Patent Description:
The systems and/or methods described in <CIT>, <CIT>, <CIT>, and <CIT> may additionally be useful to illustrate the technical background.

The present disclosure provides a system according to claim <NUM>.

In some implementations, the first rotor assembly is suitable to be connected to a higher-pressure compressor, the second rotor assembly is suitable to be connected to a lower-pressure compressor, and the first rotor assembly is configured to rotate at a first speed that is greater than a second speed at which the second rotor assembly is configured to rotate.

In some implementations, , the first rotor assembly is suitable to be connected to a lower-pressure compressor, the second rotor assembly is suitable to be connected to a higher-pressure compressor, and the first rotor assembly is configured to rotate at a first speed that is greater than a second speed at which the second rotor assembly is configured to rotate.

The first magnetic field may, once the system is connected to a turbine engine, propagate radially outward from an axis of rotation for the first rotor assembly over an air gap defined between the permanent magnet and armature winding.

The first magnetic field may, once the system is connected to a turbine engine, propagate coaxially to an axis of rotation for the first rotor assembly over an air gap defined between the permanent magnet and armature winding.

The system may further include a high frequency converter disposed between the armature winding and the resonant emitter; wherein the high frequency converter is configured to provide the electrical power input at a higher frequency to the resonant emitter than the first magnetic field is received by the armature winding.

The higher frequency may be greater than a difference in rotational speed between the first rotor assembly and the second rotor assembly and is based on a power transfer efficiency between the resonant emitter and the resonant receiver.

The electrical power output may include a plurality of electrical phases based on a number of phases defined in the armature winding.

The system may further include a power control unit configured to be disposed in the enclosure and to be connected to a power distribution bus for a vehicle.

The present disclosure additionally provides a turbine engine including a system as described above, according to any of claims <NUM>-<NUM>.

The present disclosure provides a method according to claim <NUM>.

So that the manner in which the above recited features can be understood in detail, a more particular description, briefly summarized above, may be had by reference to example aspects, some of which are illustrated in the appended drawings.

As will be appreciated, the Figures are provided to illustrate the concepts discussed in the present disclosure, and may include various components that are simplified or not drawn to scale relative to other components to better highlight and teach the inventive concepts described herein.

The present disclosure provides for power extraction and transfer from the rotational components of a turbine engine via electromagnetic (EM) components that are not in physical contact with one another, but rather extract and convert rotational energy into electrical energy via a series of induced magnetic fields. In some aspects, a permanent magnet affixed to a first rotor assembly in the engine rotates relative to a first armature winding on a second rotor assembly in the engine to induce an electrical current in the first armature when the two compressors rotate relative to one another while the engine is in operation. This induced current, in turn, powers a high frequency resonator that produces a second magnetic field with a high frequency to induce a current in receiving circuits located in fixed positions on the case or shell of the engine to thereby wirelessly transfer power to the electrical systems of the vehicle.

The electromagnetic power transfer components are arranged with radial symmetry around the engine with contact to a single thrust generating component (e.g., a rotor assembly or an enclosure). Air gaps separate the permanent magnet and the armature winding and the resonant emitter and the resonant receiver. Because none of the electromagnetic power transfer components are in physical contact with more than one thrust generating component of the engine or another power transfer component connected to a different thrust generating component, the system beneficially experiences less wear and correspondingly lower replacement rates of the power transfer components. Additionally, the electromagnetic components do not transfer power via wires or shafts disposed in the airflow of the turbine engine, and may be relatively lightweight compared to gearboxes and shafts that translate rotational energy to an external generator, thus providing greater mechanical and fuel efficiency for the engine. Moreover, the efficiency of power extraction and transfer via the electromagnetic power transfer components can exceed the efficiency of mechanical power transfer components, thus further improving the efficiency of the engine.

Although the examples provided in the present disclosure primarily illustrate the use the power transfer system in the turbine engines of aircraft, the power transfer system described in the present disclosure may be used in conjunction with turbine engines used in cars, busses, trains, boats, and various other vehicles.

<FIG> and <FIG> illustrate cross-sectional views of turbine engines <NUM>, (individually, turbine engine 100A and turbine engine 100B) which include one or more electrical generators <NUM>. The turbine engines <NUM> include an enclosure <NUM> defining an air intake <NUM> at an upstream end, a compression section <NUM> downstream of the air intake <NUM>, a combustion section <NUM> downstream of the compression section <NUM>, a turbine section <NUM> downstream of the combustion section <NUM>, and an exhaust <NUM> at a downstream end. In various aspects, the enclosure <NUM> is included inside of a nacelle <NUM> (also referred to as a housing), and a bypass flow chamber <NUM> is defined between an outer surface of the enclosure <NUM> and an inner surface of the nacelle <NUM>. A transfer cable <NUM> linking the electrical generators <NUM> to a power distribution bus <NUM> or other power transfer mechanism for a vehicle (e.g., a cable connector, spliter, or a protective device such as circuit breaker, or bus tie) in which the turbine engine <NUM> is disposed in the bypass flow chamber <NUM> running from the enclosure <NUM> to electrically connect electrical distributors <NUM> with a power distribution bus (e.g., for a vehicle).

