Power switching system for anti-icing system for use with main power source and auxiliary power source

Abstract

The power switching system may include a primary power source for powering an electrical device, such as an electric heater for ice protection, during operation of the aircraft. During the nominal mode of operation, a subset of the electrical devices may operate sufficiently based on the primary power supply. The power switching system may also include an auxiliary power source to supplement the primary power source for critical operating phases (e.g., during takeoff, landing, or flying into known icing conditions). The auxiliary power source may include a battery or supercapacitor for enhancing the power provided by the main power source. When an auxiliary mode of operation is required (e.g., during critical phases of flight), the power of the auxiliary power source may be used to boost the main power source in order to power all electrical devices.

Description

Technical Field

[0001] The present invention relates to a power switching system, and more particularly to a power switching system having a main power source and an auxiliary power source. Background Art

[0002] A gas turbine engine generally includes a turbine and a rotor assembly. A gas turbine engine (such as a turbofan engine) can be used for aircraft propulsion and may be affected by icing conditions during flight. In the presence of icing conditions, icing may occur on various components of the gas turbine engine, such as but not limited to the fan blades of an open rotor driven by the gas turbine engine. It is desirable to prevent icing to maintain engine operating margins and performance. A main power source can be used to provide some power to an anti-icing system. Improvements to the anti-icing system would be useful in the art. Brief Description of the Drawings

[0003] A complete and enabling disclosure of the present disclosure, including its best mode, is set forth in the specification with reference to the accompanying drawings, in which:

[0004] Figure 1 is a cross-sectional view of a gas turbine engine for providing propulsion power to an aircraft according to an exemplary aspect of the present disclosure.

[0005] Figure 2 is a schematic diagram of a power switching system according to another exemplary aspect of the present disclosure.

[0006] Figure 3 is a schematic diagram of a power switching system activated to provide power to a subset of electrical devices according to another exemplary aspect of the present disclosure.

[0007] Figure 4 is a schematic diagram of a power switching system activated to provide power to all electrical devices according to another exemplary aspect of the present disclosure.

[0008] Figure 5 is a schematic diagram of an input provided to a power controller according to another exemplary aspect of the present disclosure.

[0009] Figure 6 is a schematic diagram of a power switching system having a power controller and at least one switch according to another exemplary aspect of the present disclosure.

[0010] Figure 7 is a schematic diagram of a power switching system having a power controller according to another exemplary aspect of the present disclosure.

[0011] Figure 8 is a schematic diagram of a power switching system in a nominal operating mode according to another exemplary aspect of the present disclosure.

[0012] Figure 9 It is a schematic diagram of a power switching system in a nominal operation mode according to another exemplary aspect of the present disclosure.

[0013] Figure 10 It is a schematic diagram of a power switching system in a nominal operation mode according to another exemplary aspect of the present disclosure.

[0014] Figure 11 It is a schematic diagram of a power switching system in an auxiliary operation mode according to another exemplary aspect of the present disclosure.

[0015] Figure 12 It is a schematic diagram of another embodiment of a power switching system with a power controller according to another exemplary aspect of the present disclosure.

[0016] Figure 13 It is a schematic diagram of another embodiment of a power switching system in a nominal operation mode according to another exemplary aspect of the present disclosure.

[0017] Figure 14 It is a schematic diagram of another embodiment of a power switching system in a nominal operation mode according to another exemplary aspect of the present disclosure.

[0018] Figure 15 It is a schematic diagram of another embodiment of a power switching system in a nominal operation mode according to another exemplary aspect of the present disclosure.

[0019] Figure 16 It is a schematic diagram of another embodiment of a power switching system in an auxiliary operation mode according to another exemplary aspect of the present disclosure.

[0020] Figure 17 It is a logical flow of an embodiment of a power switching system according to another exemplary aspect of the present disclosure.

[0021] Figure 18 It is a schematic diagram of a computing device according to another exemplary aspect of the present disclosure.

[0022] Figure 19 It is a flowchart describing a method of switching a power supply according to the present disclosure. Detailed Description

[0023] Reference will now be made in detail to the current embodiments of the present disclosure, one or more examples of which are shown in the accompanying drawings. The detailed description uses numerical and alphabetical identifiers to refer to features in the drawings. Identical or similar identifiers in the drawings and the description have been used to refer to identical or similar parts of the present disclosure.

[0024] As used herein, the term "exemplary" means "serving as an example, instance, or illustration". Any embodiment described herein as "exemplary" is not necessarily to be construed as superior or better than other embodiments. Further, unless otherwise expressly specified, all examples described herein are to be considered exemplary.

[0025] Unless the context clearly dictates otherwise, the singular forms "a", "an", and "the" include plural referents.

[0026] For example, the term "at least one" in the context of "at least one of A, B, and C" refers to A alone, B alone, C alone, or any combination of A, B, and C.

[0027] The term "turbine" refers to a machine that includes one or more compressors, a heat addition section (e.g., a combustion section), and one or more turbines that together produce a torque output.

[0028] The term "gas turbine engine" refers to an engine that has a turbine as all or part of its power source. Exemplary gas turbine engines include turbofan engines, turboprop engines, turbojet engines, turboshaft engines, etc., as well as hybrid electric versions of one or more of these engines.

[0029] The term "combustion section" refers to any heat addition system of a turbine. For example, the term combustion section can refer to a section that includes one or more of a deflagration combustion assembly, a rotating detonation combustion assembly, a pulse detonation combustion assembly, or other suitable heat addition assemblies. In certain example embodiments, the combustion section can include an annular combustor, a can combustor, a tubo combustor, a trapped vortex combustor (TVC), or other suitable combustion systems, or combinations thereof.

[0030] The terms "axial" and "axially" refer to a direction and orientation that extends generally parallel to a reference axis. Further, the terms "radial" and "radially" refer to a direction and orientation that extends generally perpendicular to the reference axis. Further, as used herein, the terms "circumferential" and "circumferentially" refer to a direction and orientation that extends arcuately about the reference axis.

[0031] Unless otherwise specified herein, the terms "coupled", "fixed", "attached", etc. refer to both direct coupling, fixing, or attaching and indirect coupling, fixing, or attaching through one or more intermediate components or features.

[0032] As used herein, the terms "first", "second", and "third" may be used interchangeably to distinguish one component from another and are not intended to denote the position or importance of the individual components.

[0033] As used herein, the "third stream" refers to a non-primary air stream that can increase the energy of the fluid to generate a fraction of the thrust of the overall propulsion system. The third stream can typically receive inlet air (air from a duct passage downstream of the primary fan) rather than free stream air (such as the primary fan). The pressure ratio of the third stream can be higher than the pressure ratio of the primary propulsion stream (e.g., the bypass or propeller-driven propulsion stream). The thrust can be generated by a dedicated nozzle or by mixing the air stream passing through the third stream with the primary propulsion stream or the core air stream (e.g., entering a common nozzle).

[0034] As used throughout the specification and claims, the approximating language is used to modify any quantitative representation that can vary without resulting in a change in the basic function associated therewith. Accordingly, a value modified by one or more terms (e.g., "about", "approximately", and "substantially") is not limited to the specified exact value. In at least some instances, the approximating language can correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct or manufacture the component and / or system. For example, the approximating language can refer to a range within 1%, 2%, 4%, 10%, 15%, or 20%. These approximating ranges can apply to a single value, either or both endpoints defining a numerical range, and / or ranges of ranges between the endpoints.

[0035] As will be discussed in more detail below, the subject matter of the present disclosure generally relates to an electrical switching system that can be used to provide full power to an electrical device (e.g., an electric heater for anti-icing) to supplement the main power supply. The electrical switching system can also include an auxiliary power supply, such as a battery or a supercapacitor, that enhances the power provided from the main power supply. During the nominal operating mode, a subset of the electrical devices can operate adequately based on the main power supply. The electrical switching system can alternately provide power to a first subset of the electrical devices at a first time while inhibiting power to a second subset of the electrical devices, and then provide power to the second subset of the electrical devices at a second time while inhibiting power to the first subset of the electrical devices. When an auxiliary operating mode is required, such as during critical phases of flight (e.g., takeoff, landing, flying into known icing conditions, etc.), the power from the auxiliary power supply can be used to enhance the main power supply in order to power all of the electrical devices.

