Propulsion system with control system for determining health information

Abstract

A propulsion system is provided having: a gas turbine engine having a turbine including a compressor, a turbine, and a shaft rotatable with the turbine; and a power assembly including: a motor rotatable with the shaft; and a control system in electrical communication with the electric machine, the control system configured to receive data from the electric machine indicative of power flowing to or out of the electric machine, and determine health information of the gas turbine engine in response to the received data.

Description

Technical Field

[0001] The present subject matter relates generally to propulsion systems, such as hybrid electric propulsion systems for vehicles, such as aircraft vehicles. Background Art

[0002] A gas turbine engine generally includes a turbine and a rotor assembly. A gas turbine engine, such as a turbofan engine, can be used for aircraft propulsion. In the case of a turbofan engine, the rotor assembly can be configured as a fan assembly.

[0003] The gas turbine engine may be part of a hybrid electric propulsion system that also includes one or more electric machines capable of rotating with the gas turbine engine.A control system capable of operating with a hybrid electric propulsion system to provide desired operations of the hybrid electric propulsion system would be welcome in the art. BRIEF DESCRIPTION OF THE DRAWINGS

[0004] A complete and enabling disclosure of the present disclosure, including the best mode thereof, to one of ordinary skill in the art is set forth in the specification with reference to the accompanying drawings, in which:

[0005] Figure 1 is a top view of an aircraft according to various exemplary embodiments of the present disclosure.

[0006] Figure 2 yes Figure 1 A side view of an exemplary aircraft.

[0007] Figure 3 is a schematic cross-sectional view of a gas turbine engine according to an exemplary embodiment of the present disclosure, which may be mounted to Figure 1 On an exemplary aircraft.

[0008] Figure 4 is a schematic diagram of a propulsion system according to an exemplary embodiment of the present disclosure.

[0009] Figure 5 is a graph of a raw data signal according to an exemplary aspect of the present disclosure.

[0010] Figure 6 is a graph of a processed data signal according to an exemplary aspect of the present disclosure.

[0011] Figure 7 is a graph of a processed data signal according to another exemplary aspect of the present disclosure.

[0012] Figure 8 is a graph of a processed data signal according to yet another exemplary aspect of the present disclosure.

[0013] Fig. 9is a schematic diagram of a propulsion system according to another exemplary embodiment of the present disclosure.

[0014] Fig.10 is a schematic diagram of a propulsion system according to yet another exemplary embodiment of the present disclosure.

[0015] Fig.11 is a flow chart of a method of operating a propulsion system according to an exemplary aspect of the present disclosure.

[0016] Fig.12 is a schematic diagram of a controller according to an exemplary embodiment of the present disclosure. DETAILED DESCRIPTION

[0017] Reference will now be made in detail to the present embodiments of the present disclosure, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. The same or similar names in the drawings and description have been used to refer to the same or similar parts of the present disclosure.

[0018] As used herein, the word "exemplary" means "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other implementations. In addition, unless expressly stated otherwise, all embodiments described herein should be considered exemplary.

[0019] The singular forms "a," "an," and "the" include plural referents unless the context clearly dictates otherwise.

[0020] For example, the term “at least one” in the context of “at least one of A, B, and C” means only A, only B, only C, or any combination of A, B, and C.

[0021] As used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another, and are not intended to indicate the position or importance of each component.

[0022] The terms "front" and "rear" refer to relative positions within a gas turbine engine or vehicle and refer to the normal operating attitude of the gas turbine engine or vehicle. For example, for a gas turbine engine, front refers to a position closer to the engine inlet and rear refers to a position closer to the engine nozzle or exhaust.

[0023] The terms "upstream" and "downstream" refer to the relative directions of flow in a path. For example, with respect to fluid flow, "upstream" refers to the direction from which the fluid is flowing, while "downstream" refers to the direction to which the fluid is flowing. However, the terms "upstream" and "downstream" as used herein may also refer to the flow of electrical current.

[0024] Here and throughout the specification and claims, range limitations are combinable and interchangeable, and unless context or language dictates otherwise, these ranges are identified and include all sub-ranges contained therein. For example, all ranges disclosed herein include the endpoints, and the endpoints are independently combinable with each other.

[0025] The present disclosure generally relates to a propulsion system including a gas turbine engine and an electric power assembly. Therefore, the propulsion system may be referred to as a hybrid electric propulsion system. The gas turbine engine includes a turbine including a compressor, a turbine, and a shaft capable of rotating with the turbine. In addition, the electric power assembly includes an electric motor capable of rotating with the shaft and a control system electrically connected to the electric motor.

[0026] The control system is configured to receive data indicative of power flowing to or from the electric machine from the electric machine and determine health information of the gas turbine engine in response to the received data. A converter component of the control system may receive the data and provide it to a system controller of the control system. The converter component or the control system may process a signal indicative of the data and compare it to a library of processed signal patterns to determine the health information.

[0027] Such a control system may allow high bandwidth feedback from the hybrid power architecture to determine health information, such as engine faults and / or significant changes in engine health, and may also allow corrective actions to be indicated and initiated via the electric machine or through primary engine control (e.g., FADEC).

[0028] Referring now to the drawings, in which like numerals refer to like elements throughout the several views, Figure 1 A top schematic diagram of an aircraft 10 having a hybrid electric propulsion system 50 according to another exemplary embodiment of the present disclosure is provided, and Figure 2 Provided Figure 1 A side view of an exemplary aircraft. Specifically, Figure 1 and Figure 2 An aircraft 10 is shown that defines a longitudinal centerline 14 extending therethrough, a lateral direction L, a front end 16, and a rear end 18. The aircraft 10 includes a fuselage 12, a tail 19, a first wing 20, and a second wing 22. The first wing 20 and the second wing 22 each extend laterally outward relative to the longitudinal centerline 14. The first wing 20 and a portion of the fuselage 12 together define a first side 24 of the aircraft 10, while the second wing 22 and another portion of the fuselage 12 together define a second side 26 of the aircraft 10. For the illustrated embodiment, the first side 24 of the aircraft 10 is configured as the port side of the aircraft 10, while the second side 26 of the aircraft 10 is configured as the starboard side of the aircraft 10.