The turbine engine 100A of <FIG> includes a first spool shaft 160A (generally, spool shaft or shaft <NUM> or collectively, shaft assembly) and a second spool shaft 160B, while the turbine engine 100B of <FIG> includes a first spool shaft 160A, a second spool shaft 160B, and a third spool shaft 160C. Each shaft <NUM> extends coaxially with the other shafts <NUM>, and rotates during operation at different rates relative to one another due to the ejection of high pressure exhaust rotating the turbines 180A-B (generally, turbine <NUM>), which in turn drive the associated compressors 170A-B or 170A-C (generally, compressor <NUM>) at different rates via the associated spool shafts <NUM>. For example, a first spool shaft 160A rotates (due to forces imparted by the first turbine 180A) to drive the rotation of a first compressor 170A at a first rotational speed, while a second spool shaft 160B rotates (due to forces imparted by the second turbine 180B) to drive the rotation of a second compressor 170B at a second rotational speed. Similarly, in <FIG>, the third turbine 180C rotates a third spool shaft 160C to drive the rotation of a third compressor 170C at a third rotational speed, where the first, second, and third rotational speeds are all different from one another.

The compressors <NUM> are disposed in the compression section <NUM> of the enclosure <NUM>, and may each include several fan blades arranged in one or more rows. The turbines <NUM> are disposed in the turbine section <NUM> of the enclosure <NUM>, and may each include several fan blades arranged in one or more rows. Although not illustrated, various bearings or low friction surfaces may be located between the shafts <NUM> to improve rotational characteristics of the shafts <NUM> (e.g., to reduce friction).

As illustrated in <FIG>, the first spool shaft 160A is a low-pressure shaft relative to the high-pressure shaft of the second spool shaft 160B. Accordingly, the first compressor 170A is located upstream of the second compressor 170B, and rotates at a lower rotational speed than the second compressor 170B during operation of the turbine engine <NUM>. Similarly, the first turbine 180A is located downstream of the second turbine 180B, and rotates at a lower rotational speed than the second turbine 180B during operation of the turbine engine <NUM>.

As illustrated in <FIG>, the first spool shaft 160A is a low-pressure shaft, the second spool shaft 160B is a medium-pressure shaft, and the third spool shaft 160C is a high-pressure shaft relative to one another. Accordingly, the first compressor 170A is located upstream of the second compressor 170B, which is located upstream of the third compressor 170C, each of which operates at lower rotational speeds than downstream compressors <NUM> during operation of the turbine engine <NUM>. Similarly, the first turbine 180A is located downstream of the second turbine 180B, which is located downstream of the third turbine 180C, each of which operates at progressively lower rotational speeds than upstream turbines <NUM> during operation of the turbine engine <NUM>.

Accordingly, a first differential rotational speed exists between the first spool shaft 160A and the second spool shaft 160B (and any components attached thereto) during operation, and, in <FIG>, a second differential rotational speed (which may be the same as or different than the first differential rotational speed) exists between the second spool shaft 160B and the third spool shaft 160C (and any components attached thereto).

The electrical generators <NUM> include electrical extractors <NUM> affixed to the compressors <NUM> and electrical distributors <NUM> affixed to the enclosure <NUM>. The electrical extractors <NUM> are not physically connected to the electrical distributors <NUM>, but are separated by an empty space (e.g., an "air gap") and electromagnetically linked during operation by a generated electromagnetic field. The electrical extractors <NUM> are connected to the compressors <NUM> and capitalize on the different rotational speeds of the compressors <NUM> attached to different shafts <NUM> to rotate the components relative to one another using the operational rotation of the components of the turbine engine <NUM>. As illustrated in <FIG>, an electrical extractor <NUM> is located at the interface between the first compressor 170A and the second compressor 170B. As illustrated in <FIG>, a first electrical extractor 111A is located at the interface between the first compressor 170A and the second compressor 170B, and a second electrical extractor 111B is located at the interface between the second compressor 170B and the third compressor 170C.

Each electrical extractor <NUM> is associated with a corresponding electrical distributor <NUM> affixed radially around a corresponding portion of the enclosure <NUM> (e.g., a first electrical extractor 111A corresponding to a first electrical distributor 112A, a second electrical extractor 111B corresponding to a second electrical distributor 112B). The electrical distributor <NUM> includes a resonant receiver for receiving high frequency power from the electrical extractor <NUM> and a power conversion unit (PCU) to convert the high frequency power to a predefined frequency (e.g., <NUM>) for consumption and/or storage in the vehicle, and is connected to the power distribution bus <NUM> via the cable <NUM>. Although not illustrated, in some aspects using a three-shaft design, the turbine engine <NUM> may include only one electrical generator <NUM>; omitting one of the first electrical generator 110A or the second electrical generator 110B. Additionally, although one arrangement of the components of the electrical generators <NUM> is shown in <FIG> and <FIG>, the components may be arranged in various configurations, such as those discussed in relation to <FIG> and 3A-3B.

