Aircraft engine hybrid electric thermal management system

Abstract

The thermal management system defines a thermal management system flow path to provide a fluid flow to the electric machine and a power electronics component electrically connected to the electric machine. The thermal management system includes a first heat exchanger thermally connected to the thermal management system flow path and the electric machine, and a second heat exchanger thermally connected to the thermal management system flow path downstream of the first heat exchanger. The second heat exchanger is thermally connected to the power electronic component.

Description

Technical Field

[0001] The present disclosure relates to an aviation power system including a thermal management system for one or more electric machines that may be incorporated into an aviation gas turbine engine. Background Art

[0002] Conventional commercial aircraft typically include a fuselage, a pair of wings, and a propulsion system that provides thrust. The propulsion system typically includes at least two aircraft engines, such as turbofan jet engines. Each turbofan jet engine is typically mounted to a respective one of the aircraft's wings, such as in a suspended position below the wing that is separate from the wing and fuselage.

[0003] Hybrid-electric propulsion systems are being developed to improve the efficiency of conventional commercial aircraft. Some hybrid-electric propulsion systems include one or more electric motors, each mechanically coupled to a rotating component of one of the aircraft's engines. The electric motors may each have associated power electronics components electrically connected thereto, including a power converter and a power distribution or management unit. BRIEF DESCRIPTION OF THE DRAWINGS

[0004] A full 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 Schematic top views of aircraft having hybrid electric propulsion systems according to various exemplary embodiments of the present disclosure are provided.

[0006] Figure 2 Provided Figure 1 A schematic cross-sectional view of one of the hybrid electric propulsion systems of an aircraft.

[0007] Figure 3 is a simplified schematic diagram of a thermal management system for an aviation power system according to an exemplary aspect of the present disclosure.

[0008] Figure 4 is a simplified schematic diagram of a thermal management system for an aviation power system according to another exemplary aspect of the present disclosure.

[0009] Figure 5 is a simplified schematic diagram of a thermal management system for an aviation power system according to another exemplary aspect of the present disclosure.

[0010] Figure 6 is a simplified schematic diagram of a thermal management system for an aviation power system according to another exemplary aspect of the present disclosure.

[0011] Figure 7is a simplified schematic diagram of a thermal management system for an aviation power system according to another exemplary aspect of the present disclosure.

[0012] Figure 8 A method for thermal management of an aviation power system according to exemplary aspects of the present disclosure is described.

[0013] Figure 9 An example computing system according to example embodiments of the present disclosure is provided. DETAILED DESCRIPTION

[0014] 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 references to refer to features in the drawings. Like or similar reference numerals have been used in the drawings and the description to refer to like or similar parts of the present disclosure.

[0015] The word "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. Additionally, unless expressly stated otherwise, all embodiments described herein should be considered exemplary.

[0016] The singular forms "a," "an," and "the" include plural referents unless the context clearly dictates otherwise.

[0017] In a context such as “at least one of A, B, and C,” the term “at least one of” means only A, only B, only C, or any combination of A, B, and C.

[0018] 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.

[0019] 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.

[0020] The terms "upstream" and "downstream" refer to relative directions relative to the flow of a path. For example, with respect to fluid flow, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction toward which the fluid is flowing. However, as used herein, the terms "upstream" and "downstream" may also refer to the flow of an electric current.

[0021] Within the confined space of a gas turbine engine, the integration of electric machines having different power ratings (e.g., a low-pressure (LP) electric machine that can rotate with the engine's LP system having a higher power rating than a high-pressure (HP) electric machine that can rotate with the engine's HP system) can present several challenges. For example, by having separate power ratings, thermal management becomes more complex because each of the various components associated with the LP and HP electric machines has more tailored thermal requirements, including power electronics components electrically connected to the LP and HP electric machines that convert and distribute power to various components of the gas turbine engine or aircraft.

[0022] To address the aforementioned issues, the present disclosure provides a thermal management system tailored to meet the thermal requirements of the LP and HP electric machines and the power distribution components associated with them. The present disclosure provides dedicated or separate cooling circuits for hybrid electric systems. Each cooling circuit provides thermal management for the LP and HP electric machines, as well as the power converters and distribution electronics associated with them, to meet the aforementioned unique thermal requirements. In an exemplary embodiment, these cooling circuits are separate from other engine cooling circuits and include the electric machines and the power electronics components electrically connected to the electric machines.

[0023] Referring now to the drawings, in which like numerals represent like elements throughout, Figure 1 A schematic top view of an exemplary aircraft 100 is provided, which may incorporate one or more aspects of the present disclosure. Figure 1 As shown, for reference, the aircraft 100 defines a longitudinal direction L1 and a transverse direction L2. The transverse direction L2 is perpendicular to the longitudinal direction L1. The aircraft 100 also defines a longitudinal centerline 114 extending therethrough along the longitudinal direction L1. The aircraft 100 extends, for example, along the longitudinal direction L1 between a front end 116 and a rear end 118.

[0024] As shown, aircraft 100 includes a fuselage 112 that extends longitudinally from a front end 116 of aircraft 100 to a rear end 118 of aircraft 100. Aircraft 100 also includes a tail 119 at rear end 118 of aircraft 100. Furthermore, aircraft 100 includes a wing assembly comprising a first wing 120 (e.g., a port-side wing) and a second wing 122 (e.g., a starboard-side wing). The first and second wings 120, 122 each extend laterally outward relative to longitudinal centerline 114. The first wing 120 and a portion of the fuselage 112 together define a first side 124 of aircraft 100, and the second wing 122 and another portion of the fuselage 112 together define a second side 126 of aircraft 100. For the illustrated embodiment, the first side 124 of aircraft 100 is configured as the port side of aircraft 100, and the second side 126 of aircraft 100 is configured as the starboard side of aircraft 100.

[0025] Aircraft 100 includes various control surfaces. For this embodiment, each wing 120, 122 includes one or more leading edge flaps 128 and one or more trailing edge flaps 130. Aircraft 100 also includes, or more specifically, the tail 119 of aircraft 100 includes a vertical stabilizer 132 and a pair of horizontal stabilizers 134, the vertical stabilizer 132 having rudder flaps (not shown) for yaw control, and the pair of horizontal stabilizers 134 each having elevator flaps 136 for pitch control. The fuselage 112 also includes an outer surface or skin 138. It should be understood that in other exemplary embodiments of the present disclosure, aircraft 100 can additionally or alternatively include any other suitable configuration. For example, in other embodiments, aircraft 100 can include any other control surface configuration.

[0026] Figure 1 The exemplary aircraft 100 also includes a hybrid electric propulsion system 150. For this embodiment, the hybrid electric propulsion system 150 has a first propeller 200A and a second propeller 200B, both of which are operable to generate thrust. The first propeller 200A is mounted to the first wing 120, and the second propeller 200B is mounted to the second wing 122. Moreover, for the illustrated embodiment, the first propeller 200A and the second propeller 200B are each configured in an underwing mounting configuration. However, in other exemplary embodiments, one or both of the first propeller 200A and the second propeller 200B can be mounted in any other suitable location in other exemplary embodiments.

[0027] The first propulsion unit 200A includes a gas turbine engine 210A and one or more electric motors, such as an electric motor 300A mechanically coupled to the gas turbine engine 210A. The electric motor 300A can be a generator, an electric motor, or a combination generator / motor. For this example embodiment, the electric motor 300A is a combination generator / motor. In this manner, when operating as a generator, the electric motor 300A can generate electrical power when driven by the gas turbine engine 210A. When operating as an electric motor, the electric motor 300A can drive or motor the gas turbine engine 210A.

[0028] Similarly, the second propulsion unit 200B includes a gas turbine engine 210B and one or more motors, such as a motor 300B mechanically coupled to the gas turbine engine 210B. The motor 300B can be a generator, an electric motor, or a combination generator / motor. For this example embodiment, the motor 300B is a combination generator / motor. In this way, when operating as a generator, the motor 300B can generate electrical power when driven by the gas turbine engine 210B. When operating as a motor, the motor 300B can drive or start the spool of the gas turbine engine 210B. The motor 300B can be configured as the motor 300A described herein and can operate in a manner similar to the motor 300A described herein.

[0029] The hybrid electric propulsion system 150 also includes an electrical energy storage unit 180 that can be electrically connected to the motors 300A, 300B and, in some embodiments, can be electrically connected to other electrical loads. In some exemplary embodiments, the electrical energy storage unit 180 can include one or more batteries. Additionally or alternatively, the electrical energy storage unit 180 can include one or more supercapacitor arrays, one or more ultrasonic capacitor arrays, or both. For the hybrid electric propulsion system 150 described herein, the electrical energy storage unit 180 is configured to store relatively large amounts of electrical power. For example, in certain exemplary embodiments, the electrical energy storage unit 180 can be configured to store at least approximately fifty kilowatt-hours of electrical power, such as approximately seventy-five kilowatt-hours of electrical power, and up to approximately one thousand kilowatt-hours of electrical power.

[0030] The hybrid electric propulsion system 150 also includes a power management system having a controller 182 and a power bus 184 . The electric machines 300A, 300B, the electrical energy storage unit 180 , and the controller 182 are each electrically connected to one another via one or more wires 186 of the power bus 184 .

[0031] The controller 182 is configured to control the power electronics to distribute electrical power among the various components of the hybrid electric propulsion system 150. For example, the controller 182 can control the power electronics of the power bus 184 to provide electrical power to various components, such as the motors 300A, 300B, or to draw electrical power from various components, such as the motors 300A, 300B, to operate the hybrid electric propulsion system 150 between various operating modes and perform various functions. As shown schematically, wires 186 of the power bus 184 extend through the controller 182.

[0032] The controller 182 may form part of a computing system 190 of the aircraft 100. The computing system 190 of the aircraft 100 may include one or more processors and one or more memory devices contained in one or more computing devices. Figure 1 As shown, computing system 190 includes controller 182 and other computing devices, such as computing device 192. Computing system 190 may also include other computing devices, such as an engine controller (not shown). The computing devices of computing system 190 may be communicatively coupled to each other via a communication network. For example, computing device 192 is located in the cockpit of aircraft 100 and is communicatively coupled to controller 182 of hybrid electric propulsion system 150 via a communication link 194 of the communication network. Communication link 194 may include one or more wired or wireless communication links.