[0029] Each wing 20, 22 in the illustrated exemplary embodiment includes one or more leading edge flaps 28 and one or more trailing edge flaps 30. The aircraft 10 also includes, or more precisely, the tail 19 of the aircraft 10 includes a vertical stabilizer 32 having a rudder flap (not shown) for yaw control, and a pair of horizontal stabilizers 34, each having a lift flap 36 for pitch control. The fuselage 12 also includes an outer surface or skin 38. However, it should be understood that in other exemplary embodiments of the present disclosure, the aircraft 10 may additionally or alternatively include any other suitable configuration. For example, in other embodiments, the aircraft 10 may include stabilizers of any other configuration.

[0030] Figure 1 The exemplary aircraft 10 in FIG. 1 also includes a hybrid electric propulsion system 50 having a first gas turbine engine 100A, a second gas turbine engine 100B, and an electrical energy storage unit 55. For the illustrated embodiment, the first gas turbine engine 100A and the second gas turbine engine 100B are both configured in an underwing mounted configuration.

[0031] Reference now Figure 3 , a schematic cross-sectional view of a gas turbine engine 100 is provided. Figure 1 and Figure 2 The first and second gas turbine engines 100A, 100B shown in FIG. 1 may be operated with Figure 3 The exemplary engine 100 is configured in a similar manner.

[0032] Figure 3 The gas turbine engine 100 is more specifically configured as a turbofan engine 100, including a turbine 102 and a fan 104. Figure 3 As shown, the turbofan 100 defines an axial direction A1 (extending parallel to the longitudinal axis 101 for reference) and a radial direction R1 . As depicted, the turbofan 100 includes a fan 104 and a turbine 102 located downstream of the fan 104 .

[0033] The illustrated exemplary turbomachine 102 generally includes a generally tubular casing 106 defining an annular inlet 108. The casing 106 surrounds, in series flow relationship, a compressor section including a supercharger or low pressure (LP) compressor 110 and a high pressure (HP) compressor 112; a combustion section 114; a turbine section including a first high pressure (HP) turbine 116 and a second low pressure (LP) turbine 118; and an ejection exhaust nozzle section 120. The compressor section, the combustion section 114, and the turbine section together at least partially define a core air flow path 121.

[0034] The exemplary turbine 102 of the turbofan 100 also includes one or more shafts that can rotate with at least a portion of the turbine section and at least a portion of the compressor section (for the illustrated embodiment). More specifically, for the illustrated embodiment, the turbofan 100 includes a high pressure (HP) shaft or spool 122 that drives the HP turbine 116 to the HP compressor 112. In addition, the exemplary turbofan 100 includes a low pressure (LP) shaft or spool 124 that drives the LP turbine 118 to the LP compressor 110.

[0035] In addition, the exemplary fan 104 shown is configured as a variable pitch fan having a plurality of fan blades 128 coupled to a disk 130 in a spaced apart manner. The fan blades 128 extend outwardly from the disk 130 generally in a radial direction R1. Each fan blade 128 is rotatable about a respective pitch axis P1 relative to the disk 130 by virtue of the fan blades 128 being operably coupled to appropriate actuating members 132 configured to collectively vary the pitch of the fan blades 128. The fan 104 is mechanically coupled to the LP shaft 124 such that the fan 104 is mechanically driven by the second LP turbine 118. More specifically, the fan 104, including the fan blades 128, the disk 130, and the actuating members 132, is mechanically coupled to the LP shaft 124 through a power gearbox 134 and is rotatable about the longitudinal axis 101 through the LP shaft 124 across the power gearbox 134. The power gearbox 134 includes a plurality of gears for reducing the rotational speed of the LP shaft 124 to a more efficient fan speed. Thus, the fan 104 is powered by the LP system of the turbomachine 102 , including the LP turbine 118 .

[0036] Still refer to Figure 3 In the exemplary embodiment of the present invention, the disk 130 is covered by a rotatable front hub 136 having an aerodynamic profile to facilitate airflow through the plurality of fan blades 128. In addition, the turbofan 100 includes an annular fan case or outer nacelle 138 that circumferentially surrounds the fan 104 and / or at least a portion of the turbine 102. Therefore, the exemplary turbofan 100 shown may be referred to as a "ducted" turbofan engine. In addition, the nacelle 138 is supported relative to the turbine 102 by a plurality of circumferentially spaced outlet guide vanes 140. A downstream section 142 of the nacelle 138 extends over an outer portion of the turbine 102, thereby defining a bypass airflow passage 144 therebetween.

[0037] Still refer to Figure 3, the hybrid electric propulsion system 50 also includes an electric machine, which for the illustrated embodiment is configured as an electric motor / generator 56. For the illustrated embodiment, the electric motor / generator 56 is located within the turbine 102 of the turbofan engine 100 and is mechanically connected to one of the shafts of the turbofan engine 100. More specifically, for the illustrated embodiment, the electric motor / generator 56 is a first electric motor / generator 56-1 and is located inside the core air flow path 121 and is driven by the first HP turbine 116 through the HP shaft 122. The first electric motor / generator 56-1 is configured to convert the mechanical power of the HP shaft 122 into electricity during certain operations, and is also configured to convert electricity into mechanical power during other operations. Therefore, the first electric motor / generator 56-1 can be powered by the HP system (including the HP turbine 116) of the turbine 102 during certain operations, and can power the HP system during other operations.

[0038] In addition, for Figure 3 In the embodiment shown in the example, the hybrid electric propulsion system 50 also includes a second motor / generator 56-2. The second motor / generator 56-2 is configured to convert the mechanical power of the LP shaft 124 into electric power during certain operations, and is also configured to convert electric power into mechanical power during other operations. Thus, the second motor / generator 56-2 can be powered by the LP system (including the LP turbine 118) of the turbine 102 during certain operations, and can power the LP system during other operations.

[0039] It is worth noting that the motor / generators 56-1, 56-2 can be relatively powerful motor / generators. For example, during certain operations, the motor / generators 56-1, 56-2 can be configured to generate at least about fifty kilowatts of electricity or at least about sixty-five horsepower of mechanical power, and up to, for example, three hundred horsepower of mechanical power. However, in other embodiments, the motor / generators 56-1, 56-2 can generate other amounts of power.

