Starter / generator system

Abstract

A starter / generator system including a first motor and a second motor. The first motor has a first rotor and a first stator, where the first rotor is adapted to receive kinetic energy and the first stator includes a first set of windings. The second motor has a rotatable second rotor and a second stator. The second stator is fixed relative to the first stator and the second stator includes a second set of windings.

Description

Technical Field

[0001] This disclosure generally relates to a starter / generator system having first and second motors for starting an engine, and more particularly to a starter / generator system for starting a turbine engine. Background Technology

[0002] A drive mechanism, such as an electric motor or engine, can generate driving force at an output (e.g., at a rotatable output shaft). The output shaft can provide rotational motion to another device via, for example, a rotatable drive shaft connected to the output shaft. This rotational motion can then be used as an energy source for operation. In an exemplary configuration, a gas turbine engine, also known as a combustion turbine engine, is a rotary engine that can obtain at least some energy from a drive mechanism such as a starter. Summary of the Invention

[0003] In one aspect, this disclosure relates to a starter / generator (S / G) system comprising a first motor having a first rotor rotatable relative to a first stator and a second motor having a second rotor rotatable relative to a second stator. The first rotor is adapted to receive a power source, and the first stator includes a first set of windings. The second stator is fixed relative to the first stator and includes a second set of windings. The S / G dynamic input / output is rotatably coupled to the second rotor, and the S / G power output is electrically connected to the second set of windings.

[0004] In another aspect, this disclosure relates to a method of operating a starter / generator (S / G) system. The method includes operating in a first starting mode by dynamically driving a first rotor to generate current in a first set of windings in a first stator. The current generated in the first set of windings is supplied to a second set of windings in a second stator to cause rotation of the second rotor. The second stator rotates the S / G system dynamic input / output to start the engine. Operating in a second generating mode, the S / G dynamic input / output is dynamically driven to rotate the second rotor, thereby generating current in the second set of windings and providing power output to the S / G. Attached Figure Description

[0005] In the attached diagram:

[0006] Figure 1 This is a schematic diagram of a turbine engine with a starter / generator system according to the various aspects described herein.

[0007] Figure 2 Based on the various aspects described in this article Figure 1 A 3D view of the starter / generator system.

[0008] Figure 3 It is along the various aspects described in this article. Figure 2 Line III-III is a schematic cross-sectional view of the starter / generator system.

[0009] Figure 4 It is based on the various aspects described in this article along Figure 2 A schematic cross-sectional view of the starter motor taken from line IV-IV.

[0010] Figure 5 It is based on the various aspects described in this article for use Figure 2 A schematic diagram of the electrical communication of the starter motor.

[0011] Figure 6 yes Figure 1 A schematic diagram of a turbine engine and starter / generator system in a vehicle or structure. Detailed Implementation

[0012] The aspects of this disclosure described herein relate to a turbine engine having a starter including a starter / generator system. For illustrative purposes, this disclosure will be described with respect to a starter for an aircraft turbine engine. For example, this disclosure may be applicable to other vehicles or engines and can be used in industrial, commercial, and residential applications, such as... Figure 6 Further description of the benefits is provided.

[0013] As used herein, the term "upstream" refers to the direction opposite to the direction of fluid flow, and the term "downstream" refers to the direction in the same direction as the fluid flow. The terms "forward" or "before" refer to something in front of it, while "backward" or "after" refer to something behind it. For example, when used in relation to fluid flow, forward / forward can indicate upstream, and backward / afterward can indicate downstream.

[0014] Additionally, as used herein, the term "radial" or "radially" refers to a direction away from a common center. For example, in the context of a turbine engine, radial refers to the direction of a ray extending between the engine's central longitudinal axis and its outer circumference. Furthermore, as used herein, the term "set" or "group" of elements can refer to any number of elements, including only one.

[0015] All directional references (e.g., radial, axial, proximal, distal, up, down, upward, downward, left, right, lateral, front, rear, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, backward, forward, backward, etc.) are used for identification purposes only to aid the reader in understanding this disclosure and do not impose limitations, particularly on the location, orientation, or use of the aspects disclosed herein. Connection references (e.g., attachment, coupling, fixing, fastening, joining, and engagement) should be interpreted broadly and, unless otherwise indicated, may include intermediate members between sets of elements and relative movement between elements. Therefore, connection references do not necessarily imply that two elements are directly connected and have a fixed relationship with each other. Exemplary figures are for illustrative purposes only, and the dimensions, positions, order, and relative dimensions reflected in the accompanying figures are subject to change.