<FIG> illustrate cross-sectional views of the components of an electrical generator <NUM>. <FIG> and <FIG> illustrate the components arranged with a radial magnetic linkage, and <FIG> and <FIG> illustrate the components arranged with an axial magnetic linkage. As will be appreciated, as cross-sectional views, <FIG> illustrate one segment of a radially arranged electrical generators <NUM>, and an electrical generator <NUM> may be constructed as illustrated in one of <FIG> or more than one of <FIG> at different arc segments in the radial arrangement around the shafts <NUM>/within the enclosure <NUM> of the turbine engine <NUM>.

The electrical extractors <NUM> are located at the interface of two compressors 170A and 170B. For example, the illustrated electrical extractors <NUM> may be located on the first compressor 170A and the second compressor 170B. In another example, the illustrated electrical extractors <NUM> may be located on the second compressor 170B and the third compressor 170C. In various aspects, the components illustrated in <FIG> may belong to a sole electrical extractor <NUM> (as in <FIG>), or to one of a primary or secondary electrical extractor <NUM> (as in <FIG>). In aspects including multiple electrical extractors <NUM>, the individual components may be arranged both according to the same one of <FIG> or one according to a first one of <FIG> and the other one according to a different one of <FIG>. As used herein, when differentiating components between multiple electrical generators <NUM>, the components of one electrical generator <NUM> may be distinguished by referring to those components as "secondary" components. For example, a first electrical extractor 111A includes a primary permanent magnet <NUM>, and a second electrical extractor 111B includes a secondary permanent magnet <NUM>. In another example, a first electrical extractor 111A is attached to a primary first compressor 170A and a primary second compressor 170B, and a second electrical extractor 111B is attached to a secondary first compressor 170A (which may be a different end of the same compressor <NUM> as the primary first compressor 170A or the primary second compressor 170B) and a secondary second compressor 170B (which may be a different end of the same shaft <NUM> as the primary first compressor 170A or the primary second compressor 170B).

<FIG> illustrates a first component arrangement 200A for an electrical extractor <NUM>, according to aspects of the present disclosure. A first rotor assembly 210A (generally, rotor assembly <NUM>) is connected to a lower-pressure first compressor 170A and a second rotor assembly 210B is connected to a higher-pressure second compressor 170B at an interface between the two compressors <NUM>. In various aspects, the rotor assemblies <NUM> are connected to one or more blades of the associated compressor <NUM>, to a ring/connection point of the blades to an associated spool shaft <NUM>, or to the associated spool shaft <NUM>. The rotor assemblies <NUM> position various electromagnetic components of the electrical extractor <NUM> at known distances and orientations relative to one another, the shafts <NUM>, the compressors <NUM>, and the electrical distributor <NUM>.

In <FIG>, the first rotor assembly 210A includes a permanent magnet <NUM>, which produces a first magnetic field <NUM>. The permanent magnet <NUM> emits the first magnetic field <NUM> radially through an air gap defined coaxially to the shafts <NUM> to magnetically link the permanent magnet <NUM> with an armature winding <NUM> included in the second rotor assembly 210B. In various aspects, the permanent magnet <NUM> may include a plurality of magnets arranged circumferentially around the shafts <NUM> to emit a plurality of first magnetic fields <NUM>.

The second rotor assembly 210B includes the armature winding <NUM> and a resonant emitter <NUM>. The armature winding <NUM> is arranged concentrically and radially around, but not in physical contact with, the permanent magnet <NUM> or the shafts <NUM>, and positions the armature winding <NUM> within a predefined field strength of the first magnetic field <NUM>. Accordingly, the first magnetic field <NUM> radially links the permanent magnet <NUM> and the armature winding <NUM>. In various aspects, when rotated relative to the permanent magnet <NUM>, the armature winding <NUM> produces a first current (I<NUM>) as a multiphase alternating current, which is input to power the resonant emitter <NUM> to generate a second magnetic field <NUM>. The second rotor assembly 210B positions the resonant emitter <NUM> outside of a predefined field strength of the first magnetic field <NUM>, and accordingly, the permanent magnet <NUM> is positioned outside of a predefined field strength of the second magnetic field <NUM>. The second magnetic field <NUM> is radially emitted outward from the resonant emitter <NUM> to electromagnetically link the resonant emitter <NUM> with a resonant receiver <NUM>.

<FIG> illustrates a second component arrangement 200B for an electrical extractor <NUM>, according to aspects of the present disclosure. A first rotor assembly 210A is connected to a higher-pressure second compressor 170B and a second rotor assembly 210B is connected to a lower-pressure second compressor 170A at an interface between the two compressors <NUM>. In various aspects, the rotor assemblies <NUM> are connected to one or more blades of the associated compressor <NUM>, to a ring/connection point of the blades to an associated spool shaft <NUM>, or to the associated spool shaft <NUM>. The rotor assemblies <NUM> position various electromagnetic components of the electrical extractor <NUM> at known distances and orientations relative to one another, the shafts <NUM>, the compressors <NUM>, and the electrical distributor <NUM>.