[0040] However, it should be appreciated that in other exemplary embodiments, the motor / generators 56-1, 56-2 may be located at any other suitable location or other location within the turbine 102, and may be powered, for example, in any other suitable manner. For example, in other embodiments, the first motor / generator 56-1 may be mounted coaxially with the HP shaft 122 within the turbine section, or may be offset from the HP shaft 122 and driven by a suitable gear train. Similarly, in other embodiments, the second motor / generator 56-2 may be mounted coaxially with the LP shaft 124 within the compressor section, or may be offset from the LP shaft 124 and driven by a gear train. In addition or alternatively, in still other embodiments, the hybrid electric propulsion system 50 may not include first and second motor / generators 56-1, 56-2, but may include only one of such motor / generators 56-1, 56-2.

[0041] It should also be understood that Figure 3 The exemplary turbofan engine 100 shown in may have other configurations in other exemplary embodiments. For example, in other exemplary embodiments, the fan 104 may not be a variable pitch fan, and in addition, in other exemplary embodiments, the LP shaft 124 may be directly mechanically coupled to the fan 104 (i.e., the turbofan engine 100 may not include a gearbox 134). In addition, it should be understood that in other exemplary embodiments, the first propeller 52 may include any other suitable type of engine. For example, in other embodiments, the turbofan engine 100 may be configured as a turboprop engine or a ductless turbofan engine instead. In addition, in other embodiments, the turbofan engine 100 may be configured as any other suitable combustion engine for driving the motor / generator 56-1, 56-2 instead. For example, in other embodiments, the turbofan engine may be configured as a turboshaft engine, or any other suitable combustion engine (e.g., a ductless, open rotor engine).

[0042] Still refer to Figure 1 and 2, the turbofan engine 100 also includes an engine controller 150, and one or more sensors (although not shown). The engine controller 150 may be a full authority digital engine control system, also known as a FADEC. The engine controller 150 of the turbofan engine 100 may be configured to control the operation of, for example, the actuating member 132, the fuel delivery system (not shown) of the combustion section 114, and the like. In addition, the engine controller 150 may be operably connected to one or more sensors to receive data from the sensors and determine various operating parameters of the turbofan engine 100. For example, the engine controller 150 may determine one or more of the exhaust gas temperature, the rotational speed of the core (i.e., the rotational speed of the HP system), the compressor exhaust temperature, and the like. In addition, referring again to Figure 1 , the engine controller 150 of the turbofan engine 100 is operably connected to the controller 72 of the hybrid electric propulsion system 50. In addition, as will be understood, the controller 72 may also be operably connected to one or more of the first and second gas turbine engines 100A, 100B, the energy storage unit 55, etc. via an appropriate wired or wireless communication system (indicated by dashed lines).

[0043] Special Review Figure 1 and 2 , the electric power system of the hybrid electric propulsion system 50 includes one or more electric machines (e.g., the schematically shown electric machine 56A) mechanically coupled to the first gas turbine engine 100A and one or more electric machines (e.g., the schematically shown electric machine 56B) mechanically coupled to the second gas turbine engine 100B. Although schematically shown as being external to the respective gas turbine engines 100A, 100B, in certain embodiments, the electric motor / generators 56A, 56B may be located within a respective one of the gas turbine engines 100A, 100B (e.g., see Figure 3 ). In addition, although each gas turbine engine 100A, 100B is depicted as being equipped with a single motor / generator, in certain embodiments, each gas turbine engine may be equipped with multiple motor / generators 56A, 56B (e.g., gas turbine engine 100A is equipped with motor / generators 56A-1, 56A-2, and gas turbine engine 100B is equipped with motor / generators 56B-1, 56B-2).

[0044] In addition, as mentioned above Figure 3 Briefly mentioned, Figure 1 and 2In an embodiment of the hybrid electric propulsion system 50, the hybrid electric propulsion system 50 also includes a control system having a controller 72. As will be appreciated, the energy storage unit 55 may be configured to receive power from one or both of the first motor / generator 56A and the second motor / generator 56B under certain operating conditions, and may be further configured to provide stored power to one or both of the first motor / generator 56A and the second motor / generator 56B under certain operating conditions. In addition, the controller 72 may be operably connected to the turbofan engines 100A, 100B, the motor / generators 56A, 56B, and the energy storage unit 55 to, for example, control the operation of the hybrid electric propulsion system 50 and selectively electrically connect components of the hybrid electric propulsion system 50 under various operating conditions.

[0045] Additionally, the controller 72 may communicate with one or more aircraft controllers to receive data indicative of the aircraft's need for power, and may responsively provide power to the aircraft loads 74 from one or more of the motor / generators 56A, 56B and the energy storage unit 55 .

[0046] However, it should be appreciated that in other exemplary embodiments of the present disclosure, any other suitable aircraft 10 may be provided having a hybrid electric propulsion system 50 configured in any other suitable manner. For example, in other embodiments, the turbofan engines 100A, 100B may each be configured as any other suitable combustion engine (e.g., a turboprop, an unducted turbofan, a turboshaft, a turbojet, etc.) and may be mounted in any other suitable location.

[0047] Furthermore, it should be appreciated that in at least some exemplary aspects of the present disclosure, electrical components 224 (eg, including electric machines and control system 230 ) operable with the propulsion system of the present disclosure may be used to determine health information of gas turbine engine 202 .

[0048] Specifically, now refer to Figure 4 , a propulsion system 200 according to exemplary aspects of the present disclosure is provided. In at least some exemplary aspects, Figure 4 The propulsion system 200 can be used in the same manner as described above. Figures 1 to 3 The exemplary propulsion system 50 described is configured in a similar manner.

[0049] For example, Figure 4 The exemplary propulsion system 200 generally includes an aircraft gas turbine engine 202, which can be used with Figure 31. The exemplary turbofan engine 100 of FIG. 1 is configured in a similar manner. For example, as shown in the schematic diagram, the aircraft gas turbine engine 202 includes a fan section 204 having a fan 206 and a turbine 208. The turbine 208 generally includes a compressor section having an LP compressor 210 and an HP compressor 212, a combustion section 214, and a turbine section having an HP turbine 216 and an LP turbine 218. The turbine 208 also includes an HP shaft 220 that can rotate with the HP compressor 212 and the HP turbine 216, and an LP shaft 222 that can rotate with the LP compressor 210 and the LP turbine 218. The LP shaft 222 can further drive the fan 206 of the fan section 204.