[0016] Additionally, as used herein, "controller" or "controller module" can include components configured or adapted to provide instructions, control, operation, or any form of communication to enable operable components to perform their operations. A controller module can include any known processor, microcontroller, or logic device, including but not limited to: field-programmable gate arrays (FPGAs), application-specific integrated circuits (ASICs), full-authority digital engine control (FADECs), proportional controllers (P), proportional-integral controllers (PI), proportional-derivative controllers (PD), proportional-integral-derivative controllers (PID controllers), hardware-accelerated logic controllers (e.g., for encoding, decoding, transcoding, etc.), the like, or combinations thereof. Non-limiting examples of controller modules may be configured or adapted to run, operate, or otherwise execute program code to achieve operational or functional results, including performing various methods, functions, processing tasks, calculating, comparing, sensing or measuring values, etc., or similar situations, to achieve or implement the technical operations or actions described herein. Operational or functional results may be based on one or more inputs, stored data values, sensed or measured values, correct or incorrect indications, etc. Although described as "program code," non-limiting examples of operable or executable instruction sets can include routines, programs, objects, components, data structures, algorithms, etc., that have the technical effect of performing a specific task or implementing specific abstract data. In another non-limiting example, the controller module may also include a data storage component accessible to the processor, including memory, whether transient, volatile, or non-transient or non-volatile. Other non-limiting examples of memory can include random access memory (RAM), read-only memory (ROM), flash memory, or one or more different types of portable electronic memory, such as optical discs, DVDs, CD-ROMs, flash drives, universal serial bus (USB) drives, etc., or any suitable combination of these types of memory. In one example, program code may be stored in memory in a processor-accessible, machine-readable format. Furthermore, as described herein, memory can store various types of data, perceived or measured data values, input, generated or processed data, or similar data accessible to the processor when providing instructions, control, or operations to affect the functional or operable results described herein.

[0017] Additionally, as used herein, an element described as “electrical connection,” “electrical link,” or “in signal communication” may include the transmission, reception, or communication of electrical signals to or from the element of the connection or link. Furthermore, such an electrical connection or link may include wired or wireless connections, or a combination of both.

[0018] Reference Figure 1A starter, such as the starter of a starter / generator (S / G) system 10, is coupled to an accessory gearbox (AGB) 12, also known as a transmission housing, and together is schematically shown mounted to a turbine engine 14 (e.g., a gas turbine engine). The turbine engine 14 includes an intake port with a fan 16 that supplies air to a high-pressure compression zone 18. The intake port with fan 16 and the high-pressure compression zone are collectively referred to as the "cold section" of the turbine engine 14 upstream of combustion. The high-pressure compression zone 18 supplies high-pressure air to the combustion chamber 20. Inside the combustion chamber, the high-pressure air mixes with fuel and burns. Before exiting the turbine engine 14, the hot and pressurized combustion gases pass through a high-pressure turbine zone 22 and a low-pressure turbine zone 24. As the pressurized gas passes through the high-pressure turbine (not shown) of the high-pressure turbine zone 22 and the low-pressure turbine (not shown) of the low-pressure turbine zone 24, the turbines extract rotational energy from the gas flow passing through the turbine engine 14. The high-pressure turbine in high-pressure turbine region 22 is connected to the compression mechanism (not shown) in high-pressure compression region 18 via a shaft, thereby powering the compression mechanism. The low-pressure turbine is connected to the fan 16 at the air inlet via a shaft, thereby powering the fan 16.

[0019] The turbine engine 14 is a turbofan engine commonly used in modern commercial and military aviation, such as the General Electric GEnx or CF6 series engines, or it can be any of the other known turbine engines, such as a turboprop or turbine shaft. The turbine engine may also have an afterburner that burns an additional amount of fuel downstream of the low-pressure turbine region 24 to increase the velocity of the exhaust gases and thereby increase thrust.

