TURBOFAN JET ENGINE, POWERED BY AN ELECTRIC MOTOR WITH POWER FROM A HIGH EFFICIENCY ELECTRIC GENERATOR

Abstract

A power system for an aircraft engine provides rotational drive to propeller driven and turbofan jet engine powered aircraft by use of a propeller or fan drive motor. Electrical power is provided to the drive motor by a high efficiency electrical power generator with reduced electromagnetic drag or reverse torque. The electric generator utilizes a solid state rotor that does not rotate which allows for power generation without reverse torque or the usual energy required to rotate the rotor inside the stator of the generator. Only the magnetic poles of the disclosed rotor rotate to generate the power. The fan blades of the turbofan jet engine are driven by the electric drive motor in which the rotor is a part of the fan as well as the drive from the high pressure turbine.

Claims

1. An airplane engine system, comprising: a circular electric motor coupled to a fan of a turbofan jet engine of an airplane, the circular electric motor comprising: a motor support structure; a spin rotor member with arms radiating toward the motor support structure having four cardinal points; a plurality of stator pole irons wound with stator coils, wherein the stator pole irons are affixed at the cardinal points and intermediate points between the cardinal points and excited by a generator to create magnetic poles of a first polarity; and a rotor pole affixed at one end of each spin rotor member arm; wherein each rotor pole faces outwards towards the stator pole irons axially aligned with the rotor poles, and wherein rotor poles at first opposite cardinal points are at a first polarity and the rotor poles at the other opposite cardinal points are at a second polarity.

2. The engine system of claim 1, wherein the generator comprises a solid state, non-rotating electromagnetic rotor which generates a 360° revolving polar magnetic field which is emitted sequentially from salient poles and moves parallel to the surface of the stator in a 360° circular motion as either a uni-pole, dipole, or four-pole, wherein the rotor is placed inside a stator of the generator and electric power leads from the generator are connected to the stator coils of the electric motor to excite the stator pole irons of the motor with at least a portion of the generated electric power being sent to a storage device where a portion of the stored power is utilized to re-excite the rotor of the generator.

3. The engine system of claim 1, wherein the stator pole irons are activated in sequence for spinning the spin rotor member.

4. The engine system of claim 1, wherein each rotor pole is magnetized using a permanent magnet or an electromagnetic magnet.

5. The engine system of claim 1, wherein the circular electric motor is configured to spin the fan blades at variable speeds.

6. A generator coupled to a circular electric motor affixed to a fan of a turbofan jet engine of an airplane and comprising: a motor support structure; a spin rotor member with arms radiating toward the motor support structure having four cardinal points; and a plurality of stator pole irons wound with stator coils, each stator pole iron being affixed at the cardinal points and intermediate points between the cardinal points; wherein the generator powers the plurality of wound stator pole irons to sequentially excite windings on each stator pole iron such that a pair of stator pole irons opposite each other are each excited for a fixed or variable time after which a next pair of stator pole irons opposite each other are excited in a clockwise direction until all opposite pairs are excited and the process continues to maintain a desired spin velocity of the turbofan jet engine.

7. The generator of claim 6, comprising a solid state, non-rotating electromagnetic rotor which generates a 360° revolving polar magnetic field which is emitted sequentially from salient poles and moves parallel to the surface of the stator in a 360° circular motion as either a uni-pole, dipole, four-pole, wherein the rotor is placed inside a stator of the generator and electric power leads from the generator are connected to the stator coils of the electric motor to excite the stator pole irons of the electric motor with at least a portion of the generated electric power being sent to a storage device where a portion of the stored power is utilized to re-excite the rotor of the generator.

8. A turbofan jet engine, wherein the engine comprises: an outer cowling; a motor structure with a stator of a circular electric drive motor with stator pole irons attached, stator coils wound on the stator pole irons; a fan and fan blades, and a rotor coupled to the fan wherein the fan blades are configured to spin at a variable speed by deriving power from the circular electric motor.

9. The engine of claim 8, wherein the stator coils of the motor's stator are excited by a generator having a solid state, non-rotating electromagnetic rotor which generates a 360° revolving polar magnetic field which is emitted sequentially from salient poles and moves parallel to the surface of the stator in a 360° circular motion as either a uni-pole, dipole, or four-pole, wherein the rotor is placed inside a stator of the generator and electric power leads from the generator are connected to the stator coils of the electric motor to excite the stator pole irons of the electric motor with at least a portion of the generated electric power being sent to a storage device where a portion of the stored power is utilized to re-excite the rotor of the generator.

10. A circular electric drive motor coupled to a turbofan jet engine of an airplane, the circular electric motor comprising: a motor support structure; a spin rotor member with arms radiating toward the motor support structure having four cardinal points; and a plurality of stator pole irons wound with stator coils, wherein a stator pole iron is affixed at each cardinal point and an intermediate point on the motor support structure and sequentially electrically activated by a generator coupled to the stator coils for magnetizing the stator pole irons.