In <FIG>, the first rotor assembly 210A includes a permanent magnet <NUM>, which produces a first magnetic field <NUM>. The permanent magnet <NUM> emits the first magnetic field <NUM> radially through an air gap defined coaxially to the shafts <NUM> to magnetically link the permanent magnet <NUM> with an armature winding <NUM> included in the second rotor assembly 210B. In various aspects, the permanent magnet <NUM> may include a plurality of magnets arranged circumferentially around the shaft <NUM> to emit a plurality of first magnetic fields <NUM>.

The second rotor assembly 210B includes the armature winding <NUM> and a resonant emitter <NUM>. The armature winding <NUM> is arranged concentrically and radially, but not in physical contact with, the permanent magnet <NUM> or the shafts <NUM>, and positions the armature winding <NUM> within a predefined field strength of the first magnetic field <NUM>. Accordingly, the first magnetic field <NUM> radially links the permanent magnet <NUM> and the armature winding <NUM>. In various aspects, when rotated relative to the permanent magnet <NUM>, the armature winding <NUM> produces a first current (I<NUM>) as a multiphase alternating current, which powers the resonant emitter <NUM> to generate a second magnetic field <NUM>. The second rotor assembly 210B positions the resonant emitter <NUM> outside of a predefined field strength of the first magnetic field <NUM>, and accordingly, the permanent magnet <NUM> is positioned outside of a predefined field strength of the second magnetic field <NUM>. The second magnetic field <NUM> radially links the resonant emitter <NUM> with a resonant receiver <NUM>.

<FIG> illustrates a third component arrangement 200C for an electrical extractor <NUM>, according to aspects of the present disclosure. A first rotor assembly 210A is connected to a lower-pressure first compressor 170A and a second rotor assembly 210B is connected to a higher-pressure second compressor 170B at an interface between the two compressors <NUM>. In various aspects, the rotor assemblies <NUM> are connected to one or more blades of the associated compressor <NUM>, to a ring/connection point of the blades to an associated spool shaft <NUM>, or to the associate shaft <NUM>. The rotor assemblies <NUM> position various electromagnetic components of the electrical extractor <NUM> at known distances and orientations relative to one another, the shafts <NUM>, the compressors <NUM>, and the electrical distributor <NUM>.

In <FIG>, the first rotor assembly 210A includes a permanent magnet <NUM>, which produces a first magnetic field <NUM>. The permanent magnet <NUM> emits the first magnetic field <NUM> through an air gap defined in a plane intersecting the axis of rotation for the shafts <NUM> to magnetically link the permanent magnet <NUM> with an armature winding <NUM> included in the second rotor assembly 210B. Although illustrated as defining an air gap in a plane orthogonal to the axis of rotation (e.g., for a coaxial magnetic linkage between the permanent magnet <NUM> and the armature winding <NUM>), in other aspects, the air gap may be defined at other angles relative to the shafts <NUM>. In various aspects, the permanent magnet <NUM> may include a plurality of magnets arranged radially around the shaft <NUM> to emit a plurality of first magnetic fields <NUM>.

The second rotor assembly 210B includes the armature winding <NUM> and a resonant emitter <NUM>. The armature winding <NUM> is arranged radially around, but not in physical contact with, the shafts <NUM> and arranged planetary to the permanent magnet <NUM>. As used herein, when two objects are described as being "planetary" with one another, it will be understood that the objects rotate about a shared axis of rotation (at the same or different radial distances from the axis of rotation), but at different points along the length of the axis of rotation so as to be clear of the orbit (i.e., not physically contact) of the other object. The relative positions and lengths of the rotor assemblies <NUM> position the armature winding <NUM> within a predefined field strength of the first magnetic field <NUM>. Accordingly, the first magnetic field <NUM> axially links the permanent magnet <NUM> and the armature winding <NUM>. In various aspects, when rotated relative to the permanent magnet <NUM>, the armature winding <NUM> produces a first current (I<NUM>) as a multiphase alternating current, which powers the resonant emitter <NUM> to generate a second magnetic field <NUM>. The second rotor assembly 210B positions the resonant emitter <NUM> outside of a predefined field strength of the first magnetic field <NUM>, and accordingly, the permanent magnet <NUM> is positioned outside of a predefined field strength of the second magnetic field <NUM>. The second magnetic field <NUM> radially links the resonant emitter <NUM> with a resonant receiver <NUM>.