[0020] The AGB 12 is coupled to the turbine engine 14 at either the high-pressure turbine region 22 or the low-pressure turbine region 24 via a mechano-powered takeoff device 26. The mechano-powered takeoff device 26 includes multiple gears and means for mechanically coupling the AGB 12 to the turbine engine 14. During startup operating conditions, the S / G system 10 can utilize an energy source to drive kinetic energy or power from the S / G system 10 to initiate the self-sustaining combustion or "normal operation" conditions of the gas turbine engine 14. For example, in a non-limiting example, pressurized air can be used to initiate the rotation of a set of rotors of the turbine engine 14 via the AGB 12 and the mechano-powered takeoff device 26 until the rotational speed of the rotors is high enough to initiate the self-sustaining combustion cycle of the turbine engine operation. Under normal operating conditions, the mechano-powered takeoff device 26 converts power from the turbine engine 14 to the AGB 12, thereby powering aircraft accessories such as, but not limited to, fuel pumps, electrical systems, and cabin environmental controls. The S / G system 10 can be installed on the outside of the air intake area containing the fan 16 or on the core near the high-pressure compression area 18.

[0021] Reference Figure 2 The S / G system 10 is shown in more detail. Typically, the S / G system 10 includes a housing 30 defining an inlet 32, an outlet 34, and a fluid flow path 36 extending between the inlet 32 ​​and the outlet 34 for allowing fluid flow through it. In a non-limiting example, the fluid is air, such as pressurized air, supplied from a pressurized air source, including but not limited to a ground-operated air cart, an auxiliary power unit, or a cross-emission originating from an already operating engine. The S / G system 10 includes a journal within the housing 30 and a turbine system 38 disposed within the flow path 36 for rotatably extracting mechanical power from the gas flow along the flow path 36. An electric motor system 42 is mounted within the housing 30. The motor system 42 may include an S / G dynamic input / output 44 and an S / G power output 46, that is, the S / G dynamic input / output may be adapted or operable to receive dynamic input or supply or provide dynamic output, wherein electricity, current, voltage, power, etc. may be supplied from the S / G system 10 to another component, such as a power distribution system or an electrical load.

[0022] Figure 3 It is along Figure 2 The cross-section of line III-III further illustrates the S / G system 10, which may include a turbine system 38 and a motor system 42. The turbine system 38 of the S / G system 10 may include, but is not limited to, a stationary portion 47 that can at least direct air in the flow path 36 to the rotatable portion 48. The rotatable portion 48 may include a set of rotor blades 49 coupled to a drive shaft 51 capable of rotating about the centerline 50 of the S / G system 10. Alternatively, the blades 49 or the drive shaft 51 may rotate relative to the S / G system 10 about any axis.

[0023] The motor system 42 may include a first motor 52 and a second motor 62. The first motor 52 may be an internal machine, and the second motor may be an external machine. As shown, as a non-limiting example, the first motor 52 may be positioned or arranged concentrically, coaxially, or opposite to the second motor 62. In other words, the second motor 62 may at least partially enclose, cover, or receive the first motor 52 within a radial cavity of the second motor 62. The second motor 62 may be concentric or coaxial with the first motor 52. That is, the second motor 62 may be located at the same or similar axial position as the first motor 52, or the second motor 62 may be located at a greater radial distance than the first motor 52. It is conceivable that the second motor 62 at least partially axially covers the first motor 52. Alternatively, the second motor 62 may not axially cover the first motor 52. Furthermore, any position or orientation of the first motor 52 and the second motor 62 is contemplated.

[0024] The motor system 42 may include a magnetic shield 70, a power source or drive shaft 51, and a carrier 90. The first motor 52 may include a first rotor 54 rotatably connected to the drive shaft 51 and configured to rotate relative to a stationary (i.e., non-rotating) first stator 56. As a non-limiting example, the first rotor 54 may be an inner rotor. The first stator 56 may include a first set of windings 58.

[0025] The second motor 62 may include a second rotor 64, which is rotatable relative to a fixed second stator 66 and rotatably connected to the S / G dynamic input / output 44. The second rotor 64 may be an external rotor. As explained herein, the first rotor 54 and the second rotor 64 may rotate independently. The second stator 66 may include a second set of windings 68 electrically connected to the S / G power output 46. The first stator 56 and the second stator 66 are fixed relative to the housing 30. Further envisioned, the first set of windings 58 of the first stator 56 may selectively communicate electrically with the second set of windings 68 of the second stator 66. That is, when selective communication is possible, current may flow between the first set of windings 58 and the second set of windings 68.