[0033] For this embodiment, the computing device 192 is configured to receive and process input and / or other information, such as from a pilot or other crew member. In this manner, as an example, one or more processors of the computing device 192 may receive input indicating a command to change the thrust output of the first and / or second thrusters 200A, 200B, and in response to the input, may cause the controller 182 to control the electrical power drawn from or delivered to one or both of the motors 300A, 300B to ultimately change the thrust output of one or both of the thrusters 200A, 200B.

[0034] The controller 182 and other computing devices of the computing system 190 of the aircraft 100 may be configured as described below with reference to Figure 9 The exemplary computing devices of the described computing system 900 are configured in substantially the same manner.

[0035] It should be appreciated that the electric machines 300A, 300B, the electrical energy storage unit 180 , and the power management system (having the controller 182 and the power bus 184 ) may more specifically be configured as part of an aviation power system integrated with the gas turbine engine of the hybrid-electric propulsion system 150 .

[0036] Figure 2 Provided Figure 1 Schematic diagram of a first propeller 200A of the hybrid electric propulsion system 150 of the aircraft 100. Although the first propeller 200A is shown, it should be understood that the second propeller 200B can be used in conjunction with the first propeller 200A. Figure 2 The first thruster 200A shown is configured in the same or similar manner. Figure 2 The exemplary gas turbine engine 210A is configured as a single unducted rotor engine 210A having a single stage of unducted rotor blades. In this manner, the rotor assembly may be referred to herein as an "unducted fan," or the entire gas turbine engine 210A may be referred to as an "unducted turbofan engine." Additionally, Figure 2 The gas turbine engine 210A includes a third flow path extending from the compressor section to the rotor assembly above the turbine, as will be explained in greater detail below.

[0037] For reference, the gas turbine engine 210A defines an axial direction A, a radial direction R, and a circumferential direction C. Furthermore, the gas turbine engine 210A defines an axial centerline or longitudinal axis 214 extending along the axial direction A. Generally, the axial direction A extends parallel to the longitudinal axis 214, the radial direction R extends outwardly from and inwardly to the longitudinal axis 214 in a direction orthogonal to the axial direction A, and the circumferential direction extends three hundred and sixty degrees (360°) about the longitudinal axis 214. The gas turbine engine 210A extends, for example, along the axial direction A between a forward end 211 and an aft end 213.

[0038] The gas turbine engine 210A includes a turbine 230 and a rotor assembly 212 (also referred to as a fan section) positioned upstream thereof. Generally, the turbine 230 includes a compressor section, a combustion section, a turbine section, and an exhaust section in a series flow order. In particular, as Figure 2 As shown, the turbine 230 includes a core cover 248 that defines an annular core inlet 250. The core cover 248 also at least partially surrounds a low-speed or low-pressure system and a high-speed or high-pressure system. For example, the core cover 248 shown at least partially surrounds and supports a supercharger or low-speed or low-pressure compressor 244 for pressurizing air entering the turbine 230 through the core inlet 250. The high-speed or high-pressure multi-stage axial flow compressor (referred to herein as the high-pressure compressor 234) receives the compressed air from the low-pressure compressor 244 and further increases the pressure of the air. The pressurized air flows downstream to the combustor 240 of the combustion section, where fuel is injected into the pressurized air flow and ignited to increase the temperature and energy level of the pressurized air.

[0039] It should be understood that, as used herein, the terms "high / low speed" and "high / low pressure" are interchangeable for high-pressure / high-speed systems and low-pressure / low-speed systems. Furthermore, it should be understood that the terms "high" and "low" are used in the same context to distinguish between the two systems and are not meant to imply any absolute speed and / or pressure values.

[0040] The high-energy combustion products flow downstream from the combustor 240 to a high-pressure turbine 236. The high-pressure turbine 236 drives the high-pressure compressor 234 via a high-pressure shaft 238. In this regard, the high-pressure turbine 236 is drivingly coupled to the high-pressure compressor 234. The high-pressure compressor 234, the high-pressure turbine 236, and the high-pressure shaft 238 may collectively be referred to as a high-speed spool 253 of the gas turbine engine 210A. The high-energy combustion products then flow to a low-pressure turbine 242. The low-pressure turbine 242 drives the low-pressure compressor 244 and components of the rotor assembly 212 via a low-pressure shaft 246. In this regard, the low-pressure turbine 242 is drivingly coupled to the low-pressure compressor 244 and components of the rotor assembly 212. The low-pressure compressor 244, the low-pressure turbine 242, and the low-pressure shaft 246 may collectively be referred to as a low-speed spool 255 of the gas turbine engine 210A. In this exemplary embodiment, the low-pressure shaft 246 is coaxial with the high-pressure shaft 238. After driving each of the turbines 236 , 242 , the products of combustion exit the turbine 230 through a turbine exhaust nozzle 252 .

[0041] Thus, the turbine 230 defines a working gas flow path or core duct 241 extending between a core inlet 250 and a turbine exhaust nozzle 252. The core duct 241 is an annular duct positioned generally inboard of the core shroud 248 in the radial direction R. The core duct 241 (e.g., the working gas flow path through the turbine 230) may be referred to as a secondary flow.

[0042] The rotor assembly 212 includes a fan 215, which in this example embodiment is the main fan. Figure 2 In the illustrated embodiment, fan 215 is an open rotor or unducted fan. In this manner, gas turbine engine 210A may be referred to as an open rotor engine. However, it should be understood that embodiments of the present disclosure may also be applied to other types of engines, such as, by way of non-limiting example, a ducted gas turbine engine.

[0043] As shown, the fan 215 includes an array of airfoils, and more specifically, an array of fan blades 216, arranged about the longitudinal axis 214 of the gas turbine engine 210A. Figure 2 Only one is shown). The fan blades 216 are rotatable, for example about the longitudinal axis 214. As described above, the fan 215 is drivingly coupled to the low-pressure turbine 242 via the low-pressure shaft 246. Figure 2 In the illustrated embodiment, the fan 215 is coupled to the low-pressure shaft 246 via a power or reduction gearbox 256 (eg, in an indirect drive or gear drive configuration).

[0044] In addition, the array of fan blades 216 can be arranged at equal intervals about the longitudinal axis 214. Each fan blade 216 has a proximal end or root 222 and a distal end or tip 224 relative to the longitudinal axis 214, and a span defined therebetween. Each fan blade 216 defines a pitch change or central blade axis 260. For this embodiment, each fan blade 216 of the rotor assembly 212 can rotate about its central blade axis 260, for example, in unison with each other. A pitch change mechanism 258 in the form of one or more actuators is provided to facilitate such rotation and, therefore, can be used to change the pitch of the fan blades 216 about their respective central blade axes 260.

[0045] An array of airfoils positioned rearward of fan blades 216 and also disposed about longitudinal axis 214, and more specifically includes a fan guide vane assembly 218 including fan guide vanes 220 disposed about longitudinal axis 214 ( Figure 2 For this embodiment, the fan guide vanes 220 are non-rotatable about the longitudinal axis 214. Each fan guide vane 220 has a proximal end or root 226 and a distal end or tip 228 relative to the longitudinal axis 214, and a span defined therebetween. Figure 2 As shown, the fan guide vanes 220 may be unshielded or, alternatively, may be shielded, such as by an annular shroud spaced outwardly in the radial direction R from the tips of the fan guide vanes 220 or attached to the fan guide vanes 220 .

[0046] Each fan guide vane 220 defines a central guide vane axis 264. For this embodiment, each fan guide vane 220 of the fan guide vane assembly 218 is rotatable about its respective central guide vane axis 264, e.g., in unison with one another. One or more pitch change mechanisms 262 in the form of one or more actuators are provided to facilitate such rotation and, thus, can be used to change the pitch of the fan guide vanes 220 about their respective central guide vane axis 264. However, in other embodiments, each fan guide vane 220 can be fixed or unable to pitch about its central guide vane axis 264. The fan guide vanes 220 are mounted to the fan housing 232.

[0047] like Figure 2As shown, in addition to the unducted fan 215, a ducted fan 284 is included behind the fan 215, so that the gas turbine engine 210A includes a ducted fan and an unducted fan, both of which are used to generate thrust by the movement of air without a passage through at least a portion of the turbine 230 (for example, for the embodiment shown, without a passage through the high-pressure compressor 234 and the combustion section). The ducted fan 284 can rotate about the same axis as the fan blades 216 (for example, the longitudinal axis 214). For the embodiment shown, the ducted fan 284 is driven by the low-pressure turbine 242 (for example, coupled to the low-pressure shaft 246). In the embodiment shown, as described above, the fan 215 can be referred to as the main fan, and the ducted fan 284 can be referred to as the auxiliary fan. It should be understood that these terms "main" and "auxiliary" are terms of convenience and do not imply any particular importance, authority, etc.

[0048] The ducted fan 284 includes a plurality of fan blades arranged in a single stage (in Figure 2 214 ), so that ducted fan 284 can be referred to as a single-stage fan. The fan blades of ducted fan 284 can be arranged at equal intervals about longitudinal axis 214. Each blade of ducted fan 284 has a proximal end or root and a distal end or tip, and a span defined therebetween.

[0049] The fan shroud 232 annularly surrounds at least a portion of the core shroud 248 and is generally positioned outboard of at least a portion of the core shroud 248 along the radial direction R. Specifically, a downstream section of the fan shroud 232 extends over a forward portion of the core shroud 248 to define a fan duct flow path, or simply, a fan duct 272. According to this embodiment, the fan flow path or fan duct 272 may be understood as forming at least a portion of the tertiary flow of the gas turbine engine 210A.

[0050] Incoming air may enter the fan duct 272 through the fan duct inlet 276 and may exit through the fan exhaust nozzle 278 to generate propulsive thrust. The fan duct 272 is an annular duct positioned generally outboard of the core duct 241 in the radial direction R. The fan shroud 232 and the core shroud 248 are connected together and are supported by a plurality of substantially radially extending, circumferentially spaced stationary struts 274 ( Figure 2The fan duct 272 and the core duct 241 may be supported by the fan duct 232 and the core duct 241 (only one shown in FIG). The stationary struts 274 may each have an aerodynamic profile to guide the air flow therethrough. In addition to the stationary struts 274, other struts may also be used to connect and support the fan shroud 232, the core shroud 248, or both. In many embodiments, the fan duct 272 and the core duct 241 may at least partially extend together (typically axially) on opposite sides (e.g., opposite radial sides) of the core shroud 248. For example, the fan duct 272 and the core duct 241 may each extend directly from the leading edge 279 of the core shroud 248 and may partially extend together approximately axially on the opposite radial sides of the core shroud 248.