<FIG> illustrates a fourth component arrangement 200D for an electrical extractor <NUM>, according to aspects of the present disclosure. A first rotor assembly 210A is connected to a higher-pressure first compressor 170A and a second rotor assembly 210B is connected to a lower-pressure second compressor 170B at an interface between the two compressors <NUM>. In various aspects, the rotor assemblies <NUM> are connected to one or more blades of the associated compressor <NUM>, to a ring/connection point of the blades to an associated spool shaft <NUM>, or to the associated spool shaft <NUM>. The rotor assemblies <NUM> position various electromagnetic components of the electrical extractor <NUM> at known distances and orientations relative to one another, the shafts <NUM>, the compressors <NUM>, and the electrical distributor <NUM>.

The second rotor assembly 210B includes the armature winding <NUM> and a resonant emitter <NUM>. The armature winding <NUM> is arranged radially around, but not in physical contact with, the shafts <NUM> and arranged planetary to the permanent magnet <NUM>. The relative positions and lengths of the rotor assemblies <NUM> position the armature winding <NUM> within a predefined field strength of the first magnetic field <NUM>. Accordingly, the first magnetic field <NUM> axially links the permanent magnet <NUM> and the armature winding <NUM>. In various aspects, when rotated relative to the permanent magnet <NUM>, the armature winding <NUM> produces a first current (I<NUM>) as a multiphase alternating current, which powers the resonant emitter <NUM> to generate a second magnetic field <NUM>. The second rotor assembly 210B positions the resonant emitter <NUM> outside of a predefined field strength of the first magnetic field <NUM>, and accordingly, the permanent magnet <NUM> is positioned outside of a predefined field strength of the second magnetic field <NUM>. The second magnetic field <NUM> radially links the resonant emitter <NUM> with a resonant receiver <NUM>.

In each of <FIG>, a resonant receiver <NUM> of an electrical distributor <NUM> is affixed to an interior surface of the enclosure <NUM>, and is positioned in relation to the resonant emitter <NUM> to receive at least a predefined field strength of the second magnetic field <NUM>. The resonant receiver <NUM> is arranged with radial symmetry around the enclosure <NUM>, and is configured to receive the second magnetic field <NUM> to produce a third multiphase alternating current (I<NUM>) that is provided to a power control unit <NUM> (also referred to as a PCU) that conditions the power for provision to a bus or other electrical distribution system of a vehicle.

During operation of the turbine engine <NUM> in which the components are disposed, the rotational forces imparted by turbines cause the compressors <NUM> and attached EM components to rotate relative to one another and the stationary enclosure <NUM>. Due to the differential in the rotational speeds of the higher-pressure compressor <NUM> and the lower-pressure compressor <NUM>, the first magnetic field <NUM> rotates relative to the armature winding <NUM>, and the second magnetic field <NUM> rotates relative to the (nominally stationary) resonant receiver <NUM>. Accordingly, electrical energy is extracted from the rotational forces of the shafts <NUM> and is wirelessly transferred between the various assemblies via magnetic fields instead of via mechanical transfer components, such as gears or the like.

The relative sizes and positions of the electromagnetically coupled components in <FIG> have been illustrated for the easy identification and differentiation of the reader. However, in various aspects, a fabricator may alter the relative sizes, shapes, and orientations of these components based on the physical properties of the turbine engine <NUM> in which the components are installed (e.g., length, thickness, circumference, gap distance, rotational torque, and speed, operating temperature), the desired power characteristics for the extracted power (e.g., number of power phases, voltage/current levels), and the like. The lengths of the components along the axis of the shafts <NUM> are determined by the torque and/or power rating requirements of the vehicle from the turbine engine <NUM>, and the relative sizes and distances of individual components are sized to optimize torque production and speed from the turbine engine <NUM> and power transfer efficiency in the electrical generator <NUM> within the physical confines of the turbine engine <NUM>. Thus, <FIG> are intended to demonstrate the concepts of operation, and not necessarily a specific implementation, which may be modified based on the power requirements, thrust requirements, turbine engine specific fuel consumption, and material properties of various components.

For example, a fabricator can design the permanent magnet <NUM> and the armature winding <NUM> according to <FIG> or <FIG> when radial space along the length of blades of the compressors <NUM> is more readily available or according to <FIG> or <FIG> when axial space between the compressors <NUM> is more readily available. Similarly, to optimize the power transfer capabilities of the electrical extractor <NUM>, the resonant emitter <NUM> may be sized and positioned to overlay the armature winding <NUM> and/or the permanent magnet <NUM> so that the resonant emitter <NUM> extends over the entire length of the electrical extractor <NUM>, and the length and position of the resonant receiver <NUM> is matched to overlay the resonant emitter <NUM>.

<FIG> is a circuit diagram <NUM> of the EM components of an electrical generator <NUM>. The first rotor assembly 210A (which includes the permanent magnet <NUM>) is arranged in magnetic contact, but not physical contact, with the second rotor assembly 210B (which includes the armature winding <NUM> and the resonant emitter <NUM>) via the first magnetic field <NUM>. As used herein, magnetic contact describes the state in which a magnetic field produced by a permanent or electromagnet is of at least a predefined strength between two components. The armature winding <NUM> includes a plurality of receiving windings 310A-C (generally, receiving winding <NUM>) that each produce one phase of power from the received first magnetic field <NUM>. Although illustrated as providing three-phase current to the resonant emitter <NUM> via three corresponding receiving windings 310A-C, in other aspects, more or fewer than three phases may be used by, for example, using more or fewer receiving windings.