11. The electric drive motor of claim 10, wherein the generator comprises a solid state, non-rotating electromagnetic rotor which generates a 360° revolving polar magnetic field which is emitted sequentially from salient poles and moves parallel to the surface of the stator in a 360° circular motion as either a uni-pole, dipole, or four-pole, wherein the rotor is placed inside a stator of the generator and electric power leads from the generator are connected to the stator coils of the electric motor to excite the stator pole irons of the electric motor with at least a portion of the generated electric power being sent to a storage device where a portion of the stored power is utilized to re-excite the rotor of the generator.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0041] The accompanying drawings, which are incorporated in and constitute part of this specification, and together with the description, illustrate and serve to explain the principles of various exemplary embodiments. In the drawings, in which like reference numerals designate similar or corresponding elements, regions, and portions:

[0042] FIG. 1 is a diagram illustrating an exemplary turbofan jet engine mounted on the side of a jet aircraft, consistent with embodiments of the present disclosure.

[0043] FIG. 2 is a diagram of a front view of an exemplary turbofan jet engine with the outer cowling removed revealing the fan and exemplary wound stator pole irons of an exemplary electric motor, consistent with embodiments of the present disclosure.

[0044] FIG. 3 is a diagram of a front view of an exemplary turbofan jet engine with the outer cowling and fan removed revealing exemplary wound pole irons of the stator and exemplary poles of the rotor of the exemplary electric motor, consistent with embodiments of the present disclosure.

[0045] FIG. 4 is a diagram of a lateral view of an exemplary turbofan jet engine with an exemplary electric motor, consistent with embodiments of the present disclosure.

[0046] FIG. 5 is a diagram of a cross sectional view of the exemplary turbofan jet engine of FIG. 4, consistent with embodiments of the present disclosure.

[0047] FIG. 6 is a diagram of an end view of an exemplary solid state rotor of an exemplary electric power generator which provides power to the exemplary electric motor of the turbofan jet engine, consistent with embodiments of the present disclosure.

DETAILED DESCRIPTION

[0048] Embodiments herein include apparatus, systems and methods. At least some disclosed methods may be executed, for example, by at least one processor that receives instructions from a non-transitory computer-readable storage medium. Similarly, systems consistent with the present disclosure may include at least one processor and memory, and the memory may be a non-transitory computer-readable storage medium. As used herein, a non-transitory computer-readable storage medium refers to any type of physical memory on which information or data readable by at least one processor may be stored. Examples include random access memory (RAM), read-only memory (ROM), volatile memory, nonvolatile memory, hard drives, CD ROMs, DVDs, flash drives, disks, and any other known physical storage medium. Singular terms, such as “memory” and “computer-readable storage medium,” may additionally refer to multiple structures, such a plurality of memories and/or computer-readable storage mediums. As referred to herein, a “memory” may comprise any type of computer-readable storage medium unless otherwise specified. A computer-readable storage medium may store instructions for execution by at least one processor, including instructions for causing the processor to perform steps or stages consistent with an embodiment herein. Additionally, one or more computer-readable storage mediums may be utilized in implementing a computer-implemented method. The term “computer-readable storage medium(s)” should be understood to include tangible items and exclude carrier waves and transient signals.

[0049] Reference will now be made in detail to the exemplary embodiments implemented according to the disclosure, the examples of which are illustrated in the accompanying drawings. In accordance with various exemplary embodiments discussed and described herein by way of brief summary, an exemplary all-electric turbofan jet engine is powered by an exemplary electric motor which is powered by an exemplary solid state electric power plant is presented.

[0050] FIG. 1 is a diagram illustrating an exemplary turbofan jet engine attached to the fuselage of, for example, a small, twin jet aircraft. Engine cowling 1 forms the intake opening for fan 3 and its fan blades 2. Attachment 4 attaches the engine to the aircraft's fuselage and serves as a conduit for power cables and controls from the aircraft to the engine.

[0051] FIG. 2 is a diagram illustrating the front end view of an exemplary turbofan jet engine with outer cowling 1 removed, revealing motor structure 5, fan 3 and its fan blades 2, and exemplary wound stator pole irons 6-13 with coil windings 14-21 of an exemplary electric drive motor. As illustrated, the inward poles of the stators are of a first polarity (e.g., south pole).

[0052] In FIG. 3, outer cowling 1 and fan 2 and its fan blades 2 are removed from the engine, revealing exemplary wound stator pole irons 6-13 with their coil windings 14-21 of FIG. 2 and exemplary rotor member 22 with rotor poles 23-26 of the exemplary electric motor 2a in FIG. 4. Rotor poles 24 and 26 facing outward toward the stator pole irons are of a first polarity (e.g., south pole) whereas rotor poles 23 and 25 facing outward are of a second polarity (e.g., north pole). The rotor magnets can be either permanent magnets or electromagnets.