[0050] In addition, the exemplary propulsion system 200 shown includes an electric power assembly 224. The electric power assembly 224 includes an electric machine that can rotate with the shaft of the turbine 208. Specifically, the electric machine is a first electric machine 226 that can rotate with the first shaft of the turbine 208 (or more specifically, the HP shaft 220), and the electric power assembly 224 also includes a second electric machine 228 that can rotate with the second shaft of the turbine 208 (or more specifically, the LP shaft 222). Therefore, the first electric machine 226 can be referred to as an HP motor, and the second electric machine 228 can be referred to as an LP motor.

[0051] The power assembly 224 also includes a control system 230 that is in electrical communication with the electric machines, more specifically, the first electric machine 226 and the second electric machine 228. As will be explained in more detail below, the control system 230 is configured to receive data from the first electric machine 226, from the second electric machine 228, or both. The received data may indicate power flowing to or from the first electric machine 226, the second electric machine 228, or both. The control system 230 is also configured to determine health information of the gas turbine engine 202 in response to the received data.

[0052] It will be appreciated from the disclosure herein that health information may be an indication of a fault condition or fault event. For example, health information may be an indication of a bird strike, a compressor stall, a flameout condition, a blade fall condition, etc. In each case, the power flowing to or from the motors 226, 228 may be affected by the condition of the gas turbine engine. For example, in the event of a bird strike, the rotor capable of rotating with the fan (which strikes one or more birds) may therefore exhibit a speed change, which may affect the power flowing to or from the motors 226, 228. Similarly, in the event of a compressor stall, the rotor capable of rotating with the affected rotor may therefore exhibit a speed change, which in turn may affect the power flowing to or from the motors 226, 228. In this manner, it should be appreciated that the received data may indicate the power flowing to or from the first motor 226, the second motor 228, or both may represent a speed change of one or more components capable of rotating with the rotors of the motors 226, 228.

[0053] Still refer to Figure 4 It should be appreciated that the control system 230 includes a converter assembly capable of operating with the motor to regulate power flowing to or from the motor. More specifically, the control system 230 includes a first converter assembly 232 capable of operating with the first motor 226 to regulate power flowing to or from the first motor 226, and also includes a second converter assembly 234 capable of operating with the second motor 228 to regulate power flowing to or from the second motor 228.

[0054] The first converter assembly 232 generally includes a first plurality of switches 236 and a first converter controller 238. The first plurality of switches 236 are operable to convert power from alternating current (AC) power to direct current (DC) power, and vice versa. For example, the first plurality of switches 236 are operable to convert AC power generated by the first motor 226 and provided to the first converter assembly 232 via the wires 240 to a DC power output via the wires 242; operable to convert a DC power input provided to the first converter assembly 232 via the wires 242 to an AC power output provided to the first motor 226 via the wires 240; or both.

[0055] The first converter controller 238 can control the operation of the first plurality of switches 236, for example, to achieve the desired power conversion. The first converter controller 238 can include one or more sensors for sensing data indicating power (e.g., current, voltage, or power) through the lines 240, 242, through the first converter assembly 232, or a combination thereof, for example, to assist in making control decisions. The first converter controller 238 can be used with reference to the following Fig.12 The controller 400 described is configured in a similar manner.

[0056] In this manner, it should be appreciated that in the exemplary embodiment shown, the control system 230 is configured to receive data from the first electric machine 226 via the first converter assembly 232 (and more specifically, via the first converter controller 238 ) that indicates power flowing to or from the first electric machine 226 .

[0057] In at least some exemplary aspects, the data received by the control system 230, and more specifically, the data received by the first converter controller 238, may be data indicating a current of power provided to or generated by the first motor 226, a voltage of power provided to or generated by the first motor 226, a speed of the first motor 226, a torque applied to or applied by the first motor 226, or some combination thereof.

[0058] Still refer to Figure 4 , the exemplary control system 230 shown also includes a system controller 244. The system controller 244 may be an independent controller, may be incorporated into the power assembly 224 or one or more other controllers of the propulsion system 200, or may be formed by multiple separate controllers. The system controller 244 may be similar to the following reference Fig.12 The controller 400 described is configured in a similar manner.

[0059] The first converter controller 238 is configured to provide a signal 246, and the system controller 244 is configured to receive the signal 246, which indicates received data indicating power flowing to or from the first electric machine 226. In the illustrated embodiment, it should be understood that the signal 246 provided from the first converter controller 238 to the system controller 244 is a raw data signal. As will be explained, the system controller 244 is configured to process the signal 246 to generate a processed data signal, and further analyze the processed data signal and determine health information of the gas turbine engine 202.

[0060] It should be understood that the term "raw data signal" as used herein refers to the unaltered electrical output from the motor. The unaltered electrical output may be characterized by a time domain representation and may contain all inherent fluctuations, noise and other characteristics inherent to the operation of the motor.

[0061] As used herein, the term "processed data signal" refers to an electrical output derived from a raw data signal after undergoing an analysis and / or computational procedure to extract, enhance and / or separate specific information or features. The processed data signal may be characterized by a frequency domain representation, such as by a Fourier transform or similar mathematical operation.

[0062] Specifically, the system controller 244 includes a signal processing module 248 configured to receive a raw data signal (signal 246 in the illustrated embodiment) from the first converter assembly 232. The signal processing module 248 may generally receive the raw data signal and process the raw data signal to obtain a processed signal. The processing may include utilizing a transformation or other decryption model to extract a signal that, for example, more easily identifies health data of the gas turbine engine 202.

[0063] It should be understood that the term "module" as used herein refers to a unique functional unit or component within a controller or control system that is designed to perform a specific subset of tasks related to the management and operation of the overall system. A module may be composed of hardware elements, software routines, or a combination of both, and is configured to integrate and cooperate with other modules within a controller or control system to facilitate the desired processing and operating functions. The module may be responsible for a variety of tasks, including but not limited to receiving input signals, executing predetermined algorithms, controlling machine parameters, and generating output signals to affect the behavior or performance of the motor in a coordinated manner.

[0064] Specifically, for the exemplary aspects shown, the signal processing module 248 can process the raw data signal into a processed data signal using a Fourier transform model. In this way, the signal processing module 248 can transform the raw data signal (e.g., a time domain signal) into a processed data signal (e.g., a frequency domain signal) in the form of a Fourier spectrum signal.