[0026] Magnetic shielding 70 may be included in motor system 42. Magnetic shielding 70 may define a magnetic isolation layer to magnetically separate or isolate the first motor 52 from the second motor 62. As shown, as a non-limiting example, magnetic shielding 70 may be a radial shield between the first stator 56 and the second stator 66. As a non-limiting example, magnetic shielding 70 may include a high-permeability metal alloy, such as permalloy and / or molybdenum sheet. Alternatively, magnetic shielding 70 may include a nanocrystalline ferromagnetic metal coating, other high-nickel alloys, or copper.

[0027] The S / G system 10 may include an S / G housing 72 that limits at least one of a first motor 52 or a second motor 62. The S / G housing 72 may be coupled to or formed as part of a housing 30. The S / G housing 72 or the housing 30 may include or be coupled to a receiving portion 74, which may receive or be fixed to a magnetic shield 70.

[0028] Drive shaft 51 rotatably connects the rotatable portion 48 of turbine system 38 to the first rotor 54 of first motor 52. Drive shaft 51 allows mechanical or kinetic energy to be transferred from the rotatable portion 48 to the first rotor 54. Although illustrated as drive shaft 51, it is conceivable that the first rotor 54 can be adapted to receive any power source or rotation.

[0029] At least one pair of shaft bearings 82 rotatably supports the drive shaft 51. Although two shaft bearings 82 are illustrated, any number or type of known bearings can be expected to rotatably support the drive shaft 51.

[0030] The carrier 90 can connect the second rotor 64 to the S / G dynamic input / output 44. The carrier 90 may include a rotatable radial arm that carries at least the second rotor 64 at a radial distance spaced from the drive shaft 51. It is conceivable that the distance from the drive shaft 51 to the carrier of the second rotor 64 is a larger radial distance than the radial distance from the drive shaft 51 to the first rotor 54, the first stator 56, or the second stator 66.

[0031] The carrier bearing 92 rotatably supports the carrier 90. Although two carrier bearings 92 are shown, it is contemplated that any number or type of known bearings can be used to rotatably support the carrier 90. A component 94 of the AGB 12, such as a splined interface as a non-limiting example, can be coupled to the S / G dynamic input / output 44. That is, the S / G dynamic input / output 44 can transfer mechanical power or kinetic energy from the motor system 42 to the AGB 12.

[0032] The S / G system 10 is envisioned to contain a lubricant, including but not limited to grease or oil, to provide lubrication and cooling to moving parts, which may include, but are not limited to, drive shaft 51, shaft bearing 82, carrier 90, carrier bearing 92, first rotor 54, second rotor 64, or S / G dynamic input / output 44.

[0033] The S / G starter 10 can be formed from any known materials and by any method, including but not limited to additives or die casting of high-strength and lightweight metals such as aluminum, stainless steel, iron, or titanium. The housing 30, S / G housing 72, turbine system 38, and motor system 42 can be formed to have sufficient thickness to provide adequate mechanical rigidity without adding unnecessary weight to the S / G system 10 and thus to the aircraft.

[0034] The drive shaft 51 and the S / G dynamic input / output 44 can be constructed using any known materials and methods, including but not limited to additive manufacturing, extrusion, or machining of high-strength metal alloys, such as those containing aluminum, iron, nickel, chromium, titanium, tungsten, vanadium, or molybdenum. The diameter of the drive shaft 51 or the S / G dynamic input / output 44 can be fixed or vary along its axial length.

[0035] Figure 4 It is along Figure 2Another cross section of line IV-IV is shown to further illustrate a portion of the motor system 42. Permanent magnets 96 may be included in the first rotor 54 or the second rotor 64. It is contemplated that any number of permanent magnets 96 may be located at the first rotor 54 or the second rotor 64. Furthermore, the set of permanent magnets 96 may be circumferentially spaced around the surfaces of the respective rotors 54, 64 facing the respective stators 56, 66. Similarly, any number of windings may be used in the first set of windings 58 and the second set of windings 68. It is conceivable that at least one of the first stator 56 or the second stator 66 may be configured or wound to operate in a three-phase stator winding configuration or a six-phase stator winding configuration. In another non-limiting example, it is contemplated that at least one of the first stator 56 or the second stator 66 may be configured to operate optionally in a three-phase stator winding configuration or a six-phase stator winding configuration. In yet another non-limiting example, the first stator 56 may be configured, wound, or optionally configured to operate with a different winding configuration relative to the second stator 66 (e.g., the first stator 56 may be selected to operate with a three-phase stator winding configuration, while the second stator 66 may be selected to operate with a six-phase stator winding configuration).