[0053] The stator pole irons are activated in sequence such that they spin rotor member 22 of FIG. 3. When activated, winding coils 14-21 are sequentially activated making stator pole irons 6-13 a first polarity (south pole) facing the rotor member. The stator poles are powered with DC power from the exemplary onboard solid state power generator discussed below. The stator pole irons are excited sequentially for 0.75 milliseconds with a 0.75 collapse time. In order to reach a spin velocity of 20,000 rpm's, the following sequence is employed: Pole irons 6 and 10 are excited with DC current from a solid state excitation system, pole irons 7 and 11 are excited 0.375 milliseconds after pole irons 6 and 10, pole irons 8 and 12 are excited 0.375 milliseconds after pole irons 7 and 11, pole irons 9 and 13 are excited 0.375 milliseconds after pole irons 8 and 12 are excited, and then pole irons 6 and 10 are again excited 0.375 milliseconds following pole irons 9 and 13. This timing sequence allows rotational speeds of 20,000 rpm's. The times given above are exemplary. Appropriate timing changes are programmed into a programmable logic controller (PLC), for example, which controls the DC excitation system for variable speeds of fan 3 and low pressure compressor 27 in turbofan jet engine shown in FIG. 4.

[0054] The engine includes a fan placed in the intake of the engine draws air in by the pitch and speed of the fan, thereby forming backward thrust. The exemplary engine disclosed herein also includes a high efficiency electric drive motor which can drive the fan at variable speeds. Furthermore, air pulled into the intake of the engine by the fan is divided into two columns, one air column bypasses the jet intake and is bypassed around and out through the jet nozzle to provide thrust and the remaining intake air is taken in through the low pressure compressor. The air taken in through the intake is chilled and compressed by the low pressure compressor and pushed back into the high pressure compressor. The airflow into the high pressure compressor is compressed and pushed into the hot section of the engine containing heating rods or other electrical heating mechanisms where the compressed air expands due to the heat inside the hot section. The heat expanded air in the hot section drives the high pressure turbine which, in turn, drives the high pressure compressor and expanded air then flows through the low pressure turbine and out through the jet nozzle which results in thrust. The low pressure turbine drives the low pressure compressor and the fan. The thrust intensity can be controlled by the fan drive motor, the heat intensity of the hot section, and the thrust control flaps of the engine.

[0055] In FIG. 4, high pressure compressor 30 is powered by the compressed gas in hot section 35 when the gas is expanded by the heat from the heating system, for example, exemplary high resistance heat rods or calrods 36. The expanded gas drives high pressure turbine 32 and low pressure turbine 34 and is then jetted out through nozzle 33 to provide thrust. High pressure turbine 32 drives high pressure compressor 30. The speed and thrust of the engine is controlled by the exemplary electric fan drive motor 2a, thrust control flaps 28, and the amount of current through heat rods 36 of the heating system. The cross-section A-A′ of a part of the engine is illustrated in FIG. 5 which shows low pressure shaft 29, high pressure shaft 31, hot section 35, and heat rods 36.

[0056] The power supply for the engine, including its electric fan drive motor and heating system, is provided by a rotary electric generator in which the conventional dipole or multi-pole spinning rotor is replaced with a dipole or multi-pole static, that is, non-rotating, solid state rotor insert. The rotor creates rotating magnetic poles and generates electric power without rotating itself. Since the rotor is stationary there is no energy consuming interaction with the magnetic poles formed in the stator when the generator is connected to an electric load. Nor does the rotor require energy to spin the physical mechanism at the proper frequency.

[0057] Shown in FIG. 6 and more fully described in the PCT Application entitled “Solid State Multi-Pole and Uni-Pole Electric Generator Rotor for AC/DC Electric Generators” (PCT Appln. No. PCT/EP2017/079687, filed Nov. 17, 2017) is an exemplary high efficiency electric power generator 37 with 3-phase windings lapped clockwise. This redesign of the generator rotor is accomplished by, for example, but not limited to, cutting laminates from electrical steel in the desired diameter with salient pole pieces of equal number, size, and distribution. Exemplar rotor pole pieces 1-16 in FIG. 6 are wound with the desired and appropriate magnet wire. The magnet wire coils are each terminated in two leads which are wired to a PLC controlled excitation system. The excitation system allows sequential excitation of alternating polarity such that separated and discrete magnetic poles rotate around the periphery of the rotor parallel to the surface of the rotor, thereby generating voltage and amperage in the field coils of stator 40.

[0058] In FIG. 6, each wound salient poles in a first polarity 38 and a second polarity 39 are excited in a sequential fashion such that four discrete magnetic poles are rotated parallel to the surface of the stator 40 at the desired speed in order to generate power without experiencing reverse torque on the rotors. Generator 37 is shown attached to base 41. As noted above, the rotor remains stationary while the discrete magnetic poles rotate at the desired frequency. The high efficiency generator does not require energy to spin the rotor or to overcome reverse torque. Furthermore, it can produce the same amount of electric energy as a conventional generator with the same specifications. Additionally, as described more fully in the above referenced PCT Application, some of the energy produced by the generator can be taken back through a battery interface and used to excite the rotor pole windings.

[0059] The onboard electric power generator disclosed herein can provide energy for every electrical demand of an aircraft, including the energy required to move it in space either by use of a propeller or a jet engine. In the case of a propeller driven aircraft, the generator provides electric power to an electric drive motor which turns the propeller through a gear mechanism. And in the case of a turbofan jet engine, as discussed above, the generator provides power to an electric fan drive motor which turns the fan of the engine.