[0051] Gas turbine engine 210A further defines or includes an inlet duct 280. Inlet duct 280 extends between an engine inlet 282 and core inlet 250 and fan duct inlet 276. Engine inlet 282 is generally defined at the forward end of fan shroud 232 and positioned between fan 215 and fan guide vane assembly 218 in axial direction A. Inlet duct 280 is an annular duct positioned inboard of fan shroud 232 in radial direction R. Air flowing downstream along inlet duct 280 is divided (but not necessarily evenly) into core duct 241 and fan duct 272 by a fan duct splitter or leading edge 279 of core shroud 248. In the illustrated embodiment, inlet duct 280 is wider than core duct 241 in radial direction R. Inlet duct 280 is also wider than fan duct 272 in radial direction R.

[0052] It is noted that for the embodiment shown, the gas turbine engine 210A includes one or more features to increase the third flow thrust Fn 3S 284 ). Specifically, gas turbine engine 210A includes an array of inlet guide vanes 286 positioned in inlet duct 280, upstream of ducted fan 284 and downstream of core inlet 250. The array of inlet guide vanes 286 is arranged about longitudinal axis 214. For this embodiment, inlet guide vanes 286 are non-rotatable about longitudinal axis 214. Each inlet guide vane 286 defines a central blade axis (not labeled for clarity) and is rotatable about its respective central blade axis, for example, in unison with one another. In this manner, inlet guide vanes 286 can be considered variable geometry components. One or more actuators 288 are provided to facilitate such rotation and can therefore be used to vary the pitch of inlet guide vanes 286 about their respective central blade axes. However, in other embodiments, each inlet guide vane 286 may be fixed or non-pitched about its central vane axis.

[0053] Additionally, at a location downstream of the ducted fan 284 and upstream of the fan duct inlet 276, the gas turbine engine 210A includes an array of outlet guide vanes 290. Like the array of inlet guide vanes 286, the array of outlet guide vanes 290 is non-rotatable about the longitudinal axis 214. However, for the illustrated embodiment, unlike the array of inlet guide vanes 286, the array of outlet guide vanes 290 is configured as fixed-pitch outlet guide vanes.

[0054] Furthermore, it should be understood that for the illustrated embodiment, the fan exhaust nozzle 278 of the fan duct 272 is further configured as a variable geometry exhaust nozzle 278. In this manner, the gas turbine engine 210A includes one or more actuators 292 for adjusting the variable geometry exhaust nozzle 278. For example, the variable geometry fan exhaust nozzle 278 can be configured to vary the total cross-sectional area (e.g., the area of ​​the nozzle in a plane perpendicular to the longitudinal axis 214) to adjust the amount of thrust generated based on one or more engine operating conditions (e.g., the temperature, pressure, mass flow rate, etc. of the airflow through the fan duct 272). A fixed geometry exhaust nozzle may also be employed.

[0055] In addition, still refer to Figure 2 In an exemplary embodiment, the air passing through fan duct 272 may be relatively cooler (e.g., lower temperature) than one or more fluids utilized in turbine 230. In this manner, one or more heat exchangers 291 may be positioned in thermal communication with fan duct 272. For example, one or more heat exchangers 291 may be disposed within fan duct 272 and used to cool one or more fluids from the core engine using the air passing through fan duct 272 as a resource for removing heat from the fluids (e.g., compressor bleed air, oil, or fuel).

[0056] Still refer to Figure 2 As described above, the first propeller 200A includes an electric motor 300A operatively coupled to its rotating member. In this regard, the first propeller 200A is an aviation hybrid electric propulsion machine. In particular, as Figure 2 As shown, the electric motor 300A is mechanically coupled to the low-speed spool 255 of the gas turbine engine 210A, and more specifically, to the low-pressure shaft 246 of the low-speed spool 255. As shown, the electric motor 300A is embedded within the core of the gas turbine engine 210A. Specifically, the electric motor 300A is positioned inboard of the core duct 241 in the radial direction R. Furthermore, for this embodiment, the electric motor 300A is generally positioned at the rear end of the gas turbine engine 210A and at least partially overlaps or is rearward of the low-pressure turbine 242 in the axial direction A.

[0057] However, in other exemplary embodiments, the motor 300A may be positioned at other suitable locations within the gas turbine engine 210A. For example, in some embodiments, the motor 300A may be coupled to the low-speed spool 255 at other suitable locations. For example, in some embodiments, the motor 300A may be positioned in front of the low-pressure compressor 244 in the axial direction A and inward of the turbomachinery flow path 254 in the radial direction R. In addition, as Figure 2 As shown, electric machine 300A, which is mechanically coupled to low-pressure shaft 246 , is electrically coupled to power bus 184 .

[0058] In addition to or as an alternative to the gas turbine engine 210A having the electric machine 300A coupled to the low-speed spool 255, in the illustrated embodiment, the gas turbine engine 210A also includes an electric machine 302A mechanically coupled to the high-speed spool 253 of the gas turbine engine 210A, and more specifically, to the high-pressure shaft 238 of the high-speed spool 253. Figure 2 As shown, the motor 302A is mechanically coupled to the high pressure shaft 238 via a mechanical linkage. The motor 302A is positioned radially R outside the core duct 241 and axially A forward of the combustion section of the gas turbine engine 210A.

[0059] However, in other exemplary embodiments, the electric machine 302A may be positioned at other suitable locations within the gas turbine engine 210A (eg, inside the core duct 241 in the radial direction R).

[0060] Similar to the motor 300A mechanically coupled to the low-speed spool 255, the motor 302A mechanically coupled to the high-speed spool 253 may be an electric motor operable to drive or crank the high-pressure spool 238, for example, during a startup operation of the gas turbine engine 210A. In other embodiments, the motor 302A may be a generator operable to convert mechanical energy into electrical energy. In this manner, the electrical power generated by the motor 302A may be directed to various engine and / or aircraft systems. In some embodiments, the motor 302A may be a dual-function motor / generator.

[0061] In addition, if Figure 2 As shown, electric machine 302A, which is mechanically coupled to high voltage shaft 238, is also electrically coupled to power bus 184. More specifically, the aircraft power system may include a power electronics assembly 188 located between electric machines 300A, 302A and power bus 184. Power electronics assembly 188 may include one or more power inverters, power controllers, or other types of electronic components that are electrically coupled to one or more electric power loads (e.g., of an engine or aircraft, or both), a power source, or both.

[0062] Additionally or alternatively, in other exemplary embodiments, any other suitable gas turbine engine may be provided. For example, in other exemplary embodiments, the gas turbine engine may be a turboshaft engine, a turboprop engine, a turbojet engine, etc. Furthermore, for example, although the engine is described as a single unducted rotor engine, in other embodiments, the engine may include a multi-stage open rotor configuration, and the aspects of the present disclosure described below may be incorporated therein.

[0063] Now refer to Figure 3 , provides a simplified schematic diagram of a thermal management system 400 according to an exemplary aspect of the present disclosure. Figure 3 The exemplary thermal management system 400 may be incorporated into one or more of the gas turbine engines 210A, 210B and / or aircraft 100 described herein, or into any other suitable engine and / or aircraft.

[0064] The thermal management system flow path 401 is defined by the thermal management system 400 and is the flow path for a fluid flow to, through, or both the components of the thermal management system 400. The thermal management system flow path 401 may include one or more conduits, tubes, pipes, paths or passages, walls, or other structures for flow to, through, or both the components of the thermal management system 400. The fluid may have a suitable temperature for heat energy transfer corresponding to the desired or specific functions of the components of the thermal management system 400. In the exemplary embodiment, the fluid includes oil. However, it should be understood that the fluid flowing through the thermal management system flow path 401 may include any suitable fluid for heat energy transfer, such as, by way of non-limiting example, supercritical gases (e.g., carbon dioxide (CO2), nitrogen (N2), helium (He), xenon (Xe), and other gaseous mixtures), ethylene glycol, propylene glycol, Dow Corning's Syltherm TM or Exxon Mobil's Coolanol TM .

[0065] The exemplary thermal management system 400 generally includes an electric motor 402. The electric motor 402 is thermally coupled to a thermal management system flow path 401. When the thermal management system 400 is integrated with an engine, the electric motor 402 can be rotatable with a first rotating component of the engine. For example, in certain exemplary embodiments, the electric motor 402 can be coupled to a low-voltage spool (e.g., Figure 2 LP motor that rotates with the low speed spool 255 of the gas turbine engine 210A in the embodiment of the present invention, or the motor 402 can be an LP motor that rotates with the high speed spool of the engine (e.g., Figure 2The HP motor rotates together with the high-speed spool 253 of the gas turbine engine 210A.

[0066] Still refer to Figure 3 , the exemplary thermal management system 400 shown also includes a power electronics assembly 404 electrically connected to the motor 402. The power electronics assembly 404 is thermally connected to the thermal management system flow path 401 and the motor 402. The power electronics assembly 404 may include a power supply coupled to the gas turbine engine 210A, 210B, the aircraft 100, or both ( Figure 1 and Figure 2 ) in one or more of the power electronics assemblies 188. The power electronics assembly 404 may include one or more power converters 406 and one or more power controllers, and more specifically, one or more power distribution and monitoring units 408 (referred to herein as "PDMUs") that are electrically connected to the one or more power converters 406 and to one or more electrical power loads (e.g., of the engine or the aircraft or both), the power source, or both. In this manner, the one or more PDMUs 408 may receive electrical power from the one or more power converters 406 and may distribute the electrical power to one or more electrical power loads of the engine and the aircraft, for example, in response to one or more commands or other data inputs. Of course, in other embodiments, the directional flow of electrical power may be reversed. It should be understood that the PDMU 408 may include a PDMU that is similar to the one or more power converters 406 described below. Figure 9 The exemplary computing device of the described computing system 900 may be configured in substantially the same manner as the computing device. In this manner, the PDMU 408 may be configured to receive one or more data inputs and may make control decisions in response to the one or more data inputs.