[0065] For example, briefly refer to Figure 5 , Figure 5 A graph 250 depicting a raw data signal is provided according to an exemplary aspect of the present disclosure, wherein the gas turbine engine 202 is operating in a nominal manner (eg, not under a fault condition or fault event). Figure 5 The original data signal can be Figure 4 A signal 246 is provided from the first converter controller 238 to the system controller 244 in the embodiment. Figure 5 The signal in the graph 250 of is represented in the time domain (in units of time along the x-axis). Now briefly refer to Figure 6 , Figure 6 A graph 252 is provided, which depicts a processed data signal according to an exemplary aspect of the present disclosure. The processed data signal in graph 252 may be a signal processing module 248 receiving a signal from Figure 5 The output after the signal of 250 is shown in the graph. Figure 6 The signal in the graph 252 of is represented in the frequency domain (in units of frequency along the x-axis). Specifically, Figure 6 The processed data signal is Figure 5 The Fourier spectrum signal corresponding to the original data signal in .

[0066] Back to Figure 4 As briefly described above, control system 230 is configured to determine health information of gas turbine engine 202 in response to the received data. Figure 4 In the exemplary aspect shown, the system controller 244 is configured to determine health information using pattern recognition analysis. Specifically, the system controller 244 includes a pattern recognition module 254 and a fault determination module 256. The pattern recognition module 254 is configured to receive a processed data signal from the signal processing module 248. The pattern recognition module 254 may compare the processed data signal with one or more signal patterns associated with the processed data signal during one or more fault conditions and / or fault events. The pattern recognition module 254 may determine the signal pattern that is most closely associated with the received processed data signal and may provide such information to the fault determination module 256. In response to receiving such information from the pattern recognition module 254, the fault determination module 256 may determine health information of the gas turbine engine 202, which may be that the gas turbine engine 202 is experiencing a fault condition or a fault event.

[0067] In this manner, it should be appreciated that the pattern recognition module 254 may include a library of signal patterns associated with processed data signals during various operations of the gas turbine engine 202, including during one or more fault conditions and / or fault events of the gas turbine engine 202. The signal patterns may include signal patterns of nominal operation of the gas turbine engine 202 during various flight conditions (e.g., taxi, takeoff, climb, cruise, descent), fault conditions (e.g., compressor stall, flameout), and / or fault events (e.g., bird strike, blade shear, shaft shear).

[0068] For example, now refer to Figure 7 and 8 , graphs 258 and 260 provide two additional processed data signals (similar to Figure 6 252 of the processed data signal). However, Figure 7 and 8 The processed data signals in the graphs 258 and 260 are associated with two different fault conditions or fault events of the gas turbine engine 202. As described above, Figure 4 The pattern recognition module 254 in may include a library of exemplary signal patterns associated with processed data signals during various operations of the gas turbine engine. Figure 7 and Figure 8 The processed data signals in the graphs 258 and 260 may be compared with the signal patterns in the signal pattern library to determine possible fault conditions or fault events. As described above, such information may be provided to the fault determination module 256 to determine health information of the gas turbine engine 202.

[0069] from Figure 7 and Figure 8 As can be seen from the graphs 258 and 260, different fault conditions and fault events may have unique signal patterns. Therefore, the control system 230 can not only determine that a fault event or fault condition has occurred, but also determine which fault event or condition has occurred.

[0070] For example, in one exemplary scenario, the gas turbine engine may be operating in a climb mode of operation. One or both of the electric machines 226, 228 may add power to the HP shaft 220 or the LP shaft 222, respectively, or extract power from the HP shaft 220 or the LP shaft 222, respectively, in an expected and commanded manner. The first and second converter controllers 238, 270 may provide a signal 246 to the controller 244, and more specifically, to a signal processing module 248 of the controller 244. The signal 246 may be a raw data signal indicating power flowing to or from the electric machines 226, 228. The signal processing module 248 may process the signal 246 (e.g., convert to a frequency domain representation, e.g., by Fourier transform or similar mathematical operation) and provide the processed signal to the pattern recognition module 254. The pattern recognition module 254 may, for example, compare the received processed data signal to a signal pattern library associated with signal patterns of the processed data signal during various operations of the gas turbine engine to determine that the engine is in the climb mode of operation.

[0071] When operating in the climb mode of operation, the gas turbine engine may ingest one or more birds ("bird strike"), in which case the rotating components of the engine may be affected by the sudden drag caused by contact with the one or more birds. As a result, the motors 226, 228 that rotate with the rotating components may experience a change in the power flowing to / from the motors 226, 228 due to the rotating components being affected by contact with the one or more birds. During this event, the first and second converter controllers 238, 270 may continue to provide signals 246 to the controller 244, and more specifically, to the signal processing module 248 of the controller 244. The signal 246 may be a raw data signal indicating the power flowing to or from the motors 226, 228 during the event. The signal processing module 248 may process the signal 246 and provide the processed signal to the pattern recognition module 254. The pattern recognition module 254 may, for example, compare the received processed data signal to a signal pattern library associated with signal patterns of processed data signals during various operations of the gas turbine engine to determine that the engine has ingested one or more birds. Specifically, the processed data signals received by the pattern recognition module 254 during this event may match or be similar to the pattern of processed data signals associated with bird strikes to indicate that the engine has ingested one or more birds.

[0072] Reference again Figure 4 In response to determining health information (which may be a fault condition or a fault event), the control system 230 may be configured to instruct a response action to be taken. The response action may be a corrective action (e.g., correcting a compressor stall) or a mitigation action (e.g., preventing excessive vibration in a blade shedding event).

[0073] In particular, it should be appreciated that exemplary gas turbine engine 202 also includes an engine controller 262 , which may be a full authority digital engine controller or FADEC, as described above. System controller 244 of control system 230 may provide one or more responsive action signals 264 to engine controller 262 .

[0074] Additionally, or alternatively, it should be understood that Figure 4 The exemplary power assembly 224 of the propulsion system 200 shown in FIG. 2 also includes a power bus assembly 266. The power bus assembly 266 may be a power distribution bus for the gas turbine engine 202 and / or the propulsion system 200. As such, the power bus assembly 266 may be in electrical communication with one or more power sources, one or more power sinks, one or more controllers, and the like. In this manner, the system controller 244 may provide one or more response signals 264 to the power bus assembly 266 to modify the power flowing to or from the first motor 226, for example based on the type of fault condition or fault event determined.