[0036] Now referring Figure 1 , in accordance with an exemplary embodiment of the present disclosure, a schematic cross-sectional view of a gas turbine engine 100 is provided. Specifically, Figure 1 a turbofan engine having a rotor assembly with a single stage of ducted fan blades is provided. In this way, the rotor assembly can be referred to herein as a "ducted fan", or the entire gas turbine engine 100 can be referred to as a "ducted turbofan engine". Additionally, Figure 1The gas turbine engine 100 includes a third flow extending from the compressor section to the flow path of the rotor assembly on the turbine, as will be explained in more detail below.

[0037] Although Figure 1 the embodiments shown are of a ducted turbofan engine, it should be understood that other types of gas turbine engines are contemplated for the following discussion. For example, it should be understood that turbojet engines, ducted turbofan engines, turboprop engines, gas turbine engines with centrifugal compressors, etc. are all contemplated for use with the various embodiments of the inlet guide vanes described herein. Unless otherwise required, the type of gas turbine engine applicable to the inlet guide vanes described herein is not limited.

[0038] For reference, the gas turbine engine 100 defines an axial direction A, a radial direction R, and a circumferential direction C. In addition, the gas turbine engine 100 defines an axial centerline or longitudinal axis 112 extending along the axial direction A. Generally, the axial direction A extends parallel to the longitudinal axis 112, the radial direction R extends outwardly from the longitudinal axis 112 and inwardly to the longitudinal axis 112 in a direction orthogonal to the axial direction A, and the circumferential direction extends 360 degrees (360°) around the longitudinal axis 112. The gas turbine engine 100 extends between a front end 114 and a rear end 116, for example, along the axial direction A.

[0039] The gas turbine engine 100 includes a turbine 120 and a rotor assembly (also referred to as a fan section 150) located upstream thereof. Generally, the turbine 120 includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order. Specifically, as Figure 1 shown, the turbine 120 includes a core cowl 122 that defines an annular core inlet 124. The core cowl 122 also at least partially surrounds a low-pressure system and a high-pressure system. For example, the shown core cowl 122 at least partially surrounds and supports a booster or low-pressure (“LP”) compressor 126 for pressurizing air entering the turbine 120 through the core inlet 124. A high-pressure (“HP”), multi-stage, axial-flow compressor (referred to herein as the HP compressor 128) receives the pressurized air from the LP compressor 126 and further increases the pressure of the air. The pressurized air flows downstream to the burner 130 in the combustion section, where fuel is injected into the pressurized air stream and ignited to increase the temperature and energy level of the pressurized air.

[0040] It should be understood that, as used herein, the terms “high / low speed” and “high / low pressure” may be used interchangeably with respect to the high-pressure / high-speed system and the low-pressure / low-speed system. In addition, it should be understood that the terms “high” and “low” are used in the same context to distinguish between the two systems and do not imply any absolute speed and / or pressure values.

[0041] The high-energy combustion products flow downstream from the combustor 130 to the high-pressure turbine 132. The HP turbine 132 drives the HP compressor 128 via the high-pressure shaft 136. In this regard, the HP turbine 132 drives the HP compressor 128. The high-energy combustion products then flow to the low-pressure turbine 134. The LP turbine 134 drives the LP compressor 126 and the components of the fan section 150 via the low-pressure shaft 138. In this regard, the LP turbine 134 drives the LP compressor 126 and the components of the fan section 150. In this exemplary embodiment, the LP shaft 138 is coaxial with the HP shaft 136. After driving each of the HP turbine 132 and the LP turbine 134, the combustion products leave the turbine 120 through the turbine exhaust nozzle 140.

[0042] Thus, the turbine 120 defines a working gas flow path or core duct 142 that extends between the core inlet 124 and the turbine exhaust nozzle 140. The core duct 142 is an annular duct that is generally located inside the core shroud 122 in the radial direction R. The core duct 142 (e.g., the working gas flow path through the turbine 120) may be referred to as the second flow.

[0043] The fan section 150 includes a fan 152, which is the primary fan in the present exemplary embodiment. For Figure 1 the illustrated embodiment, the fan 152 is an open rotor or ducted fan 152. Thus, the gas turbine engine 100 may be referred to as an open rotor or open fan engine. In one form, the gas turbine engine 100 can be used as a prime mover for an aircraft 161 to provide propulsion power for the aircraft 161. Thus, the gas turbine engine 100 can be used to power a propeller or, in another embodiment, a helicopter rotor.

[0044] As shown, the fan 152 includes an array of fan blades 154 ( Figure 1 only one is shown). The fan blades 154 are rotatable, e.g., about the longitudinal axis 112. As described above, the fan 152 is driven by the low-pressure turbine 134 via the LP shaft 138. For Figure 1 the illustrated embodiment, the fan 152 is coupled to the LP shaft 138 via a reduction gearbox 155, e.g., in an indirect drive or gear drive configuration.

[0045] In addition, the array of fan blades 154 can be equally spaced about the longitudinal axis 112. Each fan blade 154 has a root and a tip and a span defined therebetween, more specifically, a tip radius R along the radial direction R that defines the distance from the longitudinal axis 112 to the tip of the fan blade 154 TIP。Each fan blade 154 defines a central blade axis 156. For this embodiment, each fan blade 154 of the fan 152 is rotatable about its central blade axis 156, e.g., in unison with one another. One or more actuators 158 are provided to facilitate such rotation and can thus be used to vary the pitch of the fan blades 154 about their respective central blade axes 156.

[0046] The fan section 150 also includes an array of outlet guide vanes 162 that includes outlet guide vanes 162 disposed about the longitudinal axis 112 ( Figure 1 only one is shown; sometimes also referred to as fan guide vanes). For this embodiment, the outlet guide vanes 162 are not rotatable about the longitudinal axis 112. Each outlet guide vane 162 has a root and a tip and a span defined therebetween. The outlet guide vanes 162 may be Figure 1 shown unshrouded, or alternatively, may be shrouded, e.g., by an annular shroud spaced radially outward from the tip of the outlet guide vanes 162 or an annular shroud attached to the outlet guide vanes 162.

[0047] It will be appreciated that the outlet guide vanes 162 each define an outlet guide vane (OGV) span 164 along the radial direction R from the root to the tip. Additionally, the outlet guide vanes 162 are spaced a distance or gap 166 from the fan blades 154 in the axial direction A. The gap 166 is measured in the axial direction A from the trailing edge of the fan blades 154 to the leading edge of the outlet guide vanes 162.

[0048] In the illustrated embodiment, as described above, each outlet guide vane 162 is configured as a fixed vane and cannot pitch about the central blade axis of the outlet guide vane 162. Accordingly, the outlet guide vanes 162 are mounted to the fan shroud 170 in a fixed manner.

[0049] However, it should be understood that in other embodiments, the outlet guide vanes 162 may alternatively be variable pitch outlet guide vanes 162.

[0050] As Figure 1As shown, in addition to the ducted fan 152, a ducted fan 184 is also included behind the fan 152, such that the gas turbine engine 100 includes a ducted fan and a ductedless fan, both of which are used to generate thrust through air movement without passing through at least a portion of the turbine 120 (e.g., for the illustrated embodiment, without passing through the HP compressor 128 and the combustion section). The ducted fan 184 can rotate about the same axis as the fan blades 154 (e.g., the longitudinal axis 112). For the illustrated embodiment, the ducted fan 184 is driven by the low-pressure turbine 134 (e.g., coupled to the LP shaft 138). In the illustrated embodiment, as described above, the fan 152 can be referred to as the primary fan, and the ducted fan 184 can be referred to as the secondary fan. It should be understood that the terms "primary" and "secondary" are for convenience only and do not imply any special importance, power, etc.

[0051] The ducted fan 184 includes a plurality of fan blades ( Figure 1 not individually labeled in the figure), and these fan blades are arranged in a single stage, so the ducted fan 184 can be referred to as a single-stage fan. The fan blades of the ducted fan 184 can be equally spaced around the longitudinal axis 112. Each blade of the ducted fan 184 has a root and a tip and a span defined therebetween.

[0052] The fan cowl 170 annularly surrounds at least a portion of the core cowl 122 and is generally located radially outward of at least a portion of the core cowl 122 in the radial direction R. Specifically, the downstream section of the fan cowl 170 extends over the front portion of the core cowl 122 to define a fan duct flow path, or simply referred to as the fan duct 172. According to this embodiment, the fan flow path or the fan duct 172 can be understood as forming at least a portion of the third flow of the gas turbine engine 100.

