface with a planer top 20 the position of which is defined by intersecting plane 55.

The main dome, which has upper 90 and lower 95 surfaces, includes radially-outermost portions 60. Accordingly, the dome comprises two parts: a flat disk-shaped opening 9, which is joined to a convex surface 65 with a gradual curvature and the base 70 of which has a circular boundary.

The main dome accordingly has a diameter D (FIG. 1) and a height H, as shown in FIG. 3. The diameter refers to the size of the base 70, whereas the height refers to the perpendicular distance between the center of the base and the center of the planar central opening.

The Lower Dome

A lower dome 20 is positioned axially below the main, upper dome 15. The planes of the lower rim or base surfaces 75 of the main dome and lower dome are approximately in the same plane. The lower dome is generally dimensioned to be positioned below the main dome and within the size limits of the invention. In one embodiment, the lower dome's roof 59 is formed as a disk which has roughly the dimensions of the base of a spherical cap formed from said lower dome.

Blades or Compartment Walls

A plurality of blades 25 or compartment walls 25 extend between and connect the main dome 15 and the lower dome 20. The plurality of blades are spaced apart circumferentially about the co-axial axis 40 of the upper and lower domes, in particular, circumferentially about the disked roof 58 of the lower dome such that each blade extends generally radially with respect thereto.

Each blade 25 has a planar shape of an arch, having two, opposing arch-shaped sides being inner 35 and outer 30 curves which define, in part, the planar area of the blade. The proximal and distal boundaries of the blade are defined by a leading edge 80 and a terminal edge 85. Each blade extends generally radially between the leading edge 80 and terminal edge 85 which are respectively the radially innermost and outermost portion of the edge surfaces.

The lower surface 95 of the main dome 15 is disposable simultaneously generally against the mounting surface of the outer 30 curve S_M of all of the plurality of blades, as described in further detail below.

The upper surface 105 of the inner or lower dome is disposable simultaneously generally against the inner curve mounting surfaces 35 S_M of all of the plurality of blades, as described in further detail below.

Inlets-Outlets

Each inlet or access opening 110 of a flow compartment 115 is defined between a separate pair of adjacent blade leading edge 80 surfaces and extends in height H_B between the upper 129 and lower 128 mounting points on the upper surface 105 of the lower dome extending in height H_B to the lower surface 95 of the upper dome.

Main Inlet—Central Opening Hub 9

The outer dome has an axially oriented circumferential opening 9 defining a rim 51 or inner edge circumferential surface defining a disk-shaped central opening through the roof the main dome.

The upper surface 105 of the impeller inner dome 20 forms the floor 120 of each flow compartment 115. The main dome inner (lower) surface 95 is disposable generally against the outer curves 30 of the blades so as to form the roof 125 of the flow compartments.

The inner dome includes a generally annular inner circumferential edge surface in which is defined a central opening (collet) 130. The collett is preferably a through bore extending axially through the roof of the inner dome. At least a portion of an impeller shaft 135 is disposable within the inner and/or outer dome to couple the impeller with a machine.

FIGS. 1, 3 show in general that the main opening 9 is defined by an annular space formed thru the main dome.

Further, the plurality of blades extends between and integrally connect the main and lower domes, thus forming the unitary body of the impeller.

Blades

Each blade 25 generally has a thickness commensurate with the material of the blade and the degree of force it is expected to endure from both the density of the flow medium and speed of operation. Blade thickness may vary from about 0.7 mm to about 1 inch depending on the material and operational requirements of the device.

Each blade body has a radially-innermost portion 80 disposed between the hub portion 9 and the flow compartments 115 such that a radially-innermost section leading edge surface 80 of adjacent blade bodies are set in a plane that defines the surface area of the entrance (inlet) 82 to each flow compartment 115 in combination with the height H_B of each blade extending from the blades respective attachment points between the mounting surfaces of the main and lower domes.

Mass Flow

In a flow path, mass passing through the flow compartments 115 is directed in a partly tangential direction with respect to the surfaces of the main and lower domes which form, respectively, the roof 125 and floor 120 of each flow compartment.

Structural Dimensions of the Impeller

A variety of device embodiments within the scope of the present invention are defined by the schema shown in FIG. 8.

The primary intake 9 cross-sectional area of Circle with diameter of D₁ is πr².

The primary area intake cross-sectional area is set to equal the secondary intake 110 cross-sectional area (2πr) (H).

The exhaust cross-sectional area 141 is understood as πr²{D3}−πr²{D2}.

The device of the invention conforms to: Primary (Main) Intake Area=Secondary Intake Area=Exhaust Area

πr²=(2πr(H)=πr²{D3}−πr²{D2}

Area of primary intake equals the area of the Circle defined by D1=Secondary Intake, that is, the product of the circumference of the D1 Circle and height H_B=Exhaust, which is the Area of circle D3 less the area of circle D2.

The above parameters of the device are derived as follows:

Step 1: One starts with a Circle D₁ of diameter D1

Step 2: The Circle D₁ is divided into quadrants.

Step 3: Remove half of the area of Circle D₁ denoted by a circular circumscription positioned in the center of Circle D₁.

Step 4:

(a) One of the four sections of Circle D₁ peripheral to the circumscription is selected.