[0067] The exemplary thermal management system 400 shown also includes a first heat exchanger 410 and a second heat exchanger 412. The first heat exchanger 410 is thermally connected to the thermal management system flow path 401 and the motor 402. The second heat exchanger 412 is thermally connected to the thermal management system flow path 401, the first heat exchanger 410, and the power electronics assembly 404, respectively. The first heat exchanger 410 and the second heat exchanger 412 can be located in the fan duct 272 ( Figure 2 ), for example, heat exchanger 291 ( Figure 2 ), exposed to the outboard air, located in the core cover 248 ( Figure 2 ) or located in the gas turbine engine 210A ( Figure 1 and Figure 2). The first heat exchanger 410 and the second heat exchanger 412 can be gas-to-gas, gas-to-liquid, liquid-to-liquid heat exchangers, or thermoelectric devices. The heat dissipation fluid associated with the first heat exchanger 410 and the second heat exchanger 412 can be fuel, water, water from the aircraft's lavatory system, refrigerant from the aircraft's environmental control system, or other suitable heat transfer fluids.

[0068] In the illustrated embodiment, the motor 402 is fluidly connected to the first heat exchanger 410 via a pipeline 414. The pipeline 414 partially defines the thermal management system flow path 401. As used herein, a "pipeline" may include any type of structure for enabling the passage or flow of a fluid (e.g., a conduit, a tube, a path or passage, a wall, etc.). The first heat exchanger 410 is located downstream of the motor 402 based on the flow direction of the fluid flowing through the thermal management system flow path 401. In an exemplary embodiment, the motor 402 may include a generator and an electric motor with an integrated fluid tank, a fluid pump, and a fluid filter. The fluid pump may be an electric pump or a mechanical pump.

[0069] First heat exchanger 410 is fluidically connected to second heat exchanger 412 via line 416. Line 416 partially defines thermal management system flow path 401. Second heat exchanger 412 is located downstream of first heat exchanger 410 based on the flow direction of fluid flowing through thermal management system flow path 401. Second heat exchanger 412 is fluidically connected to power electronics assembly 404 via line 418. Line 418 partially defines thermal management system flow path 401. Power electronics assembly 404 is located downstream of second heat exchanger 412 based on the flow direction of fluid flowing through thermal management system flow path 401. Power electronics assembly 404 is fluidically connected to motor 402 via line 420. Line 420 partially defines thermal management system flow path 401. Motor 402 is located downstream of power electronics assembly 404 based on the flow direction of fluid flowing through thermal management system flow path 401. Line 422 partially defines thermal management system flow path 401 and is fluidically connected to lines 416 and 420.

[0070] Flow splitter 424 partially defines thermal management system flow path 401 and fluidically connects line 422 with line 416. Flow splitter 424 is located downstream of first heat exchanger 410 and upstream of second heat exchanger 412, based on the flow direction of fluid flowing through thermal management system flow path 401. Flow splitter 424 is operable to split or divide the flow of fluid flowing through thermal management system flow path 401, such that fluid output from first heat exchanger 410 is split or divided by flow splitter 424 into a first portion 425 and a second portion 427. First portion 425 flows to second heat exchanger 412 via the remaining portion of line 416 downstream of flow splitter 424, and second portion 427 flows into line 422. In an exemplary embodiment, flow splitter 424 may include a standard Y- or T-type fitting, making flow splitter 424 a passive flow splitter. As a passive flow splitter, a normal operating pressure drop within the thermal management system flow path 401 of a component of the thermal management system 400 results in different volumes or portions of fluid being divided between two different flow paths. However, it should be understood that the flow splitter 424 can also include a flow control device 426 to actively regulate the flow of fluid to the second heat exchanger 412 and the line 422. The flow control device 426 can include an electronically controlled valve or other type of device so that the flow of the fluid can be actively regulated based on, as a non-limiting example, power or thermal demand.

[0071] Flow coupler 428 partially defines thermal management system flow path 401 and fluidically connects line 422 with line 420. Flow coupler 428 is located downstream of power electronics assembly 404 and upstream of motor 402, based on the flow direction of fluid flowing through thermal management system flow path 401. Flow coupler 428 is operable to couple, merge, or combine fluid flows flowing through thermal management system flow path 401, such that fluid output from power electronics assembly 404 joins or combines with fluid flowing through line 422 at a location downstream of power electronics assembly 404. In the illustrated embodiment, flow coupler 428 is operable to couple or combine a first portion 425 of the fluid flow flowing through thermal management system flow path 401 with a second portion 427 of the fluid flow flowing through thermal management system flow path 401. Thus, fluid output from power electronics assembly 404 joins or combines with fluid flowing through line 422 at a location downstream of power electronics assembly 404. In an exemplary embodiment, the flow coupler 428 may include a standard Y- or T-type fitting, such that the flow coupler 428 is a passive flow coupler. However, it should be understood that the flow coupler 428 may also include a flow control device 430 to actively regulate the combined flow of fluids from the power electronics assembly 404 and the pipeline 422. The flow control device 430 may include an electronically controlled valve or other type of device so that the flow of the fluid can be actively regulated based on, as non-limiting examples, power or thermal demand.

[0072] Thus, in the exemplary embodiment, thermal management system flow path 401 defines a first flow path loop 432 and a second flow path loop 434. First flow path loop 432 is thermally coupled to first heat exchanger 410 and motor 402. Second flow path loop 434 is thermally coupled to first heat exchanger 410, second heat exchanger 412, power electronics assembly 404, and motor 402. First flow path loop 432 includes motor 402, line 414, first heat exchanger 410, a portion of line 416 upstream of flow splitter 424, flow splitter 424, line 422, flow coupler 428, and a portion of line 420 downstream of flow coupler 428. Second flow path loop 434 includes motor 402, line 414, first heat exchanger 410, line 416, flow splitter 424, second heat exchanger 412, line 418, power electronics assembly 404, line 420, and flow coupler 428. In the exemplary embodiment, first flow path circuit 432 and second flow path circuit 434 each comprise a respective closed fluid circuit.

[0073] In operation, fluid flows downstream in thermal management system flow path 401 via line 414 to first heat exchanger 410. In an exemplary embodiment, first heat exchanger 410 is an air-cooled heat exchanger. In an exemplary embodiment, the thermal energy transfer fluid is oil. In such an embodiment, first heat exchanger 410 may be an air-cooled oil cooler (ACOC). The fluid flows downstream and is output from first heat exchanger 410 to line 416. The fluid flows downstream in thermal management system flow path 401 via line 416 to splitter 424. Splitter 424 separates, divides, or diverts the flow into a first portion 425 that flows downstream in thermal management system flow path 401 to second heat exchanger 412 and a second portion 427 that flows downstream in thermal management system flow path 401 to line 422. In an exemplary embodiment, second heat exchanger 412 is a fuel-cooled heat exchanger. In an exemplary embodiment, the thermal energy transfer fluid is oil. In such an embodiment, the second heat exchanger 412 is a fuel cooling oil cooler (FCOC).

[0074] A first portion 425 of the fluid flows downstream in thermal management system flow path 401 from second heat exchanger 412 via line 418 to power electronics assembly 404. The first portion 425 of the fluid flows downstream in thermal management system flow path 401 from power electronics assembly 404 via line 420 to flow coupler 428. A second portion 427 of the fluid flows downstream in thermal management system flow path 401 from flow splitter 424 via line 422 to flow coupler 428. Flow coupler 428 combines the first portion 425 of the fluid flowing downstream in thermal management system flow path 401 via line 420 with the second portion 427 of the fluid flowing downstream in thermal management system flow path 401 via line 422, resulting in a combined fluid flow that flows downstream in thermal management system flow path 401 to electric machine 402 via the remaining portion of line 420 located downstream of flow coupler 428.

[0075] Thus, in operation, approximately 100% of the fluid flows through the motor 402 and the first heat exchanger 410 via the thermal management system flow path 401. In the exemplary embodiment, the flow splitter 424 directs less than 100% of the fluid through the second heat exchanger 412 and the power electronics assembly 404 via the thermal management system flow path 401. In other words, approximately 100% of the fluid flows through the first flow path loop 432, and less than 100% of the fluid flows through the portion of the second flow path loop 434 that includes the second heat exchanger 412 and the power electronics assembly 404. In the exemplary embodiment, the first portion 425 of the fluid flowing through the thermal management system flow path 401 is less than or equal to the second portion 427 of the fluid flowing through the thermal management system flow path 401. In other words, in the exemplary embodiment, the flow splitter 424 directs 50% of the flow to the line 422 and 50% of the flow to the second heat exchanger 412 via the portion of the line 416 downstream of the flow splitter 424. It should be understood that the flow splitter 424 can divert a portion of the second flow path loop 434 through the second heat exchanger 412 and the rest of the flow through the power electronics assembly 404. In an exemplary embodiment, the flow ratio can be 90% of the flow directed to line 422 and 10% of the flow directed to the second heat exchanger 412 via the portion of line 416 downstream of the flow splitter 424. In an exemplary embodiment, the flow ratio can be 60% of the flow directed to line 422 and 40% of the flow directed to the second heat exchanger 412 via the portion of line 416 downstream of the flow splitter 424. In an exemplary embodiment, the flow ratio can be 70% of the flow directed to line 422 and 30% of the flow directed to the second heat exchanger 412 via the portion of line 416 downstream of the flow splitter 424. In an exemplary embodiment, the flow ratio may be 65% of the flow directed to line 422 and 35% of the flow directed to second heat exchanger 412 via a portion of line 416 downstream of flow splitter 424. In an exemplary embodiment, the flow ratio may be 64% of the flow directed to line 422 and 36% of the flow directed to second heat exchanger 412 via a portion of line 416 downstream of flow splitter 424. Thus, in an exemplary embodiment, a smaller portion of the fluid flow flowing through thermal management system flow path 401 flows to power electronics assembly 404 than to motor 402. Furthermore, a portion of the fluid flowing through thermal management system flow path 401 to power electronics assembly 404 has already flowed through at least two heat exchangers before reaching power electronics assembly 404.