[0053] The incoming air can enter through the fan duct inlet 176 and pass through the fan duct 172 and can be discharged through the fan exhaust nozzle 178 to generate propulsion thrust. The fan duct 172 is an annular duct that is generally located radially outward of the core duct 142 in the radial direction R. The fan cowl 170 and the core cowl 122 are connected together and are supported by a plurality of generally radially extending and circumferentially spaced stationary struts 174 ( Figure 1Only one support is shown. The stationary struts 174 may each have an aerodynamic profile to direct air flowing through the fan duct 172. In addition to the stationary struts 174, other struts may be used to connect and support the fan cowl 170 and / or the core cowl 122. In many embodiments, the fan duct 172 and the core duct 142 may at least partially co - extend (substantially axially) on opposite sides (e.g., opposite radial sides) of the core cowl 122. For example, the fan duct 172 and the core duct 142 may each extend directly from the leading edge 144 of the core cowl 122 and may partially co - extend substantially axially on opposite radial sides of the core cowl 122.

[0054] The gas turbine engine 100 also defines or includes an inlet duct 180. The inlet duct 180 extends between the engine inlet 182 and the core inlet 124 / fan duct inlet 176. The engine inlet 182 is generally defined at the front end of the fan cowl 170 and is located axially along the axial direction A between the fan 152 and the exit guide vane array 160. The inlet duct 180 is an annular duct that forms an annular flow path 171. The annular flow path 171 is located radially inward of the fan cowl 170. The annular flow path 171 includes an inner flow surface 173 and an outer flow surface 175, where the inner flow surface 173 is radially inward from the outer flow surface 175 such that the inner flow surface 173 is on the axial side of the annular flow path 171 (e.g., the inner flow surface 173 is closer to the LP axis 138 than the outer flow surface 175). Air flowing downstream along the inlet duct 180 is split by the fan duct splitter or the leading edge 144 of the core cowl 122 into the core duct 142 and the fan duct 172, but not necessarily evenly. In the illustrated embodiment, the inlet duct 180 is wider than the core duct 142 in the radial direction R. The inlet duct 180 is also wider than the fan duct 172 in the radial direction R.

[0055] It is noted that for the illustrated embodiment, the gas turbine engine 100 includes one or more features to increase the third - flow thrust Fn 3SEfficiency (e.g., the thrust generated by the airflow through the fan duct 172 that exits through the fan exhaust nozzle 178, at least in part generated by the ducted fan 184). Specifically, the gas turbine engine 100 further includes an array of inlet guide vanes 186 located in the inlet duct 180, upstream of the ducted fan 184 and downstream of the engine inlet 182. As will be appreciated, the inlet guide vanes 186 can be used to maintain the operability of the compressor. The array of inlet guide vanes 186 is arranged about the longitudinal axis 112. For this embodiment, the inlet guide vanes 186 cannot rotate about the longitudinal axis 112. Each inlet guide vane 186 defines a central vane axis (not labeled for clarity) and can rotate about its respective central vane axis, e.g., in unison with each other. In this way, the inlet guide vanes 186 can be considered variable geometry components. One or more actuators 188 are provided to facilitate such rotation and can thus be used to change the pitch of the inlet guide vanes 186 about their respective central vane axes. However, in other embodiments, each inlet guide vane 186 can be fixed or non-pitchable about its central vane axis.

[0056] In addition, the gas turbine engine 100 includes an array of outlet guide vanes 190 located downstream of the ducted fan 184 and upstream of the fan duct inlet 176. Like the array of inlet guide vanes 186, the array of outlet guide vanes 190 cannot rotate about the longitudinal axis 112. However, for the illustrated embodiment, unlike the array of inlet guide vanes 186, the array of outlet guide vanes 190 is configured as fixed pitch outlet guide vanes.

[0057] In addition, it should be understood that for the illustrated embodiment, the fan exhaust nozzle 178 of the fan duct 172 is also configured as a variable geometry exhaust nozzle. In this way, the gas turbine engine 100 includes one or more actuators 192 for adjusting the variable geometry exhaust nozzle. For example, the variable geometry exhaust nozzle can be configured to change the total cross-sectional area (e.g., the area of the nozzle in a plane perpendicular to the longitudinal axis 112) 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 172). A fixed geometry exhaust nozzle can also be employed.

[0058] The combination of the array of inlet guide vanes 186 upstream of the ducted fan 184, the array of outlet guide vanes 190 downstream of the ducted fan 184, and the fan exhaust nozzle 178 can more effectively generate a third flow thrust Fn under one or more engine operating conditions 3SIn addition, by introducing changes to the geometries of the inlet guide vanes 186 and the fan exhaust nozzle 178, the gas turbine engine 100 is capable of generating a more efficient third stream thrust Fn over a relatively wide range of engine operating conditions 3S , including takeoff and climb (where typically the maximum total engine thrust Fn is required Total ) and cruise (where typically a lesser amount of total engine thrust Fn is required Total ).

[0059] In addition, still referring to Figure 1 , in the exemplary embodiment, the air passing through the fan duct 172 may be relatively cooler (e.g., at a lower temperature) than one or more of the fluids used in the turbine 120. Thus, one or more heat exchangers 198 may be positioned in thermal communication with the fan duct 172. For example, one or more heat exchangers 198 may be disposed within the fan duct 172 and used to cool one or more fluids from the core engine, where the air passes through the fan duct 172 as a source for removing heat from the fluid (e.g., compressor bleed air, oil, or fuel).

[0060] Although not shown, the heat exchanger 198 may be an annular heat exchanger that extends substantially 360 degrees (e.g., at least 300 degrees, e.g., at least 330 degrees) within the fan duct 172. In this way, the heat exchanger 198 can effectively utilize the air passing through the fan duct 172 to cool one or more systems of the gas turbine engine 100 (e.g., the lubricating oil system, compressor bleed air, electrical components, etc.). The heat exchanger 198 uses the air passing through the fan duct 172 as a heat sink and accordingly raises the temperature of the air downstream of the heat exchanger 198 and exiting the fan exhaust nozzle 178.

[0061] It should be understood that for the purposes of the discussion of the present disclosure, the ducted fan 184, the fan cowl 170, the inlet duct 180, and the fan duct 172 may all be considered part of the turbine 120.

[0062] It should be understood that Figure 1 the exemplary gas turbine engine 100 shown in

[0063] The gas turbine engine 100 also includes an engine controller 200 for regulating the operation of one or more aspects of the gas turbine engine 100, such as delivering fuel to the combustor 130, operating the actuator 158 to rotate the fan blades 154 of the fan 152 about their central blade axis 156, and the like. The engine controller 200 may communicate with an aircraft controller or any other type of controller for receiving data and / or operating any system associated with the aircraft 161 (e.g., control surface actuators, landing gear position, etc.).

[0064] The gas turbine engine 100 includes an electrical device 202 in the form of a heating element for preventing, mitigating, or minimizing ice formation on the fan blades 154 and the outlet guide vanes 162. As described above, the electrical device 202 may also be used in other embodiments to prevent, mitigate, or minimize ice formation on a propeller, or helicopter rotor, compressor blades, and the like. Thus, the electrical device 202 can be used to remove ice from a plurality of air moving blades, whether the air moving blades are the fan blades 154, or the blades of a propeller or helicopter rotor. In some forms, the electrical device can be more generally used on any aircraft surface where ice may accumulate, not just air moving blades. Thus, the electrical device 202 can be used to prevent, mitigate, or minimize ice formation on an aircraft surface, where the aircraft may include a fixed wing aircraft, a rotary wing aircraft (e.g., a helicopter), a glider, an airship, and the like. Although for convenience the following disclosure will focus on anti-icing in an aviation environment, it should be recognized that the disclosure is equally applicable to non-aviation related applications, including wind turbine blades or other systems that require anti-icing. Additionally, although the present disclosure is directed to an electrical system for preventing, mitigating, or minimizing ice formation on the fan blades 154 and / or the outlet guide vanes 162, it should be recognized that other aircraft surfaces may also be protected using an electrical switching system. For example, the present disclosure can be applied to helicopter rotor blades, aircraft cabin entrances or boosters, heat exchangers, aircraft wings, aircraft tails, control surfaces, and / or antennas.