[0036] As described herein, in the first start-up mode, air supplied along flow path 36 causes the blades 49 of the rotatable portion 48 of turbine system 38 to rotate, thereby driving the rotation of drive shaft 51. Drive shaft 51 rotates first rotor 54. First rotor 54 may be a permanent magnet rotor, which provides a change in magnetic flux through a first set of windings 58 housed by first stator 56. The change in magnetic flux induces a current in the first set of windings 58. Optional electrical connection between the first set of windings 58 and the second set of windings 68 can result in a changing magnetic field at second stator 66, which induces rotation of second rotor 64 and carrier 90. Second rotor 64 is coupled to S / G dynamics input / output 44 at least via carrier 90. S / G dynamics input / output 44 can then provide rotational or mechanical power to engine 14 to, for example, perform the engine 14 start-up process, as described herein.

[0037] Conversely, during operation in the second power generation mode, power or rotational input can be supplied from engine 14 to the S / G dynamic input / output 44 and the second motor 62 during normal operation of engine 14. The S / G dynamic input / output 44 causes the second rotor 64 to rotate, thereby inducing current in the second set of windings 68. The second set of windings 68 can provide electrical power output via the S / G power output 46. In this second power generation mode, little or no air is supplied to inlet 32, and the first motor 52 is not utilized or is disabled.

[0038] like Figure 5As shown, the first winding 58 can be selectively electrically connected to the second winding 68. That is, the first conductive connection 100 having a first terminal 102 can be selectively connected or connectable to a second conductive connection 104 having a second terminal 106 via a switch or a first optional connector 108, the second terminal 106 being selectively conductively connected or connectable to the second winding 68. When the first optional connector 108 is selected, the induced current generated in the first winding 58 is provided to the second winding 68, thereby inducing a magnetic field at the second winding 68. Alternatively, the device 110 can change the flow of the induced current as it flows between the first winding 58 and the second winding 68. As a non-limiting example, the device 110 can be one or more of a controller, transformer, motor, generator, or exciter to operatively or controllably excite the induced magnetic field at the second winding 68. Alternatively, the device 110 may be used as a non-limiting example to controllably switch or modify the effective use of the three-phase or six-phase windings, control the output of the second set of windings 68 to ensure the required power, or switch from the first start-up mode to the second power generation mode.

[0039] When current flows through the second set of windings 68, the second rotor 64 can be induced or encouraged to rotate. For example, the permanent magnets of the second rotor 64 can rotate in response to the induced magnetic field, thereby generating torque on the second rotor 64 or the carrier 90. The rotation of the second rotor 64 or the carrier 90, in turn, causes the S / G dynamic input / output 44 to rotate. Thus, during the first start-up mode, the S / G system 10 can be a drive mechanism for the turbine engine 14 via the rotation of the drive shaft 51, the first rotor 54 and the second rotor 64, and the S / G dynamic input / output 44 to initiate self-sustaining operation of the turbine engine 14. As a non-limiting example, the S / G dynamic input / output 44 is coupled to a component 94 of the AGB 12, which provides mechanical energy to the turbine engine 14 for starting the turbine engine 14. It is conceivable that during the first start-up mode, at least one of the first stator 56 or the second stator 66 can operate together with the six-phase stator windings. Operating with six-phase stator windings produces greater torque on the S / G dynamic input / output 44 compared to using three-phase stator windings.

[0040] Alternatively, the S / G power output 46 can provide electrical power input to the second set of windings 68. As a non-limiting example, when a switch or the second optional connector 114 connects the third terminal 116 of the S / G power output 46 to the second terminal 106 and the second conductive connection 104, the power distribution system or power source 112 can provide power to the second set of windings 68 of the second stator 66. As described herein, the power source 112 may include, but is not limited to, a battery or another power source or system, such as the power distribution system of an aircraft. The power source 112 can provide power to the S / G power output 46, which can input power to the second set of windings 68 during the first startup mode. It is anticipated that the first optional connector 108 or the second optional connector 114 can provide power to the second set of windings 68 individually or in any combination during the first startup mode.