[0075] Still refer to Figure 4 As described above, the power assembly 224 also includes a second motor 228 and a second converter assembly 234. The second motor 228 and the second converter assembly 234 can be configured in a similar manner to the first motor 226 and the first converter assembly 232. For example, the second converter assembly 234 communicates with the second motor 228 and is capable of operating with the second motor 228 to regulate the power flowing to or out of the second motor 228. The second converter assembly 234 generally includes a second plurality of switches 268 and a second converter controller 270. The second converter controller 270 is capable of operating with the system controller 244 to similarly determine health information (e.g., a fault condition or a fault event) of the gas turbine engine 202 in response to data received from the second motor 228. It is noteworthy that the second motor 228 is similarly electrically connected to the power bus assembly 266 through the second converter assembly 234.

[0076] Inclusion of such a configuration may allow propulsion system 200 to determine health information of aircraft gas turbine engine 202. Furthermore, by including system controller 244 separate from engine controller 262 of aircraft gas turbine engine 202, health information may be determined more quickly, and response signal 264 may similarly be provided more quickly.

[0077] For example, as will be appreciated, in certain exemplary aspects, the engine controller 262 may define a first operating frequency, while the system controller 244 may define a second operating frequency. The second operating frequency may be higher than the first operating frequency. More specifically, the engine controller 262 may define a first control decision frequency, while the system controller 244 may define a second control decision frequency. The second control decision frequency may be higher than the first control decision frequency. For example, in certain exemplary embodiments, the system controller 244 may operate at a frequency of at least 250 Hertz (Hz), such as at least 500 Hz, such as at least 750 Hz, such as at least 1 kilohertz (kHz), such as up to 8 kHz. In contrast, the engine controller 262 may operate at a frequency less than the system controller 244, such as less than 250 Hz, such as less than 120 Hz, such as greater than 10 Hz.

[0078] However, it should be understood that in other exemplary embodiments, propulsion system 200 may be configured in any other suitable manner. Fig. 9 , a schematic diagram of a propulsion system 200 according to another exemplary embodiment of the present disclosure is provided. Fig. 9 The exemplary propulsion system 200 may be configured as described above with reference to Figure 4 The depicted exemplary propulsion system 200 is configured in a similar manner, and the same or similar numbers may refer to the same or similar parts.

[0079] For example, Fig. 9 Exemplary propulsion system 200 generally includes an aircraft gas turbine engine 202 having a turbine 208 and an electrical assembly 224 having an electric machine rotatable with a shaft of turbine 208. Electrical assembly 224 also includes a control system 230 having a converter assembly operable with the electric machine.

[0080] More specifically, the motor is a first motor 226 and the converter assembly is a first converter assembly 232. The first converter generally simply includes a first plurality of switches 236 and a first converter controller 238. However, it is noted that for the illustrated embodiment, the first converter controller 238 includes a signal processing module 248', which may be similar to that described above with reference to Figure 4 The exemplary signal processing module 248 described above operates in a similar manner. Fig. 9In an exemplary embodiment of the present invention, the first converter assembly 232 is configured to receive data indicating power flowing to or from the first motor 226 and process a raw data signal associated with the data indicating power flowing to or from the first motor 226 into a processed data signal using a signal processing module 248 of the first converter controller 238. The first converter assembly 232 is configured to provide the processed data signal (signal 246) to a system controller 244 of the control system 230. The system controller 244 may use the processed data signal to communicate with the system controller 244 described above with reference to FIG. Figure 4 The system controller 244 is described in a similar manner to determine health information (eg, fault conditions or fault events) of the gas turbine engine 202 .

[0081] from Fig. 9 As can be further understood from the view of FIG. 2 , the control system 230 also includes a second converter assembly 234 that is operable with the second motor 228 of the power assembly 224. The second converter assembly 234 similarly includes a second plurality of switches 268 and a second converter controller 270. The second converter controller 270 can operate in a similar manner to the first converter controller 238 to provide a processed data signal (e.g., signal 246) to the system controller 244.

[0082] In addition, in other exemplary embodiments, other configurations may also be provided. Fig.10 , a schematic diagram of a propulsion system 200 according to yet another exemplary embodiment of the present disclosure is provided. Fig.10 The exemplary propulsion system 200 may be similar to the one described above with reference to Figure 4 The depicted exemplary propulsion system 200 is configured in a similar manner, and the same or similar numbers may refer to the same or similar parts.

[0083] For example, in Fig.10 In the embodiment of the present invention, the propulsion system 200 generally includes an electric power assembly 224 having a control system 230, and the control system 230 includes a system controller 244. The system controller 244 can be configured to receive a raw data signal (signal 246) from a first converter assembly 232, which can operate with a first motor 226, which can rotate with the shaft of the turbine 208 of the aircraft gas turbine engine 202. The system controller 244 can be used in the same manner as described above with reference to Figure 4 The depicted exemplary system controller 244 is configured in a similar manner.

[0084] However, for Fig.10In the embodiment of the present invention, the system controller 244 includes a detection module 274, wherein the detection module 274 includes a machine learning model 276. In the illustrated embodiment, the machine learning model 276 of the detection module 274 can be configured to receive a raw data signal (signal 246) from, for example, the first converter assembly 232, and can correlate health information (e.g., a fault condition or a fault event) of the gas turbine engine 202 using the machine learning model 276. Such information can be provided to the fault determination module 256.

[0085] Inclusion of such a configuration may reduce the amount of processing required by the system controller 244 .

[0086] It should be understood that the term "machine learning model" as used herein refers to a computational model developed by applying a machine learning algorithm to analyze and interpret data signals from a motor. The machine learning model can be designed to autonomously adjust and improve its analytical capabilities by being exposed to more data over time. Using statistical and mathematical techniques, the machine learning model can process the data signals to extract important patterns and correlations, which can then be used to determine health information for the gas turbine engine. This may involve identifying anomalies, predicting or identifying fault conditions or fault events based on patterns observed in the data signals, etc. The machine learning model can be trained using supervised learning, unsupervised learning, semi-supervised learning, reinforcement learning, transfer learning, ensemble learning, deep learning, or a combination thereof.

[0087] Reference now Fig.11 , a flow chart of a method 300 for operating a propulsion system according to an exemplary aspect of the present disclosure is provided. The method 300 may be similar to the method described above with reference to Figures 1 to 10 One or more exemplary embodiments are described to operate together.

[0088] for Fig.11 In an exemplary aspect of the invention, method 300 includes receiving data from an electric machine at (302), the data indicating power flowing to or from the electric machine. The electric machine is capable of rotating with a shaft of a turbine of an aircraft gas turbine engine. In the exemplary aspect shown, receiving data from the electric machine at (302) includes receiving data from the electric machine having a converter assembly capable of operating with the electric machine at (304).