[0065] The electrical device 202 may include one or more heating elements and any associated electronics, such as a power converter required to operate the heating element. Thus, the electrical device 202 may include a heating element (or any other useful device that receives electrical energy to produce a useful result, such as a fluid valve and / or pump for flowing and / or pumping an anti-icing fluid (such as ethylene glycol), or a pneumatic valve and / or pneumatic pump for pressurizing and / or pumping a fluid (such as air) to actuate a pneumatic de-icing boot) and any potential auxiliary components, such as circuitry that aids in converting electrical energy into a useful result. In some embodiments, the electrical device 202 includes only devices that receive electrical energy to produce a useful result (e.g., an electric heater for thermal de-icing (e.g., the electric heater adds heat to a surface to prevent ice formation and / or cause ice shedding by melting), an ethylene glycol valve and / or pump for pumping an anti-icing fluid (e.g., the ethylene glycol seeps through holes formed in a surface of an aircraft surface to prevent ice formation), a pneumatic valve and / or pump for pressure-actuating a de-icing boot (e.g., temporarily changing the geometry of the de-icing boot to break ice formed on an aircraft surface)). Figure 1 The electrical device 202 is depicted schematically at each of the fan blades 154 and the outlet guide vanes 162, but it will be understood that one or more portions of the electrical device 202 may be located elsewhere. For example, the heating element may be located at the fan blades 154 and the outlet guide vanes 162, while any associated circuitry may be located elsewhere but is otherwise in electrical communication with the heating element. The gas turbine engine 100 may include a plurality of fan blades 154 and outlet guide vanes 162, each of the fan blades 154 and the outlet guide vanes 162 including one or more electrical devices 202 for preventing icing. In some applications, only the fan blades 154 or only the outlet guide vanes 162 may include the electrical device 202.

[0066] The power controller 204 may be used to regulate the operation of the electrical device 202 by delivering power to the electrical device 202. For example, the power controller 204 may be used to deliver power to a circuit connected to a heater of the electrical device 202, or, in the case where the electrical device 202 includes only a heater and no associated circuitry, may be used to deliver power directly to the heater. Embodiments of the power controller 204 and the electrical device 202 will be described further below.

[0067] Now turning to Figure 2, a configuration of a ductless fan 152 is shown in the figure, which includes four fan blades 154a - 154d. It can be understood that in other embodiments, there may be more or fewer fan blades 154. Several heater circuits (e.g., HC1 206a, HC2 206b, HC3 206c, and HC4 206d) are shown in the figure in electrical communication with heating elements 208a - 208d. The electrical device 202 includes heater circuits 206a - 206d and heating elements 208a - 208d. Each heating element 208a - 208d is shown in the figure as being associated with each heater circuit 206a - 206d. However, other embodiments may include a smaller number of heater circuits 206 relative to the number of heating elements 208. For example, in some applications, two or more heating elements 208 may be driven by a single heater circuit 206.

[0068] The heating elements 208 receive power from one or both of the main power supply 210 and the auxiliary power supply 212 through the action of the power controller 204. The main power supply 210 may take various forms, including a generator driven by the gas turbine engine 100. For example, in such an embodiment, the generator may be directly driven by the shaft of the gas turbine engine, such as through the power output of a low - voltage shaft. The auxiliary power supply 212 may also take various forms, including any suitable energy storage device, such as a battery, a supercapacitor, etc.

[0069] The power controller 204 is configured to receive power from either or both of the main power supply 210 and the auxiliary power supply 212 and deliver the power to one or more electrical devices 202 to power the electrical devices 202. The power controller 204 is configured to deliver power directly to the electrical devices 202 and, in some embodiments (such as the above - mentioned embodiments), can be used to convert the power before delivering it to one or more electrical devices 202.

[0070] Figure 2 The embodiment of the power controller 204 shown in the figure includes one or more switches 214 for directing and / or redirecting power from one or both of the main power supply 210 and the auxiliary power supply 212 to one or more electrical devices 202. The one or more switches 214 may take various forms depending on the application. For example, within certain voltage and current ranges, the switch 214 may take the form of a relay, such as but not limited to an electromechanical relay, a solid - state relay, a hybrid relay, a reed relay, etc. Other types of switches may also be considered. Although the power controller 204 is depicted in the shown embodiment as including the switch 214, in other embodiments, the power controller 204 may include additional circuits, such as but not limited to a power converter (e.g., a power converter for driving the heating elements of the electrical device 202).

[0071] The power controller 204 may further include a microcontroller 216 for operating one or more switches 214. The microcontroller 216 may be any device suitable for operating the switch 214 based on the input 218. The microcontroller 216 may be a computing device, such as an integrated circuit, for receiving the input 218 and adjusting the configuration of one or more switches 214 to any given position. In some forms, the microcontroller 216 may be replaced by any device suitable for receiving the input 218 and adjusting the switch 214. The input 218 may be a command received from a user (such as a pilot), which may be used by the power controller 204 to adjust the configuration of the switch 214 to any given position, or may be a command received from another controller, which may be used by the power controller 204 to adjust the configuration of the switch 214 to any given position, or may be data, which may be used by the power controller 204 to adjust the configuration of the switch 214 to any given position. Figure 5 Further examples of inputs that may be used by the power controller 204 to adjust the configuration of the switch 214 to any given position are provided.

[0072] Figure 3 A configuration is shown in which the power controller 204 has adjusted the configuration of the switch 214 such that the heater circuit 206a and the heating element 208a are powered, and the heater circuit 206c and the heating element 208c are powered. The fan blades 154a and 154c are shaded in the figure to indicate that these fan blades are receiving electrically generated heat. The power controller 204 has adjusted the configuration of the switch 214 such that the heater circuit 206b and the heating element 208b are not powered, and the heater circuit 206d and the heating element 208d are not powered. The fan blades 154b and 154d are not shaded in the figure to indicate that these fan blades are not receiving electrically generated heat.

[0073] As shown in the figure, in Figure 3 the example shown, the auxiliary power supply 212 is not used. Figure 3The power controller 204 therein is configured to alternately heat the fan blades 154 between the heating elements 208a and 208c and the heating elements 208b and 208d. Operating a heating device on a propeller by alternating between different heating elements has been used in prior art devices. In the present disclosure, the alternation can be driven by constraints imposed on how much power can be drawn from the main power supply 210 and / or how much power can be provided by the power controller 204 to be powered solely from the main power supply 210. The constraints can be related to the maximum current of one or more components associated with the power controller 204, and / or can be related to the operating power budget associated with the main power supply 210, since the main power supply 210 draws mechanical power from the gas turbine engine 100, converts the mechanical power into electrical power, and then delivers the electrical power to the power controller 204 and the electrical devices 202. For example, if the gas turbine engine 100 includes a constraint with an operating power draw budget (e.g., 15 kilowatts (KW)), in an embodiment where 30 KW of power delivery is required to operate all the electrical devices 202 simultaneously, such a constraint would prohibit the power controller 204 from operating all the electrical devices 202 simultaneously. Higher constraints for powering subsets of the electrical devices 202 are also envisioned, including but not limited to 50 KW, 75 KW, 100 KW, and 125 KW, to name just a few non - limiting examples. Thus, the power controller 204 can be configured to alternately energize one or more of the electrical devices 202. In Figure 3 the illustrated embodiment, the power controller 204 is configured to alternately energize the heater circuits 206a and 206c by the main power supply 210 at a first time and then switch to energizing the heater circuits 206b and 206d by the main power supply 210 at a second time. These times can be regularly spaced, but in other embodiments, can be driven by operating requirements that vary the regular spacing.

[0074] From the above discussion, it can be understood that the power controller 204 can be configured to alternately energize subsets of the electrical devices 202. The power controller 204 can be configured to prohibit power supply to one subset of the electrical devices 202 while delivering power to another subset of the electrical devices 202. The power controller 204 can be configured to prohibit power transmission through various techniques, including programming techniques such as regulating the electrical devices 202 based on the controller (e.g., via the microcontroller 216), and / or mechanical interlocks between the switches 214 for mechanically connecting one subset of the electrical devices 202 while disconnecting another subset of the electrical devices 202 through mechanical interlocks.

[0075] The illustrated embodiment depicts a total of four fan blades 154, which causes a first subset of the electrical devices to be powered by the main power supply 210 at a first time and a second subset of the electrical devices to be powered by the main power supply 210 at a second time. Since the present disclosure is applicable to any number of fan blades, the alternating subsets can include any number of electrical devices. For example, in one embodiment, each of the first subset of electrical devices and the second subset of electrical devices can include a single heating element 208, or can include more than one heating element 208. Additionally, some embodiments can include a different number of heating elements 208 between each of the two subsets of the electrical devices 202. Further, more than two subsets of the electrical devices 202 are contemplated in some embodiments.