(b) The area of the entrance to the secondary intake is set by adjusting Height “H_B ” so that the surface area of the entrance to the secondary intake equals the surface area of Circle D₁ in Step 1. The area of the secondary intake is calculated by multiplying the circumference of Circle D₁ in Step 1 “H_B”

(c) The exhaust area “W” is set to equal area of Circle D₁ in Step 1

(d) One draws a curve from the top of H_B to W so that the volume of the compartment communicating between the secondary intake and the exhaust portal is continuously equal from intake to exhaust portal.

Step 5: The compartment's cross-sectional shape 25 resulting from Step 4 is identified in FIG. 5. Compartment walls are positioned equally around D1.

FIGS. 3 and 5 are views of the device which illustrate the positioning of the compartment walls (blades) 25.

A plurality of walls are positioned and spaced equally spaced around the hub. A main dome is positioned atop the flow compartments, the curve of the inner surface of the main dome defines and conforms to the arch profiles of the compartment walls.

Ducting 140 is positioned around the circumferential base 70 of the main dome, the height of the ducting equal to W.

Operation of the Aerial Impeller

For purposes of explanation but not limitation, the operation of the aerial impeller is described in stages as follows:

In Stage 1 of the flow path, vacuum pressure generated in the device flow compartments during rotation draws flow first through the hub 9 or main intake.

The surface area of the main intake must be consistent with both the planar surface areas of the secondary intake(s) 110 collection of flow compartments 115 and exhaust planar surface area. The surface area of the central opening 9 intake(s) is described with the formula πr².

In Stage 2 of the flow path, vacuum pressure generated in the device flow compartments during rotation draws flow secondly through the flow compartment inlets 110.

The surface of the flow compartment inlets 110 must be consistent with both the surface area of main intake 9 and exhaust 141 [planar collection of exhaust surface areas].

The surface area of flow compartment inlets 110 can be calculated with the formula 2πrH where the circumference of the main intake 9 is multiplied by the height “H_B” of the compartment inlets 110.

In Stage 3 of the flow path, the rotating unit centrifugally accelerates flow thru the flow compartments 115 as defined by a plurality of flow compartment walls 25 located equally around the device. Flow compartment walls 25 in combination with lower 105 and upper surfaces 95 respectively of the main and lower domes define the dimensions of each flow compartment 115.

The purpose of the main dome and lower dome is to guide the flow as it accelerates thru and across the compartment walls 25 toward the flow exhaust 141.

In Stage 4 of the flow cycle, the accelerated flow, generated by the rotating unit exits from the flow exhaust 141 as thrust. The surface area (of an imaginary plane in the exhaust portal) of the exhaust 141 must be congruent with both the planar surface area of main intake 9 and compartment inlets 110. [i.e. same surface area of secondary intake and primary intake].

The surface area of the exhaust 141 can be calculated with the formula πr²{D3}−πr² {D2} where D3 corresponds to the surface area of an imaginary circular plane located at the base of the lower dome and D2 corresponds to the surface area of an imaginary circular plane located at the base of the bottom of hub 20, which is the roof of the lower dome, both depicted in FIG. 2.

The direction of the flow is then enhanced by the flow exhaust ducting 140. The height U of the flow exhaust ducting should be equivalent to the distance W [i.e. W=U] between the bottom edge of the main dome 70 and the hub. This ensures the flow will flow parallel to the primary intake.

It should be evident that the ACI finds use in turbines, turbo fans, silent fans, rotor blade replacement (helicopters, single engine planes, hobby grade/size vehicles), water pumps, hybrid air/water propulsion, ceiling fans, house fans, hover crafts, vacuum cleaners, leaf blowers, bi-rotor “tail-rotorless” vertical takeoff and landing (vtol) aircraft, centrifugal impellers, Dyson® vacuum, and vacuum pumps.

The device can be effectively fabricated with a range of material including light weight fabrics such as nylon, Kevlar or spectra depending on intensity of the application.

Embodiments of the device are used in applications including but not limited to aircraft rotors, helicopter rotors, multi-copter rotors, silent fans, ceiling fans, pumps, vacuums, air conditioning units, submarine propellers, boat propellers, Jet Ski propellers, and any application which requires accelerating a flow of mass.

It will be appreciated by those skilled in the art that changes could be made to the embodiments described above without departing from the broad inventive concept thereof. It is understood, therefore, that this invention is not limited to the particular embodiments disclosed, but it is intended to cover modifications within the spirit and scope of the present invention as defined in the appended claims.

Claims

1. An impeller comprising wherein a plurality of flow chambers are defined in the conjunction of said lower dome, said plurality of blades, and said upper dome.

a. a lower dome having a curved outer surface wherein an annular bore is formed therethrough;

b. a plurality of blades circumferentially disposed on said curved outer surface of said lower dome, wherein each of said blades has an inner curved surface, an outer curved surface, a leading edge and a terminal edge;

c. an upper dome having an annular opening formed therethrough, said upper dome having an interior surface mounted on the outer curved surfaces of said blades;

2. The impeller of claim 1 further comprising a shaft positioned in at least said annular bore of said lower dome.

3. The impeller of claim 2 further comprising a motor operationally connected to a motor.