[0041] Further envisioning, the exciter 118 can be used to controllably excite the rotation of the second rotor 64. The exciter 118 can be powered by current from the first set of windings 58. Alternatively, the exciter 118 can be powered by current from the power supply 112. The exciter 118 can include an exciter stator powered by either the first set of windings 58 or the power supply 112. The exciter stator can then sense the rotation of the exciter rotor. The exciter rotor can be coupled to a rotating rectifier to provide additional torque to the second rotor 64. Alternatively, the exciter stator can provide additional torque to the second rotor 64 using any known technique.

[0042] Once the turbine engine 14 is started, the motor system 42 can enter or otherwise operate in the second power generation mode. When the motor system 42 is ready to operate in the second power generation mode, the first optional connector 108 can be selectively opened or closed, thereby stopping the electrical connection between the first set of windings 5 ​​and the second set of windings 68. Optionally, the airflow through the flow path 36 can be reduced or stopped before, during, or after switching from the first start-up mode to the second power generation mode. Due to the turbine engine 14, at least component 94 of AGB 12 continues to rotate. That is, the started turbine engine 14 kinematically drives the S / G kinematic input / output 44. The rotation of the S / G kinematic input / output 44 causes the second rotor 64 to rotate via the carrier 90. The rotation of the second rotor 64 can change the magnetic flux through the second set of windings 68 housed in the second stator 66. The change in magnetic flux through the second set of windings 68 induces a current in the second set of windings 68. When the second optional connector 114 is closed and the second terminal 106 is connected to the third terminal 116, power can flow from the second set of windings 68 to the power source 112 via the S / G power output 46. The power source 112 can then output or supply power to various electrical systems or rechargeable batteries. It is conceivable that the power source 112 can be at least part of a power distribution system for supplying power to other components of the engine 14.

[0043] Alternatively, the motor system 42 can be considered a hybrid starter / generator capable of outputting both mechanical and electrical power. The motor system 42 can operate as a magnetic gearbox during a first starting mode, providing the mechanical energy required to start the engine 14. Once the engine 14 is started, the motor system 42 can operate as a generator during a second-generation mode. That is, the motor system 42 can convert the rotational energy input from the started engine 14 into electrical energy output.

[0044] In addition to those shown in the accompanying drawings above, this disclosure also contemplates many other possible structural and electrical examples and configurations. Furthermore, the design and arrangement of various components, such as AGB 12, motor system 42, or S / G system 10 or its parts, can be rearranged to enable many different ordered arrangements.

[0045] Figure 6 yes Figure 1 A schematic diagram of the turbine engine 14 and the starter / generator system 10. (See diagram below.) Figure 1 As shown, the turbine engine 14 can be in the transport work or structure 200. As a non-limiting example, the transport work or structure 200 can be a helicopter or other aircraft, a ship or other water vehicle, or a car or other land-based transport work. Furthermore, the transport work or structure 200 can be, but is not limited to, an offshore power station, a wind turbine, or a small power station. Further, the turbine engine 14 can be any engine used for the transport work or structure 200 with a turbine carrying the required starter / generator 10.

[0046] Benefits associated with aspects of this disclosure include an S / G system capable of operating in a first start-up mode when the turbine engine is started and in a second power generation mode after the turbine engine has started. Conventionally, after the turbine engine is started, the starter becomes the weight of the aircraft or turbine-driven vehicle. However, the S / G system also includes a second power generation mode in which the S / G system continuously supplies power to the aircraft or turbine-driven vehicle.

[0047] Other advantages include the ability to provide greater torque for starting the engine when supplied with high-pressure air. The first and second motors of the S / G system or motor consist of different numbers of magnetic poles to achieve speed increase / decrease functionality. The higher pole number of the electrical current transmitted from the first motor to the second motor can generate higher torque.

[0048] This written description uses examples to illustrate various aspects of the disclosure described herein, including best practices, and also enables those skilled in the art to practice aspects of the disclosure, including making and using any device or system and performing any merging methods. The patentable scope of various aspects of this disclosure is defined by the claims and may include other examples that occur to those skilled in the art. Such other examples having structural elements that are not indistinguishable from the language of the claims, or containing structural elements that are equally different from the language of the claims but not substantially different from the language of the claims, are within the scope of the claims.