[0076] Turning now to Figure 4 , the main power supply 210 and the auxiliary power supply 212 are used together such that excitation power can be provided to all of the heating elements 208 simultaneously. The operation of the power controller 204 to alternately or simultaneously power each subset of the electrical devices between when each subset of the electrical devices is powered and when each subset is not powered can be based on the input 218 and, in embodiments having a controller such as the microcontroller 216, based on the microcontroller 216's interpretation of the input. The power controller 204 can be configured to, in one embodiment, place the main power supply 210 and the auxiliary power supply 212 in a series power relationship to provide sufficient power to drive all of the electrical devices 202 simultaneously, while in other embodiments, the power controller 204 can be configured to place the main power supply 210 in electrical communication with one subset of the electrical devices 202 and the auxiliary power supply 212 in separate electrical communication with another subset of the electrical devices 202. In embodiments where each of the main power supply 210 and the auxiliary power supply 212 is in separate electrical communication with a different subset of the electrical devices 202, the power controller 204 can continue the Figure 3 alternating pattern described above, where each of the main power supply 210 and the auxiliary power supply 212 switches back and forth between subsets of the electrical devices 202. In another embodiment, where each of the main power supply 210 and the auxiliary power supply 212 is in separate electrical communication with a different subset of the electrical devices 202, the Figure 3 pattern described above can stop, and the main power supply 210 can provide power to one subset of the electrical devices 202 through the power controller 204 and the auxiliary power supply 212 can provide power to another subset of the electrical devices 202 through the power controller 204 until the input 218 indicates a return to the Figure 3 alternating pattern.

[0077] Figure 5An embodiment is shown in which the engine controller 200 sends an input 218 to the power controller 204. In other embodiments, the input 218 may be provided directly by a user or may originate from another controller or computing device. For example, in alternative and / or additional forms, the power controller 204 may receive the input 218 via a data bus. Figure 5 The input 218 shown in Figure 5 is an operating condition input that may include one or more different data values. Figure 5 The operating condition input shown in Figure 5 has several different data values, but it is understood that fewer data values are also contemplated in some embodiments. The operating condition input may include a user command, such as a user command that may be sensed from a button or lever activated by a pilot. The operating condition input may alternatively and / or additionally include a controller command generated from another controller. For example, the engine controller 200 may determine that the power switching system should transition from operating in accordance with the Figure 3 alternating excitation embodiment shown in Figure 3 to the Figure 4 fully excited embodiment shown in Figure 4 , in which case the engine controller 200 may generate a command and transmit it as part of the operating condition input. The operating condition input may alternatively and / or additionally include operating condition data that may be used by the power controller 204 to determine whether the power switching system should transition from operating in accordance with the Figure 3 alternating excitation embodiment shown in Figure 3 to the Figure 4 fully excited embodiment shown in Figure 4 . The operating condition data may include one or more of the following: data related to whether the aircraft is supported on the ground by its landing gear (so-called "weight on wheels" indication), landing gear lever position related to a pilot command to deploy or retract the landing gear, and an indication of the degree of requested or delivered power or the power level affected by an auxiliary engine system. For example, the power level may include any one of a power lever angle (e.g., the position angle of the throttle in the cockpit), throttle position (e.g., for a piston-driven internal combustion engine powerplant), propeller pitch setting, or fuel / air mixture setting (e.g., sensed and / or commanded by the engine controller 200). The operating condition data may also include sensor data from an ice detection sensor configured to determine the presence of ice. The data from the ice detection sensor may include a binary value (0 indicating insufficient ice and 1 indicating ice sufficient to trigger the system) or a value that may be compared to a threshold. The operating condition data may also include ambient temperature or a system fault detection flag / data. Additionally, the operating condition input may alternatively and / or additionally include any one of ambient temperature, main control switch position, and an indication related to the charge state of the auxiliary power supply 212.

[0078] The power switching system disclosed herein can be used to configure the heating element 208 to prevent icing and when it is desired to ensure that during Figure 3When operating in an alternating configuration without icing, the auxiliary power supply 212 can be used in conjunction with a configuration change of the power controller 204 to supplement power delivery to assist in heating a subset of the heating elements 208 that have not been heated by the main power supply 210. Ensure that during Figure 4 The conditions for operating in the configuration include during critical phases of flight (such as takeoff and landing, and / or flying into known icing conditions). In this case, the pilot can command the power switching system to operate as in Figure 4 an embodiment, and / or the engine controller 200 (or a controller in communication with the engine controller 200 or the power controller 204) can detect the operation during a critical phase of flight and command the power switching system to operate as in Figure 4 that. Detecting the operation during a critical phase of flight (takeoff, landing, flying into known icing conditions, etc.) can be accomplished using any one or more of the operating condition inputs shown in Figure 5 . For example, by evaluating the landing gear lever position in the down position, the power lever angle reduced to flight idle, and the weight on the wheels indicating that the aircraft is still in flight, the power controller 204 can determine the critical phase of flight and thus be configured to operate as in Figure 4 shown. If these three conditions are met, the power controller 204 can be configured as in Figure 4 shown. Similarly, if the landing gear lever position in the down position, the power lever angle reduced to ground idle, and the weight on the wheels indicate that the aircraft is on the ground, the power controller 204 can configure the power switching system to operate according to Figure 3 , or, shut down the system so that no power is delivered to any electrical device 202. Additionally, if the power controller 204 detects that the ambient temperature exceeds a pre-defined operating temperature, the power controller 204 can be configured to prohibit the operation of the electrical device 202. Similarly, if the power controller 204 detects a system fault flag / data, the power controller 204 can be configured to prohibit the operation of the electrical device 202.

[0079] Figure 6 is a schematic diagram of the above embodiment, which includes a first subset 220 of electrical devices and a second subset 222 of electrical devices. The power switching system operates by receiving power from either or both of the main power supply 210 and the auxiliary power supply 212 and delivering power to either or both of the first subset 220 of electrical devices and the second subset 222 of electrical devices. Although Figure 6 the heater circuit 206 is not depicted, it can be understood that in those embodiments where the heater circuit 206 is required, the electrical device 202 includes the heater circuit 206 and the heating element 208. It can also be understood that the heater circuit 206 can be included in the power controller 204. Therefore, Figure 6The schematic diagrams herein are for general description and are not intended to be limiting to all embodiments described herein.

[0080] Now turning to Figures 7 - 11 , which shows further details of the power controller 204, where the main power supply 210 and the auxiliary power supply 212 are arranged in parallel to supply power to either or both of the first subset 220 of electrical devices and the second subset 222 of electrical devices. Figure 6 The switch 214 schematically represented in Figure 3 broadly represents switches 221, 229, and 230, all of which can be regulated by the microcontroller 216. The main selection switch 221 can be used to supply power to the main power supply 210 and the auxiliary power supply 212 in a parallel configuration. Electrical contacts 223 - 228 are used in conjunction with the main selection switch 221 to electrically connect the main power supply 210 and the auxiliary power supply 212 to either or both of the first subset 220 of electrical devices and the second subset 222 of electrical devices. A charging switch 230 is provided, which can contact the charging electrical contact 232 to charge the auxiliary power supply 212. In some embodiments, the auxiliary power supply 212 can be charged when the main power supply 210 is not supplying power to any of the electrical devices 220 and 222. In embodiments where the main power supply is capable of providing excess power beyond what is required to energize the electrical devices as in Figure 3 , the auxiliary power supply 212 can be charged during alternate operations as in Figure 7 . In any of the embodiments herein, the auxiliary power supply 212 can be charged from a ground power unit (GPU) or other external source. For example, the auxiliary power supply 212 can be charged while on the ground before an aircraft takes off. The power controller 204 also includes an auxiliary disconnect switch 229, which can contact the auxiliary electrical contact 231 if auxiliary power needs to be delivered from the auxiliary power supply 212. Figures 8 - 11 The further operation scenarios of the illustrated embodiment will be further described in

[0081] Figure 8 shows an operation scenario where the power switching system is in the off state such that neither the first subset 220 of electrical devices nor the second subset 222 of electrical devices is supplied with power. The switch 221 is moved via the microcontroller 216 to a position contacting the electrical contact 223, which is the zero electrical contact. Neither the main power supply 210 nor the auxiliary power supply 212 is transmitting power. Although the power switching system is in the off state, the power switching system is operating in a mode where the auxiliary power supply 212 is being charged, which can be seen by the charging switch 230 being moved to a position contacting the charging electrical contact 232. In this configuration, the main power supply 210 supplies power to the auxiliary power supply 212. Figure 8 The power switching system shown in

[0082] Figure 9 depicts a power switching system in an on state, where main power from the main power supply 210 is delivered to a first subset 220 of electrical devices. As discussed elsewhere herein, the switch 221 can be controlled by the microcontroller 216 to alternate between the electrical contact 224 and the electrical contact 226. The auxiliary power supply 212 is not charged through the position of the charging switch 230 and does not provide auxiliary power through the position of the auxiliary disconnect switch 229. Figure 8 The power switching system depicted in is in a nominal mode - power supply state, which means that at least one electrical device 202 is receiving power via contact with either the electrical contact 224 or the electrical contact 226. The configuration of the electrical contacts 224 and 226 relative to the switch 221 provides the power controller 204 with the ability to inhibit the supply of power to one subset of electrical devices while another subset of electrical devices is receiving power.