[0076] Figure 4 is a simplified schematic diagram of a thermal management system 500 according to another exemplary aspect of the present disclosure. Figure 4The exemplary thermal management system 500 may be incorporated into one or more of the gas turbine engines 210A, 210B and / or aircraft 100 described herein, or into any other suitable engine and / or aircraft.

[0077] With the thermal management system 400( Figure 3 ), thermal management system flow path 501 is defined by thermal management system 500 and is the flow path of a fluid flow to a component of thermal management system 500, through a component of thermal management system 500, or both. Thermal management system 500 may be similar to Figure 3 The thermal management system 400 is configured to include a power electronics assembly 404, a first heat exchanger 410, and a second heat exchanger 412, each thermally connected to a thermal management system flow path 501. In the illustrated embodiment, the thermal management system 500 includes a motor 504, a fluid tank 506, and a pump assembly 508, each thermally connected to the thermal management system flow path 501. The motor 504 can be configured similarly to the motor 402 ( Figure 3 ), except that the motor 504 may not have an integrated fluid tank, fluid pump, and fluid filter. Instead, the thermal management system 500 includes a clearly positioned fluid tank 506 and a pump assembly 508. In the illustrated embodiment, the pump assembly 508 includes a fluid pump 510 and a fluid filter 512. The fluid pump 510 may be an electric pump or a mechanical pump. The motor 504 is electrically connected to the power electronics assembly 404. A first heat exchanger 410 is thermally connected to the motor 402. A second heat exchanger 412 is thermally connected to the first heat exchanger 410 and the power electronics assembly 404.

[0078] In the illustrated embodiment, the first heat exchanger 410 is fluidly connected to the second heat exchanger 412 via line 514. Line 514 partially defines the thermal management system flow path 501. The second heat exchanger 412 is located downstream of the first heat exchanger 410 based on the flow direction of the fluid flowing through the thermal management system flow path 501. The second heat exchanger 412 is fluidly connected to the power electronics assembly 404 via line 516. Line 516 partially defines the thermal management system flow path 501. The power electronics assembly 404 is located downstream of the second heat exchanger 412 based on the flow direction of the fluid flowing through the thermal management system flow path 501. The power electronics assembly 404 is fluidly connected to the fluid tank 506 via line 518. Line 518 partially defines the thermal management system flow path 501. The fluid tank 506 is located downstream of the power electronics assembly 404 based on the flow direction of the fluid flowing through the thermal management system flow path 501.

[0079] Fluid tank 506 is fluidically connected to pump assembly 508 via line 520. Line 520 partially defines thermal management system flow path 501. Pump assembly 508 is located downstream of fluid tank 506 based on the flow direction of fluid flowing through thermal management system flow path 501. First heat exchanger 410 is fluidically connected to pump assembly 508 via line 522. Line 522 partially defines thermal management system flow path 501. First heat exchanger 410 is located downstream of pump assembly 508 based on the flow direction of fluid flowing through thermal management system flow path 501.

[0080] Line 524 partially defines thermal management system flow path 501 and is fluidically connected to motor 504. Line 526 also partially defines thermal management system flow path 501 and is fluidically connected to motor 504. Thermal management system flow path 501 also includes a flow splitter 424 and a flow coupler 428. Flow splitter 424 fluidly connects line 524 to line 514. Flow splitter 424 is located downstream of first heat exchanger 410, upstream of second heat exchanger 412, and upstream of motor 504, based on the flow direction of fluid flowing through thermal management system flow path 401. Flow splitter 424 is operable to split or divide the flow of fluid flowing through thermal management system flow path 501, such that fluid output from first heat exchanger 410 is split or divided by flow splitter 424 into a first portion 525 and a second portion 427. First portion 525 flows to second heat exchanger 412 via the remaining portion of line 514 downstream of flow splitter 424, while second portion 427 flows into line 524. The flow diverter 424 may include a passive flow diverter or may include an active flow diverter, such as a flow control device 426 ( Figure 3 ).

[0081] Flow coupler 428 fluidly connects line 526 with line 518. Flow coupler 428 is located downstream of power electronics assembly 404, downstream of motor 504, and upstream of fluid tank 506, based on the flow direction of the fluid flowing through thermal management system flow path 501. Flow coupler 428 is operable to couple or combine the fluid flows flowing through thermal management system flow path 501, such that fluid output from power electronics assembly 404 couples or combines with fluid flowing through line 526 at a location downstream of motor 504. In the illustrated embodiment, flow coupler 428 is operable to couple or combine a first portion 525 of the fluid flow flowing through thermal management system flow path 501 with a second portion 527 of the fluid flow flowing through thermal management system flow path 501. Thus, the fluid output from power electronics assembly 404 (first portion 525) couples or combines with fluid flowing through line 526 (second portion 527) at a location downstream of power electronics assembly 404. The flow coupler 428 may include a passive flow coupler or an active flow coupler, such as a flow control device 430 ( Figure 3 ).

[0082] Thus, in the exemplary embodiment, thermal management system flow path 501 defines a first flow path loop 532 and a second flow path loop 534. First flow path loop 532 is thermally coupled to first heat exchanger 410, motor 504, fluid tank 506, and pump assembly 508. Second flow path loop 434 is thermally coupled to first heat exchanger 410, second heat exchanger 412, power electronics assembly 404, fluid tank 506, and pump assembly 508. First flow path loop 532 includes first heat exchanger 410, a portion of line 514 upstream of flow splitter 424, flow splitter 424, line 524, motor 504, line 526, flow coupler 428, a portion of line 518 downstream of flow coupler 428, fluid tank 506, line 520, pump assembly 508, and line 522. Second flow path loop 534 includes first heat exchanger 410, line 514, flow splitter 424, second heat exchanger 412, line 516, power electronics assembly 404, line 518, flow coupler 428, fluid tank 506, line 520, pump assembly 508, and line 522. In the exemplary embodiment, first flow path loop 432 and second flow path loop 434 each include a respective closed fluid circuit.

[0083] In operation, fluid flows downstream in the thermal management system flow path 501 from the pump assembly 508 via line 522 to the first heat exchanger 410. The fluid flows downstream in the thermal management system flow path 501 and is output from the first heat exchanger 410 to line 514. The fluid flows downstream in the thermal management system flow path 501 via line 514 to the flow splitter 424. The flow splitter 424 separates, divides, or diverts the flow into a first portion 525 that flows downstream in the thermal management system flow path 501 to the second heat exchanger 412 and a second portion 527 that flows downstream in the thermal management system flow path 501 to line 524. The second portion 527 flows downstream in the thermal management system flow path 501 along line 524 to the motor 504.

[0084] First portion 525 flows downstream in thermal management system flow path 501 along a portion of line 514 downstream of flow divider 424 to second heat exchanger 412. First portion 525 flows downstream in thermal management system flow path 501 and is output by second heat exchanger 412 to line 516, where first portion 525 flows along line 516 to power electronics assembly 404. First portion 525 flows downstream in thermal management system flow path 501 and is output by power electronics assembly 404 to line 518. First portion 525 flows downstream in thermal management system flow path 501 along line 518 to flow adapter 428. Second portion 527 flows downstream in thermal management system flow path 501 and is output by motor 504 to line 526. Second portion 527 flows downstream in thermal management system flow path 501 along line 526 to flow adapter 428. Flow coupler 428 couples or combines first portion 525 and second portion 527 and causes the combined fluid to flow downstream in thermal management system flow path 501 to fluid tank 506. Fluid flows downstream in thermal management system flow path 501 from fluid tank 506 to pump assembly 508 via line 520.

[0085] In an exemplary embodiment, the flow divider 424 may be configured to be in a manner similar to that of the first and second portions 425 and 427 ( Figure 3 ) splits or divides the fluid flow into first portion 525 and second portion 527 at a similar ratio such that the volume or portion of the flow provided to power electronics assembly 404 is equal to or less than the volume or portion of the flow provided to motor 504. In the exemplary embodiment, the flow provided to power electronics assembly 404 passes through a greater number of heat exchangers than the flow provided to motor 504.

[0086] Figure 5 is a simplified schematic diagram of a thermal management system 600 according to another exemplary aspect of the present disclosure. Figure 5 The exemplary thermal management system 600 may be incorporated into one or more of the gas turbine engines 210A, 210B and / or aircraft 100 described herein, or into any other suitable engine and / or aircraft. The thermal management system 600 is configured similarly to the thermal management system 500 ( Figure 4 ), except that the fluid tank 506 and the pump assembly 508 are located downstream of the first heat exchanger 410. Figure 5 In the illustrated embodiment, the fluid tank 506 is a cold fluid tank 506 because the fluid flowing to the fluid tank 506 is received at the fluid tank 506 from the first heat exchanger 410 via line 520 .

[0087] Figure 6is a simplified schematic diagram of a thermal management system 700 according to another exemplary aspect of the present disclosure. Figure 6 The exemplary thermal management system 700 may be incorporated into one or more of the gas turbine engines 210A, 210B and / or aircraft 100 described herein, or into any other suitable engine and / or aircraft.

[0088] With the thermal management system 400( Figure 3 ), thermal management system 500( Figure 4 ) and thermal management system 600 ( Figure 5 ), thermal management system flow path 701 is defined by thermal management system 700 and is the flow path of a fluid flow to components of thermal management system 700, through components of thermal management system 700, or both. Thermal management system 700 may be configured similarly to thermal management system 600 ( Figure 5 ), includes a power electronics assembly 404, a first heat exchanger 410, a second heat exchanger 412, a fluid tank 506, a pump assembly 508, and a motor 504, each thermally connected to a thermal management system flow path 701. The motor 504 is connected to the power electronics assembly 404. In the illustrated embodiment, the thermal management system 700 also includes a third heat exchanger 704 thermally connected to the thermal management system flow path 701. The third heat exchanger 704 can be configured similarly to the first heat exchanger 410 or the second heat exchanger 412. The thermal management system 700 also includes a flow splitter 424 and a flow coupler 428, each thermally connected to the thermal management system flow path 701.