The first rotor assembly 210A is connected to one compressor <NUM> of the turbine engine <NUM>, such as shown in <FIG> and the second rotor assembly 210B is connected to a second compressor <NUM> of the turbine engine <NUM>, such as shown in <FIG>. Due to the difference in rotational speeds of each compressor <NUM> when the turbine engine <NUM> is in operation, the first rotor assembly 210A rotates at the differential speed relative to the second rotor assembly 210B.

The second rotor assembly 210B is arranged in magnetic contact, but not physical contact, with a stationary assembly <NUM> via the resonant emitter <NUM> and the resonant receiver <NUM>. The stationary assembly <NUM> is disposed on (or through) the enclosure <NUM> of the turbine engine <NUM>, and as such, remains stationary relative to the rotating compressors <NUM> and the EM components connected thereto. The stationary assembly <NUM> includes the resonant receiver <NUM> and the power control unit <NUM>, which physically connects the stationary assembly <NUM> to an electrical bus or other power distribution system for the vehicle. The resonant emitter <NUM> and resonant receiver <NUM>, which are discussed in greater detail in regard to <FIG>, respectively generate and receive the second magnetic field <NUM> as a high-frequency magnetic field at a predefined resonant frequency to produce a power output to the power control unit <NUM> and the vehicle.

<FIG> is a circuit diagram <NUM> detailing a three-phase example of the resonant emitter <NUM> and resonant receiver <NUM>, according to aspects of the present disclosure. The armature winding <NUM> includes a plurality of receiving windings 310A-C that each produce one phase of power (e.g., I1Φ1, I1Φ2, I1Φ3) due to the interaction of the armature windings with the received first magnetic field <NUM>. In aspects using more or fewer than three phases of power, a different corresponding number of receiving windings <NUM> are used. The power is carried from the receiving windings <NUM> to a high frequency three-phase converter <NUM>, such as, for example, one or more insulated-gate bipolar transistors (IGBT), Metal oxide semiconductor field effect transistors (MOSFET), or other controlled switching devices, to increase the frequency of the power to generate the second magnetic field <NUM> at a predefined frequency. The predefined frequency is greater than the difference between the rotational speeds of the compressors <NUM> to which the resonant emitter <NUM> and other components of the electrical extractor <NUM> are connected, and is tuned for power transfer efficiency over the air gap between the resonant emitter <NUM> and the resonant receiver <NUM>. Emitter capacitors 420A-C (generally, emitter capacitor <NUM>) are disposed on each output from the high frequency converter <NUM>, each of which is connected in series with a phase inductor 430A-C (generally, phase winding <NUM>) to form a LC resonant circuit to generate the second magnetic field <NUM> at a pre-determined resonant frequency.

Each phase winding <NUM> receives one phase of high frequency power, and generates one phase of the second magnetic field <NUM>. A corresponding receiver winding 440A-C (generally, receiver winding <NUM>) of the resonant receiver <NUM>, each of which is connected in series with a corresponding receiver capacitor 450A-C (generally, receiver capacitor <NUM>) and forms an LC resonant receiving circuit that receives the second magnetic field <NUM> at the pre-determined resonant frequency to produce a corresponding phase of power for a second current (e.g., I2Φ1, I2Φ2, I2Φ3) from the received second magnetic field <NUM>. Each receiver resonant circuit, inductor or winding <NUM> and capacitor <NUM>, is connected to the power control unit <NUM>. The power control unit <NUM> may convert the power from AC to DC (or AC to AC), increase or reduce the number of phases of the power, make or break an electrical connection to the bus, raise or lower a voltage of the power, raise or lower the frequency of the power, and the like to condition the power for consumption or storage by the vehicle.

Although shown in <FIG> as an LC (Inductive and Capacitive) circuit in a series arrangement, in other aspects the circuitry of the resonant emitter <NUM> and resonant receiver <NUM> may include RLC (Resistive, Inductive, and Capacitive) elements in other arrangements that allow for a resonant magnetic linkage between the resonant emitter <NUM> and the resonant receiver <NUM> when the resonant emitter <NUM> is powered. Other examples include parallel LC circuits, RLC circuits, actively tuned resonant circuits, etc..

<FIG> is a flowchart of a method <NUM> of construction for an electrical generator <NUM>, according to aspects of the present disclosure. Method <NUM> may be performed during initial assembly of a turbine engine <NUM>, during retrofit or repair of a turbine engine <NUM>, or as a pre-assembly operation for components of a turbine engine <NUM>.