[0089] Still reference Fig.11 , method 300 also includes providing a signal from the converter assembly to the controller at ( 308 ) indicating power flowing to or from the electric machine.

[0090] In one exemplary aspect, providing a signal from the converter assembly to the controller at (308) indicating power flowing to or from the motor includes processing data from the motor with the converter assembly at (310); and providing the signal as a processed data signal at (312).

[0091] In an alternative exemplary aspect, providing a signal from the converter assembly to the controller indicating power flowing to or from the electric machine at (308) includes providing a raw data signal from the converter assembly to the controller at (314). For such exemplary aspects, method 300 also includes processing the raw data signal from the converter assembly with the controller to generate a processed data signal at (316).

[0092] Still refer to Fig.11 , the method 300 also includes determining health information of the gas turbine engine in response to the received data at (318). Specifically, for the exemplary aspect shown, determining health information of the gas turbine engine in response to the received data at (318) includes analyzing a processed data signal derived from the received data using pattern recognition analysis at (320). More specifically, for the exemplary aspect shown, analyzing the processed data signal derived from the received data using pattern recognition analysis at (320) includes comparing the processed data signal to a library of signal patterns associated with processed data signals during various operations of the gas turbine engine at (322).

[0093] For example, in one exemplary aspect, method 300 may determine health information of the gas turbine engine during a fault condition (e.g., during a bird strike). By such an exemplary aspect, the signal provided at (308) may indicate power flowing to or from the motor during the bird strike. As will be appreciated, rotating components of the gas turbine engine capable of rotating with the motor may be affected by contact with one or more birds, which may affect the signal. Method 300 may, for example, process the signal at (310) or (316) and determine at (318) that the gas turbine engine has experienced a bird strike by analyzing the processed signal at (320) (e.g., by comparing a processed data signal from the motor during a bird strike to a library of signal patterns associated with processed data signals during various operating conditions of the gas turbine engine).

[0094] Reference now Fig.12 , a controller 400 according to an exemplary aspect of the present disclosure is provided. One or more of the exemplary controllers described above may be configured in a similar manner.

[0095] In one or more exemplary embodiments, Figure 2 The controller 400 shown in FIG. 4 may be a stand-alone controller 400 for the propulsion system of the present disclosure, or alternatively, may be integrated into one or more of a controller of a gas turbine engine, a controller of an aircraft including the propulsion system, or the like.

[0096] With specific reference to the operation of the controller 400, in at least some embodiments, the controller 400 may include one or more computing devices 402. The computing device 402 may include one or more processors 402A and one or more storage devices 402B. The one or more processors 402A may include any suitable processing device, such as a microprocessor, a microcontroller, an integrated circuit, a logic device, and / or other suitable processing device. The one or more memory devices 402B may include one or more computer-readable media, including but not limited to non-transitory computer-readable media, RAM, ROM, hard disk drives, flash drives, and / or other memory devices.

[0097] One or more memory devices 402B may store information accessible by one or more processors 402A, including computer-readable instructions 402C executable by one or more processors 402A. Instructions 402C may be any set of instructions that, when executed by one or more processors 402A, cause one or more processors 402A to perform operations. In some embodiments, instructions 402C may be executed by one or more processors 402A to cause one or more processors 402A to perform operations, such as any operations and functions configured by controller 400 and / or computing device 402, operations of the propulsion system disclosed herein, and / or any other operations or functions of one or more computing devices 402. Instructions 402C may be software written in any suitable programming language or may be implemented in hardware. In addition and / or alternatively, instructions 402C may be executed in logical and / or virtual independent threads on one or more processors 402A. One or more memory devices 402B may also store data 402D accessible by one or more processors 402A. For example, data 402D may include data indicative of power flow, data indicative of engine / aircraft operating conditions, and / or any other data and / or information described herein.

[0098] The computing device 402 may also include a network interface 402E for communicating, for example, with other components of the propulsion system. For example, in the illustrated embodiment, as described above, the propulsion system (including a gas turbine engine, an electric motor, etc.) includes one or more sensors for sensing data indicating one or more parameters of the gas turbine engine, the electric motor, etc. The controller 400 may be operably coupled to the one or more sensors via, for example, a network interface, such that the controller 400 may receive data indicating various operating parameters sensed by the one or more sensors during operation.

[0099] Network interface 402E may include any suitable components for interfacing with one or more networks, including, for example, a transmitter, a receiver, a port, a controller, an antenna, and / or other suitable components.

[0100] The technology discussed herein relates to computer-based systems and actions taken by computer-based systems and information sent to and from computer-based systems. Those of ordinary skill in the art will recognize that the inherent flexibility of computer-based systems allows for various possible configurations, combinations, and division of tasks and functions between and among components. For example, the processes discussed herein can be implemented using a single computing device or multiple computing devices working in combination. Databases, memories, instructions, and applications can be implemented on a single system or distributed on multiple systems. Distributed components can operate sequentially or in parallel.

[0101] It should be understood that although the exemplary embodiments discussed above relate to an aerial vehicle, in other exemplary embodiments of the present disclosure, a propulsion system may be provided for use with any other suitable vehicle, such as a land-based vehicle (in which case the propulsion system may include, for example, a combustion engine / automobile engine).

[0102] A control system according to one or more exemplary aspects of the present disclosure may allow high bandwidth feedback from a hybrid power architecture to determine health information, such as engine faults and / or significant changes in engine health, and may also allow corrective actions to be indicated and initiated via an electric machine or by a primary engine control (e.g., FADEC). Specifically, determining health information according to exemplary aspects of the present disclosure may allow events to be determined more expediently, and therefore allow more expedient actions to be taken to correct or mitigate the event.

[0103] Further aspects are provided by the subject matter of the following clauses:

[0104] A propulsion system comprises: a gas turbine engine having a turbine, the turbine comprising a compressor, a turbine and a shaft capable of rotating together with the turbine; and an electric power component, the electric power component comprising: an electric motor capable of rotating together with the shaft; and a control system, the control system being electrically connected to the electric motor, the control system being configured to receive data indicating electric power flowing to or from the electric motor from the electric motor, and to determine health information of the gas turbine engine in response to the received data.