[0089] In the illustrated embodiment, the first heat exchanger 410 is fluidly connected to the second heat exchanger 412 via line 710. Line 710 partially defines a thermal management system flow path 701. The second heat exchanger 412 is located downstream of the first heat exchanger 410 based on the flow direction of the fluid flowing through the thermal management system flow path 701. The second heat exchanger 412 is fluidly connected to the power electronics assembly 404 via line 712. Line 712 partially defines the thermal management system flow path 701. The power electronics assembly 404 is located downstream of the second heat exchanger 412 based on the flow direction of the fluid flowing through the thermal management system flow path 701. The power electronics assembly 404 is fluidly connected to the fluid tank 506 via line 714. Line 718 partially defines the thermal management system flow path 701. The fluid tank 506 is located downstream of the power electronics assembly 404 based on the flow direction of the fluid flowing through the thermal management system flow path 701.

[0090] Fluid tank 506 is fluidically connected to pump assembly 508 via line 716. Line 716 partially defines thermal management system flow path 701. Pump assembly 508 is located downstream of fluid tank 506 based on the flow direction of fluid flowing through thermal management system flow path 701. First heat exchanger 410 is fluidically connected to pump assembly 508 via line 718. Line 718 partially defines thermal management system flow path 701. First heat exchanger 410 is located downstream of pump assembly 508 based on the flow direction of fluid flowing through thermal management system flow path 701.

[0091] Line 720 partially defines thermal management system flow path 701 and is fluidically connected to third heat exchanger 704. Line 720 fluidically connects third heat exchanger 704 to flow splitter 424. Based on the flow direction of fluid flowing through thermal management system flow path 701, flow splitter 424 is located downstream of first heat exchanger 410, second heat exchanger 412 is located downstream of flow splitter 424, and third heat exchanger 704 is located downstream of flow splitter 424. Flow splitter 424 is operable to split or divide the flow of fluid flowing through thermal management system flow path 701, such that fluid output from first heat exchanger 410 is split or divided by flow splitter 424 into a first portion 725 and a second portion 727. First portion 725 flows to second heat exchanger 412 via the remaining portion of line 710 downstream of flow splitter 424, while second portion 727 flows into line 720 and to third heat exchanger 704. The flow diverter 424 may include a passive flow diverter or may include an active flow diverter, such as a flow control device 426 ( Figure 3 ).

[0092] Line 722 partially defines thermal management system flow path 701 and is fluidically connected to third heat exchanger 704. Line 722 fluidically connects third heat exchanger 704 to motor 504. Motor 504 is located downstream of third heat exchanger 704 based on the flow direction of fluid flowing through thermal management system flow path 701. Line 724 partially defines thermal management system flow path 701 and is fluidically connected to motor 504. Line 724 fluidically connects motor 504 to flow coupler 428. Flow coupler 428 is located downstream of motor 504 based on the flow direction of fluid flowing through thermal management system flow path 701.

[0093] Flow coupler 428 fluidly connects line 724 with line 714. Flow coupler 428 is located downstream of power electronics assembly 404, downstream of motor 504, and upstream of fluid tank 506, based on the flow direction of fluid flowing through thermal management system flow path 701. Flow coupler 428 is operable to couple or combine the fluid flows flowing through thermal management system flow path 701, such that fluid output from power electronics assembly 404 couples or combines with fluid flowing through line 724 at a location downstream of motor 504. In the illustrated embodiment, flow coupler 428 is operable to couple or combine a first portion 725 of the fluid flow flowing through thermal management system flow path 701 with a second portion 727 of the fluid flow flowing through thermal management system flow path 701. Thus, fluid output from power electronics assembly 404 (first portion 725) couples or combines with fluid output from motor 504 (second portion 727) flowing through line 724. The flow coupler 428 may include a passive flow coupler or an active flow coupler, such as a flow control device 430 ( Figure 3 ).

[0094] Thus, in the exemplary embodiment, thermal management system flow path 701 defines a first flow path loop 732 and a second flow path loop 734. First flow path loop 732 is thermally coupled to first heat exchanger 410, third heat exchanger 704, motor 504, fluid tank 506, and pump assembly 508. Second flow path loop 734 is thermally coupled to first heat exchanger 410, second heat exchanger 412, power electronics assembly 404, fluid tank 506, and pump assembly 508. First flow path loop 432 includes first heat exchanger 410, a portion of line 710 upstream of flow splitter 424, line 720, third heat exchanger 704, line 722, motor 504, line 724, flow coupler 428, a portion of line 714 downstream of flow coupler 428, fluid tank 506, line 716, pump assembly 508, and line 718. Second flow path loop 734 includes first heat exchanger 410, line 710, flow splitter 424, second heat exchanger 412, line 712, power electronics assembly 404, line 714, flow coupler 428, fluid tank 506, line 716, pump assembly 508, and line 718. In the exemplary embodiment, first flow path loop 732 and second flow path loop 734 each comprise a respective closed fluid circuit.

[0095] In operation, fluid flows downstream in the thermal management system flow path 701 from the pump assembly 508 via line 718 to the first heat exchanger 410. The fluid flows downstream in the thermal management system flow path 701 and is output from the first heat exchanger 410 to line 710. The fluid flows downstream in the thermal management system flow path 701 via line 710 to the flow splitter 424. The flow splitter 424 separates, divides, or splits the flow into a first portion 725 that flows downstream in the thermal management system flow path 701 to the second heat exchanger 412 and a second portion 727 that flows downstream in the thermal management system flow path 701 to line 720. The second portion 727 flows downstream in the thermal management system flow path 701 via line 720 to the third heat exchanger 704.

[0096] The first portion 525 flows downstream in the thermal management system flow path 701 along a portion of line 710 downstream of the flow splitter 424 to the second heat exchanger 412. The first portion 525 flows downstream in the thermal management system flow path 701 and is output by the second heat exchanger 412 to line 712, where the first portion 525 flows along line 712 to the power electronics assembly 404. The first portion 525 flows downstream in the thermal management system flow path 701 and is output by the power electronics assembly 404 to line 714. The first portion 525 flows downstream in the thermal management system flow path 701 along line 714 to the flow coupler 428.

[0097] The second portion 527 flows downstream in the thermal management system flow path 701 and is output from the third heat exchanger 704 to line 722. The second portion 527 flows downstream in the thermal management system flow path 701 along line 722 to the motor 504. The second portion 527 flows downstream in the thermal management system flow path 701 and is output by the motor 504 to line 724. The second portion 527 flows downstream in the thermal management system flow path 701 along line 724 to the flow coupler 428. The flow coupler 428 couples or combines the first portion 525 and the second portion 527 and causes the combined fluid to flow downstream in the thermal management system flow path 701 to the fluid tank 506. The fluid flows downstream in the thermal management system flow path 701 from the fluid tank 506 to the pump assembly 508 via line 716.

[0098] In an exemplary embodiment, the flow divider 424 may be configured to be in a manner similar to that of the first and second portions 425 and 427 ( Figure 3 ) splits or divides the fluid flow into a first portion 725 and a second portion 727 at a similar ratio such that the volume or portion of the flow provided to the power electronics assembly 404 is equal to or less than the volume or portion of the flow provided to the motor 504.

[0099] Therefore, in an exemplary embodiment, if Figure 3-6 The individual thermal management systems 400, 500, 600, or 700 shown may be used for one or more electric machines. For example, consider the thermal management system 400 ( Figure 3 ), there may be one thermal management system 400 for the HP motor and one thermal management system 400 for the LP motor. Thus, in the exemplary embodiment, there is a thermal management system flow path 401 for the HP motor and a separate thermal management system flow path 401 for the LP motor (i.e., separate fluid circuits, one for the HP motor and one for the LP motor). However, it should be understood that each thermal management system flow path 401 may share specific heat exchangers. For example, the thermal management system flow path 401 for the HP motor and the thermal management system flow path 401 for the LP motor may use the same heat exchanger (e.g., FCOC) to provide thermal energy transfer for their respective fluid circuits.

[0100] Figure 7 is a simplified schematic diagram of a thermal management system 800 according to another exemplary aspect of the present disclosure. Figure 7 The exemplary thermal management system 800 may be incorporated into one or more of the gas turbine engines 210A, 210B and / or aircraft 100 described herein, or into any other suitable engine and / or aircraft.

[0101] With the thermal management system 400( Figure 3 ), thermal management system 500( Figure 4 ), thermal management system 600 ( Figure 5 ) and thermal management system 700( Figure 6 ), thermal management system flow path 801 is defined by thermal management system 800 and is the flow path of a fluid flow to a component of thermal management system 800, through a component of thermal management system 800, or both. Thermal management system 800 may be configured similarly to thermal management system 600 ( Figure 5), includes a first heat exchanger 410, a second heat exchanger 412, a fluid tank 506, and a pump assembly 508, each of which is thermally connected to a thermal management system flow path 801. In the illustrated embodiment, the thermal management system 800 includes a first electric machine 802 and a second electric machine 804, each of which is thermally connected to the thermal management system flow path 801. The first electric machine 802 can be an LP electric machine, and the second electric machine 804 can be an HP electric machine. In an exemplary embodiment, the first heat exchanger 410 can be an air-cooled heat exchanger, and the second heat exchanger 412 can be a fuel-cooled heat exchanger. Therefore, in an exemplary embodiment where the thermal energy transfer fluid is oil, the first heat exchanger 410 can be an ACOC, and the second heat exchanger 412 can be an FCOC. The thermal management system 700 also includes flow splitters 806, 808, and 810, and flow couplers 812, 814, and 816, each of which is thermally connected to the thermal management system flow path 801 and partially defines the thermal management system flow path 801. Each of the splitters 806, 808, and 810 may be configured similarly to splitter 424 ( Figure 3 ), and each of the flow combiners 812, 814, and 816 may be configured similarly to flow combiner 428 ( Figure 3 ). Thus, one or more of the flow splitters 806, 808, and 810 may be configured as passive flow splitters or active flow splitters, and one or more of the flow joiners 812, 814, and 816 may be configured as passive flow joiners or active flow joiners.