[0083] Figure 9 Also depicted is a timer 234 for providing a timer output 236. The timer 234 can be executed by the microcontroller 216 and is set inside the microcontroller 216 to determine when to alternate the supply of main power from the main power supply 210 to each of a first subset 220 of electrical devices and a second subset 222 of electrical devices (similar to the alternating discussion above regarding Figure 3 . The microcontroller 216 can be used to adjust the switch 221 based on the timer output 236. For example, if the microcontroller 216 is configured to alternate after an elapsed time of 1 minute, once the timer output reaches one minute, the microcontroller 216 can adjust the configuration of the switch 221 to change from the electrical contact 224 to the electrical contact 226. After reaching the next minute, the microcontroller 216 can adjust the configuration of the switch 221 to change from the electrical contact 226 to the electrical contact 224. The timer 234 and the timer output 236 can also be present in any other embodiment described herein that uses alternating power supply to the electrical devices 202, whether alternating when only one subset is powered (also as Figure 10 shown), or alternating between the main power supply 210 and the auxiliary power supply 212 to supply power to a first subset 220 of electrical devices and a second subset 222 of electrical devices respectively, as shown in one embodiment of Figure 14 and Figure 15 .

[0084] Figure 10 shows in connection with Figure 9Operation of a similar power switching system, but where the auxiliary power supply 212 is being charged by the main power supply 210. The power switching system is in an "on" configuration where a nominal mode - power indicates that at least one of a first subset 220 of electrical devices and a second subset 222 of electrical devices is being powered, and a nominal mode - charge indicates that the auxiliary power supply 212 is receiving main power from the main power supply 210. It should be understood that the nominal mode is the mode of normal operation of the system where main power is used to power one or the other of the first subset 220 of electrical devices and the second subset 222 of electrical devices, regardless of whether the auxiliary power supply 212 is being charged.

[0085] Figure 11 Depicts operation of the power switching system where the system is in an "on" configuration but in an auxiliary mode. The microcontroller 216 has adjusted the orientation of the switch 230 to disconnect the auxiliary power supply from the main power supply 210 and has adjusted the configuration of the main selection switch 221 to contact the electrical contact 228. The electrical contact 228 is wired to a configuration where the first subset 220 of electrical devices and the second subset 222 of electrical devices are electrically connected in parallel, as visible in any of the diagrams in Figures 7 - 11 In the Figure 11 configuration shown, main power from the main power supply 210 and auxiliary power from the auxiliary power supply 212 are used to simultaneously and jointly power the first subset 220 of electrical devices and the second subset 222 of electrical devices. If a timer is present in the embodiment, the timer can be disabled to stop timing, or the microcontroller 216 can be configured to ignore the timer output because there is no need to alternate between the first subset 220 of electrical devices and the second subset 222 of electrical devices.

[0086] Now turning to Figures 12 - 16 , depicts further details of the power controller 204 where the main power supply 210 and the auxiliary power supply 212 are arranged to supply power to the first subset 220 of electrical devices and the second subset 222 of electrical devices, respectively. Figure 6The schematically representative switch 214 broadly represents switches 230, 238, and 240, all of which can be regulated by the microcontroller 216. The main power supply selection switch 238 can be used to provide main power from the main power supply 210. The auxiliary power supply selection switch 240 can be used to provide auxiliary power from the auxiliary power supply 212. The electrical contacts 242 - 246 are used in conjunction with the main power supply selection switch 238 to place the main power supply 210 in electrical communication with either the first subset 220 of electrical devices or the second subset 222 of electrical devices. The electrical contacts 248 - 252 are used in conjunction with the auxiliary power supply selection switch 240 to place the auxiliary power supply 212 in electrical communication with either the first subset 220 of electrical devices or the second subset 222 of electrical devices. A charging switch 230 is provided, which can contact the charging electrical contacts 232 to charge the auxiliary power supply 212. In some embodiments, the auxiliary power supply 212 can be charged when the main power supply 210 is not supplying power to any of the electrical devices 220 and 222. In embodiments where the main power supply can provide excess power beyond that required to energize the electrical devices as in Figure 3 the auxiliary power supply 212 can be charged during alternate operations as in Figure 3 . Figure 12 Further operating scenarios of the illustrated embodiment will be further described in Figures 13 - 16 below.

[0087] Figure 13 An operating scenario is shown where the power switching system is in the off state such that neither the first subset 220 of electrical devices nor the second subset 222 of electrical devices is supplied with power. The switches 238 and 240 are moved via the microcontroller 216 to positions in contact with the electrical contacts 242 and 252 respectively, and the electrical contacts 242 and 252 are empty electrical contacts. No power is transferred from the main power supply 210 or the auxiliary power supply 212 to either the first subset 220 of electrical devices or the second subset 222 of electrical devices. Although the power switching system is in the off state, the power switching system is operating in a mode where the auxiliary power supply 212 is being charged, which can be seen by the charging switch 230 being moved to a position in contact with the charging electrical contacts 232. In this configuration, the main power supply 210 supplies power to the auxiliary power supply 212. Figure 13 The power switching system shown in

[0088] Figure 14Shows a power switching system in the on state, where the main power from the main power supply 210 is delivered to a first subset 220 of electrical devices, and the main power from the main power supply 210 can also be delivered to a second subset 222 of electrical devices via the alternating contact of the switch 238 with the electrical contact 244 and the electrical contact 246. As described elsewhere herein, the switch 238 can be controlled by the microcontroller 216 to alternate between the electrical contact 244 and the electrical contact 246. The auxiliary power supply 212 is not charged by the position of the charging switch 230, and the auxiliary power is not provided by the position of the auxiliary disconnect switch 229. Figure 14 The power switching system shown in is in the nominal mode - power supply state, which indicates that at least one electrical device 202 is receiving power. The configuration of the electrical contact 244 and the electrical contact 246 relative to the switch 238 enables the power controller 204 to prohibit the supply of main power to one subset of electrical devices while another subset of electrical devices receives power. In addition, the power controller 204 can be configured to prohibit the supply of auxiliary power from the auxiliary power supply 212 by preventing the switch 240 from changing its position from contacting the electrical contact 252.

[0089] Although Figure 14 the embodiment shown in does not depict Figure 9 the timer 234 depicted in, it should be understood that Figure 14 an alternative embodiment of can include a timer. In this alternative embodiment, the microcontroller 216 can be used to adjust the switch 238 according to the timer output 236. For example, if the microcontroller 216 is configured to alternate after an elapsed time of 1 minute, then once the timer output reaches one minute, the microcontroller 216 can adjust the configuration of the switch 238 to change from the electrical contact 246 to the electrical contact 244. After reaching the next minute, the microcontroller 216 can adjust the configuration of the switch 238 to change from the electrical contact 244 to the electrical contact 246.

[0090] Figure 15 Shows the operation of a power switching system similar to Figure 14 but where the auxiliary power supply 212 is being charged by the main power supply 210. The power switching system is in the on configuration, where the nominal mode - power supply indicates that at least one of the first subset 220 of electrical devices and the second subset 222 of electrical devices is being powered, and the nominal mode - charging indicates that the auxiliary power supply 212 is receiving main power from the main power supply 210. It should be understood that the nominal mode is the mode of normal operation of the system, where the main power is used to power one or the other of the first subset 220 of electrical devices and the second subset 222 of electrical devices, regardless of whether the auxiliary power supply 212 is being charged.