[0049] Further aspects of the invention are provided by way of the subject matter of the following clauses:

[0050] 1. A starter / generator (S / G) system comprising: a first motor having a first rotor rotatable relative to a first stator, the first rotor being adapted to receive a power source, and the first stator having a first set of windings; a second motor having a second rotor rotatable relative to a second stator, the second stator being fixed relative to the first stator, the second stator having a second set of windings; an S / G dynamic input / output rotatably connected to the second rotor; and an S / G power output electrically connected to the second set of windings.

[0051] 2. According to any S / G system in the preceding paragraph, wherein the second motor is concentric with the first motor.

[0052] 3. According to any S / G system in the preceding paragraph, wherein the second motor at least partially axially covers the first motor.

[0053] 4. According to any S / G system in the preceding paragraph, wherein the first motor and the second motor are coaxial.

[0054] 5. According to any S / G system in the preceding paragraph, wherein the magnetic shielding radially separates the first motor from the second motor.

[0055] 6. According to any S / G system in the preceding paragraph, wherein the first rotor and the second rotor are capable of rotating independently.

[0056] 7. According to any S / G system in the preceding paragraph, wherein the power source is a turbine and the S / G system is an air turbine starter / generator.

[0057] 8. According to any S / G system in the preceding paragraph, wherein the second set of windings may be selectively connected between the first set of windings and the S / G power output.

[0058] 9. According to any S / G system in the preceding paragraph, wherein the S / G system operates in a first starting mode, whereby the power source rotatably drives a first rotor to generate current in a first set of windings, wherein the current generated in the first set of windings is supplied to a connected second set of windings, wherein the current supplied to the second set of windings causes the second rotor to rotate, and wherein the rotational operation of the S / G dynamic input / output is to start the engine.

[0059] 10. A gas turbine engine according to any of the S / G systems in the preceding paragraph, wherein the S / G dynamic inputs / outputs are operated to start the gas turbine engine.

[0060] 11. According to any S / G system in the preceding paragraph, wherein the S / G operates in a second power generation mode, thereby dynamically driving the S / G dynamic input / output by the started gas turbine engine, wherein the rotation of the second rotor relative to the second stator generates current in the second set of windings, and wherein the current generated in the second set of windings is provided to the connected S / G power output.

[0061] 12. According to any S / G system in the preceding paragraph, at least one of the first rotor or the second rotor is a permanent magnet rotor.

[0062] 13. According to any S / G system in the preceding paragraph, at least one of the first stator or the second stator is selectively operable with a three-phase stator winding or a six-phase stator winding.

[0063] 14. According to any S / G system in the preceding paragraph, wherein during the first start-up mode, at least one of the first stator or the second stator is capable of operating with a six-phase stator winding, and wherein operating with a six-phase stator winding produces a greater torque on the S / G dynamic input / output compared to operating with a three-phase stator winding.

[0064] 15. A method of operating a starter / generator (S / G) system, comprising: dynamically driving a first rotor to generate current in a first set of windings in a first stator; supplying the current generated from the first set of windings to a second set of windings in a second stator to cause rotation of the second rotor, thereby operating in a first starting mode, wherein the rotation of the second rotor causes the S / G system dynamic input / output to rotate, thereby starting an engine; and dynamically driving the S / G dynamic input / output to cause the second rotor to rotate to generate current in the second set of windings for supplying power output to the S / G, thereby operating in a second power generation mode.

[0065] 16. According to any of the methods in the preceding paragraph, wherein the operation in the second power generation mode occurs after the engine is started.

[0066] 17. According to any method in the preceding paragraph, it further includes: when operating in the first start-up mode, controllably supplying the current generated in the first set of windings to the exciter to controllably excite the rotation of the second rotor.

[0067] 18. According to any method in the preceding paragraph, wherein when operating in the first start-up mode, providing the current generated in the first set of windings further includes providing additional current from the power source to the second set of windings to further induce rotation of the second rotor.

[0068] 19. According to any method in the preceding paragraph, wherein at least a portion of the first rotor and the second rotor are concentric.

[0069] 20. According to any of the methods in the preceding paragraph, wherein during the first start-up mode, a pressurized air source is received at the input of the S / G to drive the rotation of the first rotor.