[0105] A propulsion system as described in any preceding clause, wherein the control system includes a converter assembly operable with the electric machine to regulate the flow of electric power to or from the electric machine.

[0106] A propulsion system as described in any preceding clause, wherein the control system is configured to receive the data using the converter assembly, wherein the control system further includes a controller configured to receive a signal from the converter assembly indicative of the power flowing to or from the electric machine.

[0107] A propulsion system as described in any preceding clause, wherein the controller is further configured to process the signal indicative of the power flowing to or from the electric machine.

[0108] A propulsion system as described in any preceding clause, wherein the converter assembly is further configured to process the data indicative of the power flowing to or from the electric machine, and wherein the signal indicative of the power flowing to or from the electric machine is a processed data signal.

[0109] A propulsion system as described in any preceding clause, wherein the control system is configured to determine the health information of the gas turbine engine using pattern recognition analysis.

[0110] A propulsion system according to any of the preceding clauses, wherein the control system is configured to determine the health information of the gas turbine engine by comparing a processed data signal derived from a raw data signal to a library of signal patterns associated with the processed data signal during various operations of the gas turbine engine.

[0111] A propulsion system as described in any preceding clause, wherein the processed data signal is derived from the raw data signal using a Fourier frequency transform.

[0112] A propulsion system as described in any preceding clause, wherein the control system includes a controller having a detection module, the detection module configured to determine the health information of the gas turbine engine using a machine learning model.

[0113] A propulsion system as described in any preceding clause, wherein the control system is further configured to indicate a responsive action to be taken in response to determining that the health information of the gas turbine engine is a fault event or fault condition.

[0114] A propulsion system according to any of the preceding clauses, wherein the compressor is a low-pressure compressor, wherein the turbine is a low-pressure turbine, wherein the shaft is a low-pressure shaft, wherein the turbine further includes a high-pressure compressor, a high-pressure turbine and a high-pressure shaft capable of rotating together with the high-pressure turbine, wherein the motor is a low-pressure motor, and wherein the power assembly further includes a high-pressure motor, wherein the control system is further electrically connected to the high-pressure motor, and the control system is configured to receive data indicating power flowing to or from the high-pressure motor, and determine health information of the gas turbine engine in response to the data received from the high-pressure motor.

[0115] A propulsion system as described in any preceding clause, wherein the control system operates at a frequency of at least 250 Hz.

[0116] A propulsion system as claimed in any preceding clause, further comprising an engine controller defining an operating frequency in communication with the control system, wherein the control system comprises a controller defining an operating frequency higher than the operating frequency of the engine controller.

[0117] A method of operating a propulsion system, the method comprising: receiving data indicative of power flowing to or from an electric machine, the electric machine being rotatable with a shaft of a turbine of a gas turbine engine; and determining health information of the gas turbine engine in response to the received data.

[0118] A method according to any preceding clause, wherein receiving data from the motor comprises receiving data from the motor having a converter assembly capable of operating with the motor, and wherein the method further comprises: providing a signal from the converter assembly to a controller indicative of the power flowing to or from the motor.

[0119] A method according to any preceding clause, wherein providing the signal from the converter component to the controller indicating the power flowing to or from the motor comprises: processing the data from the motor using the converter component; and providing the signal as a processed data signal.

[0120] A method according to any preceding clause, wherein providing the signal from the converter assembly to the controller indicating the power flowing to or from the motor includes providing a raw data signal from the converter assembly to the controller, and wherein the method further includes: processing the raw data signal from the converter assembly using the controller to generate a processed data signal.

[0121] A method as in any preceding clause, wherein determining the health information of the gas turbine engine in response to received data comprises analyzing a processed data signal derived from the received data using pattern recognition analysis.

[0122] A method according to any preceding clause, wherein analyzing the processed data signal derived from the received data using the pattern recognition analysis comprises comparing the processed data signal to a library of signal patterns associated with processed data signals during various operations of the gas turbine engine.

[0123] A combustion engine assembly includes: a combustion engine having a driven shaft; and an electric assembly, the electric assembly including: an electric motor capable of rotating together with the driven shaft; and a control system, the control system being electrically connected to the electric motor, the control system being configured to receive data indicating electric power flowing to or from the electric motor, and to determine health information of the combustion engine in response to the received data.

[0124] This written description uses examples to disclose the present disclosure, including the best mode, and also to enable those skilled in the art to practice the present disclosure, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the present disclosure is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to fall within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements that do not differ substantially from the literal language of the claims.

Claims

1. A propulsion system, characterized in that: include: a gas turbine engine having a turbine including a compressor, a turbine, and a shaft rotatable with the turbine; and A power component, the power component comprising: a motor, the motor being capable of rotating together with the shaft; and A control system is in electrical communication with the electric machine, the control system being configured to receive data from the electric machine indicative of power flowing to or from the electric machine and to determine health information of the gas turbine engine in response to the received data.

2. The propulsion system according to claim 1, characterized in that: The control system includes a converter assembly operable with the electric machine to regulate the electric power flowing to or from the electric machine.

3. The propulsion system according to claim 2, characterized in that: The control system is configured to receive the data using the converter assembly, wherein the control system further comprises a controller configured to receive a signal from the converter assembly indicative of the power flowing to or from the electric machine.

4. The propulsion system according to claim 3, characterized in that: Wherein the controller is further configured to process the signal indicative of the power flowing to or from the motor.

5. The propulsion system according to claim 3, characterized in that: Wherein the converter assembly is further configured to process the data indicative of the power flowing to or from the motor, and wherein the signal indicative of the power flowing to or from the motor is a processed data signal.

6. The propulsion system according to claim 1, characterized in that Wherein the control system is configured to determine the health information of the gas turbine engine using pattern recognition analysis.

7. The propulsion system according to claim 6, characterized in that Wherein the control system is configured to determine the health information of the gas turbine engine by comparing a processed data signal derived from a raw data signal to a library of signal patterns associated with the processed data signal during various operations of the gas turbine engine.

8. The propulsion system according to claim 7, characterized in that Wherein the processed data signal is derived from the raw data signal using a Fourier frequency transform.

9. The propulsion system according to claim 1, characterized in that The control system includes a controller having a detection module configured to determine the health information of the gas turbine engine using a machine learning model.

10. The propulsion system according to claim 1, characterized in that Wherein the control system is further configured to instruct a response action to be taken in response to determining that the health information of the gas turbine engine is a fault event or a fault condition.

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