[0102] In the illustrated embodiment, the thermal management system 800 includes a power electronics assembly 818 thermally coupled to the thermal management system flow path 801. The power electronics assembly 818 may be configured similarly to the power electronics assembly 404 ( Figure 3-6 ), and may include one or more power converters, one or more PDMUs, or both electrically connected to the first motor 802, the second motor 804, or both. In an exemplary embodiment, the power electronics assembly 818 includes a power converter 820 thermally connected to the thermal management system flow path 801. In an exemplary embodiment, the power converter 820 is connected to the first motor 802. Therefore, if the first motor 802 is a low-power motor, the power converter 820 can be connected to the low-power motor. In the illustrated embodiment, the power electronics assembly 818 includes a PDMU 822 and a power converter 824, each thermally connected to the thermal management system flow path 801. In an exemplary embodiment, the PDMU 822 and the power converter 824 are connected to the second motor 804. Therefore, if the second motor 804 is a high-power motor, the PDMU 822 and the power converter 824 can be connected to the high-power motor.

[0103] In the illustrated embodiment, the fluid tank 506 is fluidly connected to the pump assembly 508 via line 830. Line 830 partially defines the thermal management system flow path 801. The pump assembly 508 is located downstream of the fluid tank 506 based on the flow direction of the fluid flowing through the thermal management system flow path 801. The pump assembly 508 is fluidly connected to the first heat exchanger 410 via line 832. Line 832 partially defines the thermal management system flow path 801. The first heat exchanger 410 is located downstream of the pump assembly 508 based on the flow direction of the fluid flowing through the thermal management system flow path 801.

[0104] In the illustrated embodiment, the thermal management system 800 includes an accessory gearbox (AGB) 833 for providing rotational energy or power to the pump assembly 508, the second electric motor 804, or both. The AGB 833 can be connected to the pump assembly 508, the second electric motor 804, or both using a gearbox splitter mechanism or a common or single drive shaft. It should also be understood that the pump assembly 508 can be integrated as part of the second electric motor 804 and driven by the AGB 833.

[0105] Line 834 is fluidly connected to first heat exchanger 410 and flow splitter 806. Line 834 partially defines thermal management system flow path 801. Flow splitter 806 is located downstream of first heat exchanger 410 based on the flow direction of the fluid flowing through thermal management system flow path 801. Line 836 is fluidly connected to flow splitter 806, second heat exchanger 412, flow splitter 808, and second electric machine 804. Line 836 partially defines thermal management system flow path 801. Flow splitter 806 splits, divides, or separates the flow output from first heat exchanger 410 into a first portion 825 and a second portion 827. First portion 825 flows downstream from flow splitter 806 to second heat exchanger 412 along a portion of line 836. Second portion 827 flows downstream from flow splitter 806 to flow splitter 808 along a portion of line 836. The splitter 808 splits, divides, or separates the flow output from the splitter 806 (ie, the second portion 827 ) into a third portion 828 and a fourth portion 829 .

[0106] Line 838 is fluidly connected to flow divider 808 and first electric machine 802. Line 838 partially defines thermal management system flow path 801. Third portion 828 flows downstream from flow divider 808 to first electric machine 802 via line 838 based on the flow direction of the fluid flowing through thermal management system flow path 801. Fourth portion 829 flows downstream from flow divider 808 to second electric machine 804 along a portion of line 836 based on the flow direction of the fluid flowing through thermal management system flow path 801.

[0107] Line 840 is fluidically connected to the second electric machine 804, flow coupler 812, flow coupler 816, and fluid tank 506. Line 840 partially defines thermal management system flow path 801. A fourth portion 829 flows downstream from the second electric machine 804 to flow coupler 812 via line 840 based on the flow direction of the fluid flowing through thermal management system flow path 801. Line 842 is fluidically connected to the first electric machine 802 and flow coupler 812. Line 842 partially defines thermal management system flow path 801. A third portion 828 flows downstream from the first electric machine 802 to flow coupler 812 via line 842 based on the flow direction of the fluid flowing through thermal management system flow path 801. Flow coupler 812 joins or combines third and fourth portions 828 and 829 and allows the combined flow, which substantially reforms second portion 827, to flow via line 840 to flow coupler 816.

[0108] Second heat exchanger 412 is fluidically connected to power electronics assembly 818 via line 844. Line 844 partially defines thermal management system flow path 801. Line 844 is thermally connected to second heat exchanger 412, flow splitter 810, and power converter 820. A first portion 825 of the fluid flows from second heat exchanger 412 to flow splitter 810 via line 844 based on the flow direction of the fluid flowing through thermal management system flow path 801. Line 848 is fluidically connected to flow splitter 810 and PDMU 822. Line 848 partially defines thermal management system flow path 801. Flow splitter 810 splits, divides, or separates the flow output from second heat exchanger 412 (i.e., first portion 825) into a fifth portion 845 and a sixth portion 846. Fifth portion 845 flows downstream to power converter 820 via a portion of line 844 located downstream of flow splitter 810 based on the flow direction of the fluid flowing through thermal management system flow path 801. The sixth portion 846 flows downstream to the PDMU 822 via line 848 based on the flow direction of the fluid flowing through the thermal management system flow path 801 .

[0109] Line 850 is fluidically connected to PDMU 822 and power converter 824. Line 852 is fluidically connected to power converter 824 and flow coupler 814. Line 854 is fluidically connected to power converter 820, flow coupler 814, and flow coupler 816. Lines 850, 852, and 854 each partially define thermal management system flow path 801. Sixth portion 846 flows downstream from PDMU 822 to power converter 824 via line 850 based on the flow direction of the fluid flowing through thermal management system flow path 801. Sixth portion 846 flows downstream from power converter 824 to flow coupler 814 via line 852 based on the flow direction of the fluid flowing through thermal management system flow path 801. Fifth portion 845 flows downstream from power converter 820 to flow coupler 814 via line 854 based on the flow direction of the fluid flowing through thermal management system flow path 801.

[0110] Flow coupler 814 couples or combines fifth portion 845 with sixth portion 846, and based on the flow direction of the fluid flowing through thermal management system flow path 801, causes the combined fluid, which substantially reforms first portion 825, to flow via a portion of line 854 located downstream of flow coupler 814 to flow coupler 816, where the combined fluid is joined or combined with fourth portion 829. The combined fluid flows downstream from flow coupler 816 to fluid tank 506 via a portion of line 840 located downstream of flow coupler 816, based on the flow direction of the fluid flowing through thermal management system flow path 801.

[0111] Thus, in an exemplary embodiment, thermal management system flow path 801 forms a closed fluid loop that provides thermal energy management for one or more electric machines and one or more power electronic components connected to the one or more electric machines. A portion of the fluid flowing through thermal management system flow path 801 is used to cool the one or more electric machines, and another portion of the fluid flowing through thermal management system flow path 801 is used to cool the power converter and PDMU connected to the one or more electric machines.

[0112] See also Figure 8, a block diagram describing an exemplary method 860 for thermal management of an aircraft power system is provided. Method 860 begins at 862, where a flow of thermal energy transfer fluid flows through thermal management system flow path 401 to first heat exchanger 410. At 864, the flow of thermal energy transfer fluid passes through first heat exchanger 410. At 866, the flow of thermal energy transfer fluid output from first heat exchanger 410 is split into a first portion 425 and a second portion 427. At 868, at least the second portion 427 of the thermal energy transfer fluid flows through thermal management system flow path 401 to electric machine 402 of a gas turbine engine. At 870, the first portion 425 of the thermal energy transfer fluid flows through thermal management system flow path 401 to second heat exchanger 412. At 872, the first portion 425 of the thermal energy transfer fluid output from second heat exchanger 412 flows through thermal management system flow path 401 to power electronics assembly 404 electrically connected to electric machine 402.

[0113] Figure 9 An example computing system 900 is provided according to an example embodiment of the present disclosure. For example, computing devices or elements described herein, such as PDMUs 408 and 822, may include various components and perform various functions of the computing system 900 described below.

[0114] like Figure 9 As shown, computing system 900 may include one or more computing devices 902. Computing device 902 may include one or more processors 902A and one or more memory devices 902B. The one or more processors 902A 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 902B may include one or more computer-executable or computer-readable media, including but not limited to non-transitory computer-readable media, RAM, ROM, hard drives, flash drives, and / or other memory devices.

[0115] One or more memory devices 902B may store information accessible by one or more processors 902A, including computer-readable instructions 902C executable by one or more processors 902A. Computer-readable instructions 902C may be any set of instructions that, when executed by one or more processors 902A, cause one or more processors 902A to perform operations. In some embodiments, computer-readable instructions 902C may be executed by one or more processors 902A to cause one or more processors 902A to perform operations, such as any operations and functions for which computing system 900 and / or computing device 902 is configured, such as controlling the operation of a power system or power electronics components, motors, and one or more flow control devices 426 and 430. Computer-readable instructions 902C may be software written in any suitable programming language or may be implemented in hardware. Additionally and / or alternatively, computer-readable instructions 902C may be executed in logically and / or virtually separate threads on processor 902A. Memory device 902B may further store data 902D accessible by processor 902A. For example, data 902D may include models, lookup tables, databases, and the like.

[0116] The computing device 902 may also include a network interface 902E for communicating with other components of the computing system 900 (e.g., via a communication network). The network interface 902E 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. One or more devices may be configured to receive one or more commands from the computing device 902 or to provide one or more commands to the computing device 902.

[0117] The techniques discussed herein refer to computer-based systems and the actions taken by computer-based systems and the information sent to and from computer-based systems. Those skilled in the art will recognize that the inherent flexibility of computer-based systems allows for various possible configurations, combinations, and partitioning of tasks and functions between and within 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 across multiple systems. Distributed components can operate sequentially or in parallel.

[0118] Therefore, the present disclosure provides a thermal management system tailored to meet the thermal requirements of the LP and HP motors, as well as the power distribution components associated with them. The present disclosure provides dedicated or separate cooling circuits for hybrid electric systems. Each cooling circuit provides thermal management for the LP and HP motors, as well as the power converters and distribution electronics associated with them, to meet the aforementioned unique thermal requirements. In an exemplary embodiment, these cooling circuits are separate from other engine cooling circuits and include the motors and power electronics electrically connected to them. In an exemplary embodiment, for the LP motor circuit, heat exchange fluid is pumped from a tank to a heat exchanger and then to a splitter. A portion of the post-splitter heat exchange fluid flows to the LP motor, and the remainder flows to another heat exchanger before flowing to the power electronics for boost cooling. Exhaust heat exchange fluid from the LP motor and power electronics meet and combine to return to the tank. The HP motor circuit can be configured similarly to the LP motor circuit, but the HP motor's generator assembly can include a tank and pump, allowing the HP motor to be cooled by ACOC oil along with exhaust oil from the power electronics.