Method <NUM> begins with block <NUM>, where a fabricator affixes a permanent magnet <NUM> to a first compressor shaft. In various aspects, the first compressor shaft may be shaft <NUM> associated with the lower-pressure compressor <NUM> or the higher-pressure compressor <NUM> at an interface region between two compressors <NUM>, and the permanent magnet <NUM> is affixed directly or via a first rotor assembly 210A. In various aspects, block <NUM> may be repeated to allow a fabricator to affix a secondary permanent magnet <NUM> to a secondary first compressor shaft (e.g., at a different location on a shaft <NUM> within the primary electrical generator <NUM>) for use in a secondary electrical generator <NUM> in a three-shaft turbine engine <NUM>.

At block <NUM>, a fabricator affixes a second rotor assembly 210B, including an armature-emitter assembly, to the second compressor shaft. For example, the fabricator affixes the second rotor assembly 210B to a shaft <NUM> associated with a lower-pressure compressor <NUM> when the permanent magnet <NUM> is affixed to the shaft <NUM> of the higher-pressure compressor <NUM>, but affixes the second rotor assembly 210B to a shaft <NUM> associated with a higher-pressure compressor <NUM> when the permanent magnet <NUM> is affixed to the shaft <NUM> associated with the lower-pressure compressor <NUM>. The interface region between the first and second compressors <NUM> defines an area that is free of fans or blades of the corresponding compressors <NUM>. In various aspects, block <NUM> may be repeated to allow a fabricator to affix a secondary second rotor assembly 210B to a secondary second compressor shaft (e.g., shaft <NUM> associated with a third compressor 170C) for use in a secondary electrical generator <NUM> in a three-shaft turbine engine <NUM>.

The second rotor assembly 210B includes the armature winding <NUM>, and the resonant emitter <NUM>, and spacers. The spacers arrange the armature winding <NUM> and the resonant emitter <NUM> to position the armature winding <NUM> in the first magnetic field <NUM> and to separate the first magnetic field <NUM> from the second magnetic field <NUM> when the compressors <NUM> rotate relative to one another during operation of the turbine engine <NUM>. The spacers also position the resonant emitter <NUM> at a set location to interface and magnetically couple with the resonant receiver <NUM> when the turbine engine <NUM> is operational.

At block <NUM>, a fabricator affixes a resonant receiver <NUM> to an interior surface of the enclosure <NUM> for the turbine engine <NUM> in relation to the interface region between the two compressors <NUM> and where the second magnetic field <NUM> is produced during operation of the turbine engine <NUM>. In various aspects using a three-shaft design, block <NUM> may be repeated to allow a fabricator to affix a secondary resonant receiver <NUM> to a secondary location on the interior surface of the enclosure <NUM>, corresponding to the interface region between the two compressors <NUM> used by the secondary electrical generator <NUM> and where the secondary second magnetic field <NUM> is produced during operation of the turbine engine <NUM>. Method <NUM> may then conclude.

<FIG> is a flowchart of a method <NUM> for wirelessly extracting electrical energy from a turbine engine <NUM>, according to aspects of the present disclosure. As will be appreciated, in a three-shaft turbine engine <NUM>, method <NUM> may be performed twice in parallel - extracting electrical power from the differential rotation of a primary electrical generator <NUM> and a secondary electrical generator <NUM> located on the interfaces between different pairs of compressors <NUM>.

Method <NUM> begins at block <NUM>, where an operator of the turbine engine <NUM> causes the permanent magnet <NUM> attached to a first compressor 170A of a turbine engine <NUM> to rotate relative to a second compressor 170B of the turbine engine <NUM>. The operator may cause the relative rotation by engaging the turbine engine <NUM> to produce thrust for a vehicle; inducing rotational energy on the compressors <NUM> by the combustion of fuel in a combustion chamber and expelling the exhaust through a turbine region, thus causing the turbines <NUM> to rotate the corresponding shafts <NUM> and thereby rotate the compressors <NUM>. The permanent magnet <NUM>, which may be part of an array of permanent magnets <NUM> connected to a first compressor 170A and arranged radially around the shafts <NUM>, emits a first magnetic field <NUM>. When rotated, the first magnetic field <NUM> induces a first current, as a multiphase alternating current (e.g., I1Φ1-<NUM>), in an armature winding <NUM> that is connected to a second compressor 170B and also arranged radially around the shafts <NUM>. In various aspects, the armature winding <NUM> is arranged coaxially with the permanent magnets <NUM>, planetarily with the permanent magnets <NUM>, or alternatingly coaxially and planetarily with the permanent magnet <NUM> around the shaft <NUM>. Stated differently, the air gap between the permanent magnet <NUM> and the armature winding <NUM> through with the first magnetic field <NUM> propagates may be coaxial to the shafts <NUM>, defined in a plane that intersects the shafts <NUM>, or vary between coaxial or intersecting planes at different locations around the shaft <NUM>.