[0091] Figure 16Depicts the operation of a power switching system where the system is in an on configuration but in an auxiliary mode. The microcontroller 216 has adjusted the orientation of switch 230 to disconnect the auxiliary power supply from the main power supply 210, and adjusted the configuration of the main power supply selection switch 238 to contact either electrical contact 244 or 246, while also adjusting the configuration of the auxiliary electrical contact switch 240 to contact either electrical contact 248 and electrical contact 250. The microcontroller 216 can be configured to ensure that the main power supply selection switch 238 contacts either electrical contact 244 or 246 to supply power to either the first subset 220 of electrical devices or the second subset 222 of electrical devices, while the configuration of switch 240 supplies power to the other of the first subset 220 of electrical devices or the second subset 222 of electrical devices. In Figure 16 the configuration shown, the main power from the main power supply 210 and the auxiliary power from the auxiliary power supply 212 are used to supply power to the first subset 220 of electrical devices and the second subset 222 of electrical devices respectively and simultaneously. The power controller 204 can be configured such that switches 238 and 240 are controlled by the microcontroller 216 to ensure that the main power supply 210 and the auxiliary power supply 212 are prohibited from simultaneously delivering power to one of the electrical devices 220 or 222.

[0092] If there is a timer in the embodiment, the timer can be prohibited from counting, or the microcontroller 216 can be configured to ignore the timer output because there is no need to alternate between the first subset 220 of electrical devices and the second subset 222 of electrical devices, or the microcontroller 216 can be configured to alternate the configuration of switches 238 and 240 while ensuring that the main power supply 210 and the auxiliary power supply 212 supply power to each of the first subset 220 of electrical devices and the second subset 222 of electrical devices respectively.

[0093] For any of the above embodiments, an indication of the health and / or status of the power switching system driven by the power controller 204 or other controller can be provided in the cockpit. For example, an indication can be provided in the cockpit display in response to the power controller 204 indicating that the auxiliary power supply 212 is charging, or that the auxiliary power supply 212 is fully charged and available for the auxiliary mode.

[0094] Now turning to Figure 17 depicts an embodiment of the logic configured in the microcontroller 216 (or configured elsewhere for controlling switch 214). In Figure 17In the illustrated embodiment, the power switching system can be enabled by first activating the main switch 254, where such activation can be manually operated by a user (e.g., a pilot) or can be an automatic operation (e.g., by the engine controller 200). If the main switch 254 is placed in the off position, the power switching system remains off and does not supply power to the first subset 220 of electrical devices and the second subset 222 of electrical devices for anti-icing. The main switch 254 can supply independent power to any one of the various switches 221, 230, 238, and 240, while in another form, the power controller 204 supplies power to the switches 221, 230, 238, and 240. It can be understood that supplying power to the switches 221, 230, 238, and 240 can be separate from controlling the positions of the switches 221, 230, 238, and 240. As an alternative and / or addition to the above, the main switch can control the power supplied to the power controller 204, and the power controller 204 in turn supplies power to the various switches 221, 230, 238, and 240. In other embodiments, the position of the main switch 254 can be provided in the input 218 of the power controller 204 for use by the power controller 204 when supplying power to the switches 221, 230, 238, and 240. Regardless of whether the main switch 254 is directly connected to supply power to any one of the switches 221, 230, 238, and 240, when the main switch 254 is placed in the on position, the power switching system can be placed in an on condition, as Figures 9 - 11 and Figures 14 - 16 shown.

[0095] The power controller 204 can also receive an indication of whether a user (e.g., a pilot) has selected the auxiliary mode, where such indication can be provided, for example, via the input 218. If the microcontroller 216 determines at the decision block 256 by checking the input 218 that the pilot has not selected the auxiliary mode, then Figure 17 the logic in

[0096] moves to the decision block 258 to determine whether takeoff power has been selected. Similar to the indication of the auxiliary mode via the input 218, the power controller 204 can receive a discrete indication of the selected takeoff power via the input 218 or can receive a power level via the input 218 and determine whether takeoff power has been selected based on the power level. Although the decision block 258 is described with respect to takeoff power, it should be understood that other decision logic can be implemented in the decision block 258 to affect whether the power switching system is configured to operate in the nominal mode or the auxiliary mode. Figure 9 、 10 、14 and 15. Thus, Figure 17A logical flow indicates that if the main switch 254 is on, the pilot has not selected the auxiliary mode, and the microcontroller 216 has not detected that takeoff power has been selected, the power switching system is placed in the nominal mode.

[0097] At decision block 262, if the pilot has selected the auxiliary mode (as determined at decision block 256), then Figure 17 the logical flow continues to check the ambient temperature (available via input 218) to determine if the temperature is within the allowable range for the auxiliary mode. If the temperature is not within the allowable range, then Figure 17 the logical flow moves to block 260, and the microcontroller 216 places the system in the nominal mode. In some embodiments, decision block 262 may include a limitation such as a one-sided inequality (e.g., if the ambient temperature is less than), rather than a range of acceptable conditions. If the limitation is not met, then Figure 17 the logical flow moves to block 260. In summary, Figure 17 another logical flow specifies that if the main switch 254 is on, the power switching system is placed in the nominal mode even if the user (e.g., the pilot) selects the auxiliary mode, because if the ambient temperature is not within the allowable range, the condition data via input 218 does not support the use of the auxiliary mode.

[0098] If takeoff power is selected at decision block 258, then Figure 17 the logical flow moves to decision block 262 to determine if the operating limitations are met. In the illustrated embodiment, the operating limitation is whether the ambient temperature is within the allowable limits. If the limitation is not met, then Figure 17 the logical flow moves to block 260. In summary, Figure 17 another logical flow specifies that if the main switch 254 is on, the user has not selected the auxiliary mode, but the condition data via input 218 indicates that takeoff power has been selected, but further condition data via input 218 does not support the use of the auxiliary mode because the ambient temperature is not within the allowable range, the power switching system is placed in the nominal mode. Although the user has not selected the auxiliary mode, given the critical flight phase of takeoff, this particular logical flow serves as a further check against automatically changing to the auxiliary mode by checking if the temperature limitation dictates powering the first subset 220 of electrical devices and the second subset 222 of electrical devices.

[0099] At decision block 262, if the ambient temperature is within the allowable range, then Figure 17The logic flow proceeds to decision block 264 to determine whether the auxiliary power supply 212 is charged to a sufficient level. This check at block 264 can be achieved by examining a discrete indication provided to the power controller 204 via input 218 (e.g., a discrete indication where a "1" indicates sufficient charge or a "0" indicates insufficient charge) or by examining the charge state provided via input 218 and comparing the charge state to a limit. For example, if the power controller 204 includes a 95% limit via the microcontroller 216 to meet the charge sufficiency of block 264, then if the charge state received via input 218 meets the limit (e.g., is greater than or greater than / equal to 95%), decision block 264 proceeds to block 266, where the auxiliary mode is activated. In summary, Figure 17 Another logic flow indicates that if the main switch 254 is in the ON state, the user has selected the auxiliary mode, or the microcontroller 216 determines that takeoff power has been selected (even though the user has not selected the auxiliary mode), the ambient temperature range is met, and the auxiliary power supply 212 has been sufficiently charged, then the power switching system is placed in the auxiliary mode.

[0100] If decision block 264 determines that the auxiliary power supply 212 has insufficient charge, decision block 264 moves to block 260, where the nominal mode is activated. In summary, Figure 17 Another logic flow indicates that if the main switch 254 is ON, even if the user has selected the auxiliary mode or the microcontroller 216 determines that takeoff power has been selected (even though the user has not selected the auxiliary mode), the ambient temperature range is met, but the auxiliary power supply 212 has insufficient charge, then the power switching system is placed in the nominal mode.

[0101] Now turning to Figure 18 , any of the controllers described herein (e.g., the engine controller 200, the power controller 204, or the microcontroller 216) can be implemented using a computing device 268, Figure 18 FIG. shows an embodiment of the computing device 268. For ease of illustration, Figure 18 FIG. shows the microcontroller 216, but this description applies to any other controller discussed herein. The computing device 268 can include one or more processors 268A and one or more memory devices 268B. The one or more processors 268A can 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 268B can include one or more computer-readable media, including but not limited to non-transitory computer-readable media, RAM, ROM, hard disk drives, flash drives, and / or other memory devices.

[0102] One or more memory devices 268B may store information accessible to one or more processors 268A, including computer-readable instructions 268C executable by one or more processors 268A. The instructions 268C may be any instruction set that, when executed by one or more processors 268A, causes one or more processors 268A to perform operations. In some embodiments, the instructions 268C may be executed by one or more processors 268A to cause one or more processors 268A to perform operations such as any operations and functions that the controller and / or computing device 268 is configured for, operations of any of the above-described systems as described herein, and / or any other operations or functions of one or more computing devices 268 (e.g., as a full-authority digital engine controller). The instructions 268C may be software written in any suitable programming language or may be implemented in hardware. Additionally, and / or alternatively, the instructions 268C may be executed in logically and / or virtually separate threads on one or more processors 268A. One or more memory devices 268B may also store data 268D accessible by one or more processors 268A. For example, the data 268D may include data indicating external air conditions, power flow, data indicating engine / aircraft operating conditions, and / or any other data and / or information described herein.