Claims

1. A starter / generator system, characterized in that, include: A first motor having a first rotor rotatable relative to a first stator, the first rotor being adapted to receive a power source, and the first stator having a first set of windings; The second motor has a second rotor that is rotatable relative to a second stator, the second stator being fixed relative to the first stator, and the second stator having a second set of windings; Starter / generator dynamic input / output rotatably connected to the second rotor; and The starter / generator power output electrically connected to the second set of windings; The starter / generator system operates in a first starting mode, wherein the power source rotatably drives the first rotor to generate current in the first set of windings, wherein the current generated in the first set of windings is provided to a connected second set of windings, wherein the current provided to the second set of windings causes the second rotor to rotate, and wherein the rotational operation of the starter / generator dynamic input / output is used to start the gas turbine engine. and The starter / generator operates in a second power generation mode after the gas turbine engine is started, in which the gas turbine engine dynamically drives the starter / generator's dynamic input / output, wherein the rotation of the second rotor relative to the second stator generates current in the second set of windings, and wherein the current generated in the second set of windings is provided to the connected starter / generator's power output.

2. The starter / generator system according to claim 1, characterized in that, The second motor is concentric with the first motor.

3. The starter / generator system according to claim 2, characterized in that, The second motor at least partially covers the first motor axially.

4. The starter / generator system according to claim 3, characterized in that, The first motor and the second motor are coaxial.

5. The starter / generator system according to claim 4, characterized in that, The magnetic shielding component radially separates the first motor from the second motor.

6. The starter / generator system according to any one of claims 1-5, characterized in that, The first rotor and the second rotor can rotate independently.

7. The starter / generator system according to any one of claims 1-5, characterized in that, The power source is a turbine, and the starter / generator system is an air turbine starter / generator.

8. The starter / generator system according to any one of claims 1-5, characterized in that, The second set of windings is connected between the first set of windings and the starter / generator power output.

9. The starter / generator system according to claim 1, characterized in that, The operation in the first start-up mode includes controllably providing the current generated in the first set of windings to the exciter to controllably excite the rotation of the second rotor.

10. The starter / generator system according to claim 1, characterized in that, Further includes: A housing that defines an inlet, an outlet, and a fluid flow path extending between the inlet and the outlet; and A turbine system including a rotatable portion, wherein the turbine system is journaled within the housing and disposed within the flow path for rotatably extracting mechanical power from a gas flow along the flow path; In the first start-up mode, air supplied along the flow path causes the blades of the rotatable part to rotate, thereby driving the drive shaft, which in turn causes the first rotor to rotate.

11. The starter / generator system according to any one of claims 1-5, characterized in that, At least one of the first rotor or the second rotor is a permanent magnet rotor.

12. The starter / generator system according to any one of claims 1-5, characterized in that, At least one of the first stator or the second stator can be selectively operated together with a three-phase stator winding or a six-phase stator winding.

13. The starter / generator system according to claim 12, characterized in that, During the first start-up mode, at least one of the first stator or the second stator is capable of operating together with the six-phase stator winding, and wherein operating together with the six-phase stator winding produces greater torque on the starter / generator dynamic input / output compared to operating together with the three-phase stator winding.

14. A gas turbine engine comprising the starter / generator system of claim 9, characterized in that, The starter / generator dynamics input / output is operated to start the gas turbine engine.

15. A method for operating a starter / generator system, characterized in that, The method includes: By dynamically driving a first rotor to generate current in a first set of windings in a first stator, and supplying said current from the first set of windings to a second set of windings in a second stator to cause rotation of the second rotor, operation is performed in a first starting mode, wherein said rotation of the second rotor causes the starter / generator system dynamic input / output to rotate, thereby starting the engine; and By dynamically driving the starter / generator dynamic input / output to rotate the second rotor, a current is generated in the second set of windings to supply the power output of the starter / generator, thereby operating in a second power generation mode.

16. The method according to claim 15, characterized in that, The operation in the second power generation mode occurs after the engine is started.

17. The method according to claim 15, characterized in that, Also includes: When operating in the first startup mode, the current generated in the first set of windings is controllably supplied to the exciter to controllably excite the rotation of the second rotor.

18. The method according to any one of claims 15 to 17, characterized in that, When operating in the first startup mode, providing the current generated in the first set of windings also includes providing additional current from the power source to the second set of windings to cause the rotation of the second rotor.

19. The method according to any one of claims 15 to 17, characterized in that, At least a portion of the first rotor and the second rotor are concentric.

20. The method according to any one of claims 15 to 17, characterized in that, During the first start-up mode, a pressurized air source is received at the input of the starter / generator to drive the rotation of the first rotor.

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