In various aspects, the "first" compressor 170A may refer to a first one of a high-pressure compressor or a low-pressure compressor in a two-shaft turbine engine <NUM>, and the "second" compressor 170B may refer to the other compressor. Similarly, in a three-shaft turbine engine <NUM>, the "first" compressor 170A may refer to a high-pressure compressor or a low-pressure compressor, in which case the "second" compressor 170B refers to a medium-pressure compressor, or the "first" shaft 170A may refer to the medium-pressure compressor, in which case the "second" shaft 170B may refer to either the high-pressure compressor or the low-pressure compressor. As will be appreciated, the designations of "high-," "medium-," and "low-" pressures are used to refer to different components within the turbine engine <NUM> based on the relative operational pressures between those components. Accordingly, in a given pair of rotors, one shall be understood to be the higher-pressure rotor and the other to be the lower-pressure rotor.

At block <NUM>, the first current (I<NUM>) powers an electromagnet (e.g., a resonant emitter <NUM>) to generate a second magnetic field <NUM> at or above a predefined frequency. In various aspects, the predefined frequency is tuned to the characteristics of the turbine engine <NUM>, including, but not limited to, the distance between the resonant emitter <NUM> and the resonant receiver <NUM>, the relative location in space of the second magnetic field <NUM> to the first magnetic field <NUM> in the electrical generator <NUM>, the relative location of a primary electrical generator <NUM> to a secondary electrical generator <NUM>, the rotational speeds of the compressors <NUM>, etc. In various aspects, the predefined frequency is set high (e.g., at least <NUM>) to thereby reduce losses when wirelessly transferring power via the resonant emitter <NUM> to the resonant receiver <NUM>.

At block <NUM>, a resonant receiver <NUM>, which is disposed on an inner surface of the enclosure <NUM>, converts the radiated electromagnetic field power (e.g., from the rotating second magnetic field <NUM>) into an electrical power output. In various aspects, the electrical power output is a fourth current (I<NUM>) that is provided as a multiphase alternating current (AC) electrical power output, but in other aspects, the electrical output may be single phase and/or direct current (DC), depending on the power consumption characteristics of the vehicle.

At block <NUM>, the resonant receiver <NUM> transfers the power to an electrical bus for use and/or storage by the vehicle. In various aspects, the resonant receiver <NUM> transfers the power output to the bus via a power control unit <NUM>, which may condition the power, convert the power from AC to DC (or DC to AC), reduce or increase the number of phases of the power, make or break an electrical connection to the bus, raise or lower a voltage of the power, raise or lower the frequency of the power, and the like.

Method <NUM> may continue as long the first and second compressors <NUM> rotate relative to each other.

In the current disclosure, reference is made to various aspects. However, it should be understood that the present disclosure is not limited to specific described aspects. Instead, any combination of the following features and elements, whether related to different aspects or not, is contemplated to implement and practice the teachings provided herein, provided such combination is within the scope of the appended claims. Additionally, when elements of the aspects are described in the form of "at least one of A and B," it will be understood that aspects including element A exclusively, including element B exclusively, and including element A and B are each contemplated. Furthermore, although some aspects may achieve advantages over other possible solutions and/or over the prior art, whether or not a particular advantage is achieved by a given aspect is not limiting of the present disclosure. Thus, the aspects, features, aspects and advantages disclosed herein are merely illustrative and are not considered elements or limitations of the appended claims except where explicitly recited in a claim(s).

As will be appreciated by one skilled in the art, aspects described herein may be embodied as a system, method or computer program product. Accordingly, aspects may take the form of an entirely hardware aspect, an entirely software aspect (including firmware, resident software, microcode, etc.) or an aspect combining software and hardware aspects that may all generally be referred to herein as a "circuit," "module" or "system. " Furthermore, aspects described herein may take the form of a computer program product embodied in one or more computer readable storage medium(s) having computer readable program code embodied thereon.

Aspects of the present disclosure are described herein with reference to flowchart illustrations and/or block diagrams of methods, apparatuses (systems), and computer program products according to aspects of the present disclosure.

The flowchart illustrations and block diagrams in the Figures illustrate the architecture, functionality, and operation of possible implementations of systems, methods, and computer program products according to various aspects of the present disclosure. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order or out of order, depending upon the functionality involved.

Claim 1:
A system, comprising:
a first rotor assembly (210A) including a permanent magnet (<NUM>) that emits a first magnetic field (<NUM>) and is suitable to be connected to a first compressor of a turbine engine (<NUM>);
a second rotor assembly (210B) including an armature winding (<NUM>) and
a resonant emitter (<NUM>), wherein the second rotor assembly (210B) is suitable to be connected to a second compressor of the turbine engine at an interface between the first compressor and second compressor such that the armature winding is positioned within the first magnetic field, and the resonant emitted is configured to receive an electrical power input from the armature winding to generate a second magnetic field (<NUM>) of at least a predefined frequency when the first rotor assembly rotates relative to the second rotor assembly; and
a resonant receiver (<NUM>), configured to be disposed on an enclosure (<NUM>) of the turbine engine, positioned in relation to the resonant emitter to receive the second magnetic field and convert the second magnetic field into an electrical power output.