[0119] Further aspects are provided by the subject matter of the following clauses:

[0120] A propulsion system comprises: a power electronics assembly electrically connected to an electric motor; and a thermal management system defining a thermal management system flow path and operable to provide a fluid flow to the electric motor and the power electronics assembly through the thermal management system flow path, the thermal management system comprising: a first heat exchanger thermally connected to the thermal management system flow path and the electric motor; and a second heat exchanger thermally connected to the thermal management system flow path downstream of the first heat exchanger, the second heat exchanger being connected to the power electronics assembly.

[0121] A propulsion system according to the preceding clause, wherein the thermal management system flow path includes a splitter located downstream of the first heat exchanger, the splitter dividing the fluid flow into a first portion of the fluid flow and a second portion of the fluid flow, the splitter transferring the first portion of the fluid flow to the second heat exchanger, and wherein at least the second portion of the fluid flow flows to the electric machine.

[0122] A propulsion system as described in any preceding clause, wherein the first portion is equal to or less than the second portion.

[0123] The propulsion system of any preceding clause, wherein the thermal management system flow path includes a flow coupler positioned downstream of a power converter system, the flow coupler combining the first portion of the fluid flow with the second portion of the fluid flow.

[0124] The propulsion system of any preceding clause, wherein the thermal management system flow path includes a flow control device that regulates the fluid flow to the second heat exchanger.

[0125] The propulsion system of any preceding clause, wherein the electric machine comprises one or more of a fluid tank, a fluid pump, or a fluid filter.

[0126] The propulsion system of any preceding clause, wherein the first heat exchanger comprises an air-cooled heat exchanger.

[0127] The propulsion system of any preceding clause, wherein the second heat exchanger comprises a fuel cooling heat exchanger.

[0128] A propulsion system as described in any preceding clause, wherein the fluid comprises at least one of oil, carbon dioxide, nitrogen, helium or xenon.

[0129] The propulsion system of any preceding clause, wherein the fluid comprises oil, and wherein the first heat exchanger comprises an air-cooled oil cooler, and wherein the second heat exchanger comprises a fuel-cooled oil cooler.

[0130] The propulsion system of any preceding clause, further comprising a gas turbine engine comprising, in series flow order, a compressor section, a combustion section, and a turbine section, wherein the electric machine is configured to provide power to the gas turbine engine.

[0131] The propulsion system of any preceding clause, further comprising a gas turbine engine including a high pressure system and a low pressure system, and wherein the electric machine is coupled to one of the high pressure system or the low pressure system.

[0132] The propulsion system of any preceding clause, further comprising a computing system configured to control operation of at least one of the electric machine, the power electronics assembly, or the flow control device.

[0133] A method for thermal management of an aircraft, the method comprising: flowing a fluid flow through a thermal management system flow path to a first heat exchanger, the first heat exchanger being thermally connected to the thermal management system flow path; flowing the fluid flow through the first heat exchanger; splitting the fluid flow from the first heat exchanger into a first portion of the fluid flow and a second portion of the fluid flow; flowing at least the second portion of the fluid flow through the thermal management system flow path to an electric motor of a gas turbine engine, the electric motor being thermally connected to the thermal management system flow path; flowing the first portion of the fluid flow through the thermal management system flow path to a second heat exchanger, the second heat exchanger being thermally connected to the thermal management system flow path; and flowing the first portion of the fluid flow from the second heat exchanger through the thermal management system flow path to a power electronics component electrically connected to the electric motor, the power electronics component being thermally connected to the thermal management system flow path.

[0134] The method of any preceding clause, further comprising splitting the fluid flow from the first heat exchanger such that the first portion is equal to or less than the second portion.

[0135] The method of any preceding clause, wherein the fluid comprises oil, and wherein flowing the fluid flow through the thermal management system flow path to the first heat exchanger comprises flowing the oil flow through the thermal management system flow path to an air-cooled oil cooler.

[0136] The method of any preceding clause, wherein the fluid comprises oil, and wherein flowing the second portion of the fluid flow from the first heat exchanger through the thermal management system flow path to the second heat exchanger comprises flowing the second portion of the oil flow from the first heat exchanger through the thermal management system flow path to a fuel cooling oil cooler.

[0137] The method of any preceding clause, further comprising: combining the first portion of the fluid flow with the second portion of the fluid flow downstream of the power electronics assembly to form a combined fluid flow; and flowing the combined fluid flow through the thermal management system flow path to the electric machine.

[0138] The method of any preceding clause, further comprising: combining the first portion of the fluid flow with the second portion of the fluid flow downstream of the power electronics component to form a combined fluid flow; and flowing the combined fluid flow through the thermal management system flow path to the first heat exchanger.

[0139] A propulsion system includes: a thermal management system defining a thermal management system flow path and operable to provide a fluid flow to an electric machine and a power converter system through the thermal management system flow path, the power electronics assembly being electrically connected to the electric machine, the thermal management system flow path defining: a first flow path loop thermally connected to a first heat exchanger and the electric machine; and a second flow path loop thermally connected to the first heat exchanger, a second heat exchanger downstream of the first heat exchanger, and the power electronics assembly.

[0140] The propulsion system of any preceding clause, further comprising a flow splitter thermally connected to the first flow path circuit and the second flow path circuit downstream of the first heat exchanger, the flow splitter diverting a portion of the fluid flow into the second flow path circuit.

[0141] The propulsion system of any preceding clause, further comprising a flow coupler thermally connected to the first flow path circuit and the second flow path circuit, downstream of the power electronics assembly, the flow coupler combining the portion of the fluid flow flowing through the second flow path circuit with another portion of the fluid flow flowing through the first flow path circuit.

[0142] The propulsion system of any preceding clause, wherein the fluid comprises oil, and wherein the first heat exchanger comprises an air-cooled oil cooler, and wherein the second heat exchanger comprises a fuel-cooled oil cooler.

[0143] An aircraft, comprising: a hybrid electric propulsion system, the hybrid electric propulsion system comprising: a gas turbine engine, the gas turbine engine including a high-pressure system and a low-pressure system; an electric motor, the electric motor being coupled to one of the high-pressure system or the low-pressure system; and a power electronics assembly, the power electronics assembly being electrically connected to the electric motor; a thermal management system, the thermal management system defining a thermal management system flow path and being operable to provide a fluid flow to the electric motor and the power electronics assembly through the thermal management system flow path, the thermal management system comprising: a first heat exchanger, the first heat exchanger being thermally coupled to the thermal management system flow path and the electric motor; and a second heat exchanger, the second heat exchanger being thermally coupled to the thermal management system flow path downstream of the first heat exchanger, the second heat exchanger being thermally coupled to the power electronics assembly.

[0144] A non-transitory computer-readable medium including computer-executable instructions that, when executed by a processor associated with an electronic controller, cause the electronic controller to perform a method for thermally managing a hybrid electric propulsion system for an aircraft, the hybrid electric propulsion system including a gas turbine engine having a high pressure system, a low pressure system, and an electric machine coupled to one of the high pressure system or the low pressure system, the method comprising: flowing a fluid flow through a thermal management system flow path to a first heat exchanger, the first heat exchanger being thermally connected to the thermal management system flow path; flowing the fluid flow through the first heat exchanger; and transferring heat from the first heat exchanger to the thermal management system flow path. The fluid flow of the first heat exchanger is split into a first portion of the fluid flow and a second portion of the fluid flow; at least the second portion of the fluid flow is caused to flow through the thermal management system flow path to the motor, the motor being thermally connected to the thermal management system flow path; the first portion of the fluid flow is caused to flow through the thermal management system flow path to a second heat exchanger, the second heat exchanger being thermally connected to the thermal management system flow path; and the first portion of the fluid flow is caused to flow from the second heat exchanger through the thermal management system flow path to a power electronic component electrically connected to the motor, the power electronic component being thermally connected to the thermal management system flow path.

[0145] This written description uses examples to disclose the present disclosure, including the best mode, and also to enable any person 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 be 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 with insubstantial differences from the literal language of the claims.

Claims

1. A propulsion system, characterized in that: include: A thermal management system defining a thermal management system flow path and operable to provide a fluid flow through the thermal management system flow path to an electric machine and a power electronics assembly electrically connected to the electric machine, the thermal management system comprising: a first heat exchanger thermally coupled to the thermal management system flow path and the electric machine; and A second heat exchanger is thermally coupled to the thermal management system flow path downstream of the first heat exchanger, the second heat exchanger being thermally coupled to the power electronics assembly.

2. The propulsion system according to claim 1, characterized in that The thermal management system flow path includes a splitter located downstream of the first heat exchanger, the splitter splitting the fluid flow into a first portion of the fluid flow and a second portion of the fluid flow, the splitter transferring the first portion of the fluid flow to the second heat exchanger, and wherein at least the second portion of the fluid flow flows to the motor.

3. The propulsion system according to claim 2, characterized in that wherein the first portion is equal to or smaller than the second portion.

4. The propulsion system according to claim 2, characterized in that Wherein the thermal management system flow path includes a flow coupler positioned downstream of the power electronics assembly, the flow coupler combining the first portion of the fluid flow with the second portion of the fluid flow.

5. The propulsion system according to claim 1, characterized in that The thermal management system flow path includes a flow control device that regulates the fluid flow to the second heat exchanger.

6. The propulsion system according to claim 1, characterized in that The motor includes one or more of a fluid tank, a fluid pump, or a fluid filter.

7. The propulsion system according to claim 1, characterized in that Wherein the first heat exchanger comprises an air-cooled heat exchanger.

8. The propulsion system according to claim 1, characterized in that Wherein the second heat exchanger comprises a fuel cooling heat exchanger.

9. The propulsion system according to claim 1, characterized in that The fluid comprises at least one of oil, carbon dioxide, nitrogen, helium or xenon.

10. The propulsion system according to claim 1, wherein: Wherein the fluid comprises oil, and wherein the first heat exchanger comprises an air-cooled oil cooler, and wherein the second heat exchanger comprises a fuel-cooled oil cooler.

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