[0103] The computing device 268 may also include a network interface 268E for communicating, for example, with other components of the systems described herein (e.g., via a communication network). The network interface 268E may include any suitable components for interfacing with one or more networks, including, for example, a transmitter, a receiver, ports, 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 268 or provide one or more commands to the computing device 268.

[0104] The network interface 268E may include any suitable components for interfacing with one or more networks, such as including a transmitter, a receiver, ports, a controller, an antenna, and / or other suitable components.

[0105] The techniques discussed herein relate to computer-based systems and actions taken by and information sent to and from computer-based systems. Those of ordinary skill in the art will recognize that the inherent flexibility of computer-based systems allows for many possible configurations, combinations, and divisions of tasks and functions among and within components. For example, the processes discussed herein may be implemented using a single computing device or a combination of multiple computing devices working together. Databases, memories, instructions, and applications may be implemented on a single system or distributed across multiple systems. Distributed components may operate sequentially or in parallel.

[0106] Figure 19 A method 270 of switching power is disclosed, which includes operating a plurality of power devices in step 272. The plurality of power devices are configured to generate an electrical response when powered by main power from a main power source 210. The plurality of electrical devices 202 include a first subset 220 of electrical devices and a second subset 222 of electrical devices. As described above, the electrical devices can take any form, including electric heaters, fluid pumps, pneumatic pumps, etc. In addition, the first subset 220 of electrical devices may include the same or different numbers of electrical devices 202 as the second subset 222 of electrical devices. In step 274, the method 270 further includes alternately powering the first subset 220 of electrical devices and the second subset 222 of electrical devices with main power during a nominal operating mode, such that the first subset 220 of electrical devices is not powered by main power simultaneously with the second subset 222 of electrical devices. In step 276, the method 270 further includes: during an auxiliary operating mode, selectively powering one of the first subset 220 of electrical devices or the second subset 222 of electrical devices with auxiliary power from an auxiliary power source 212 when the other of the first subset 220 of electrical devices or the second subset 222 of electrical devices is receiving main power from the main power source 210.

[0107] The method 270 may include further steps, including operating a prime mover configured as a propulsion power source of an aircraft 161. The prime mover includes an open rotor 152 having a plurality of fan blades 154, and each of the plurality of fan blades 154 includes at least one electrical device 202 from the plurality of power devices. The method 270 may further include alternating based on a timer. In addition, the method 270 may include initiating the auxiliary operating mode based on at least one of the following: (1) user input; (2) the operating condition of the open rotor; or (3) a command received by a power controller from another controller. In addition, the method 270 may include prohibiting alternation during the auxiliary operating mode.

[0108] Embodiments of the present disclosure can be used to provide continuous heating during an operating portion of a gas turbine engine 100 (e.g., during a flight-critical operating portion). During nominal use, the system can alternate between main power and the first subset 220 and the second subset of electrical devices to avoid exceeding operating constraints (e.g., the maximum current flowing through the electrical devices) and / or exceeding the budgeted power draw of the gas turbine engine 100. When it is necessary to fully utilize the electrical devices 202 (e.g., during a critical phase of flight), an auxiliary power source can be used to provide additional electrical energy so that all electrical devices can be powered simultaneously.

[0109] A further aspect is provided by the subject matter of the following clauses:

[0110] A power switching system, the power switching system comprising: a main power supply configured to provide main power; a plurality of power devices configured to generate an electrical response when powered by the main power, the plurality of power devices including a first subset of power devices and a second subset of power devices; a power controller having a normal operation mode and an auxiliary operation mode, the normal operation mode being configured to supply the main power to the first subset of power devices and, when supplying the main power to the first subset of power devices, prohibit the main power from being delivered to the second subset of power devices; and an auxiliary power supply configured to provide auxiliary power; wherein the power controller further includes an auxiliary operation mode configured to supply the main power to the first subset of power devices and supply the auxiliary power to the second subset of power devices.

[0111] The power switching system according to the preceding item, wherein each of the plurality of power devices is the same as the other power devices in the plurality of power devices.

[0112] A power switching system, the power switching system comprising: a main power supply configured to provide main power; an auxiliary power supply configured to provide auxiliary power; a plurality of power devices configured to generate an electrical response when powered by the main power, the plurality of power devices including a first subset of power devices and a second subset of power devices; and a power controller having a normal operation mode and an auxiliary operation mode, the normal operation mode being configured to prohibit the first subset of power devices and the second subset of power devices from being simultaneously powered by the main power supply, the auxiliary operation mode being configured to supply the main power to the first subset of power devices from the main power supply while supplying the auxiliary power to the second subset of power devices from the auxiliary power supply.

[0113] The power switching system according to the preceding claim, wherein if only one of the main power or the auxiliary power is supplied to either the first subset of power devices or the second subset of power devices, the auxiliary operation mode is configured to supply the main power to the first subset of power devices and supply the auxiliary power to the second subset of power devices.

[0114] A power switching system for an anti-icing system, the power switching system comprising: a main power source configured to provide main power; a plurality of power devices electrically coupled to the main power, each of the plurality of power devices including a heating element configured to remove ice from an aircraft surface, the plurality of power devices including a first subset of power devices and a second subset of power devices; a power controller having a normal operating mode configured to supply the main power to the first subset of power devices and, when supplying the main power to the first subset of power devices, prohibit the delivery of the main power to the second subset of power devices; and an auxiliary power source configured to provide auxiliary power; wherein the power controller further includes an auxiliary operating mode configured to supply the main power or the auxiliary power, or both, to the first subset of power devices and simultaneously supply the main power or the auxiliary power, or both, to the second subset of power devices.

[0115] The power switching system for an anti-icing system according to the preceding claim, wherein if only one of the main power or the auxiliary power is supplied to either the first subset of power devices or the second subset of power devices, the auxiliary operating mode is configured to supply the main power to the first subset of power devices and supply the auxiliary power to the second subset of power devices.

[0116] The power switching system for an anti-icing system according to any one of the preceding claims, wherein the plurality of power devices are electric heaters.

[0117] The power switching system for an anti-icing system according to any one of the preceding claims, further comprising a prime mover configured as a propulsion power source of the aircraft.

[0118] The power switching system for an anti-icing system according to any one of the preceding claims, wherein the prime mover includes an open rotor having a plurality of open rotor blades, each open rotor blade including at least one of the plurality of power devices.

[0119] A power switching system for an ice protection system according to any one of the preceding claims, wherein the normal operation mode is further configured to alternate between the following configurations: (1) a first configuration, wherein the power controller is configured to supply the main power to a first subset of the power devices and prohibit the delivery of the main power to a second subset of the power devices; and (2) a second configuration, wherein the power controller is configured to supply the main power to the second subset of the power devices and prohibit the delivery of the main power to the first subset of the power devices.

[0120] A power switching system for an ice protection system according to any one of the preceding claims, wherein the normal operation mode is further configured to alternate between the first configuration and the second configuration based on a timer, and wherein the power controller responds to a timer output from the timer such that the power controller alternates between the first configuration and the second configuration based on the timer output in the normal operation mode.

[0121] A power switching system for an ice protection system according to any one of the preceding claims, wherein the power controller is configured to supply the main power to a first subset of the power devices and supply the auxiliary power to a second subset of the power devices throughout the auxiliary operation mode.

[0122] A power switching system for an ice protection system, the power switching system comprising: a main power source configured to provide main power; an auxiliary power source configured to provide auxiliary power; a plurality of power devices electrically coupled to the main power, each of the plurality of power devices including a heating element configured to remove ice from an aircraft surface, the plurality of power devices including a first subset of power devices and a second subset of power devices; and a power controller having a normal operation mode and an auxiliary operation mode, the normal operation mode being configured to prohibit the first subset of the power devices and the second subset of the power devices from being powered by the main power source simultaneously, the auxiliary operation mode being configured to supply the main power or the auxiliary power or both to the first subset of the power devices and simultaneously supply the main power or the auxiliary power or both to the second subset of the power devices.

[0123] A power switching system for an ice protection system according to the preceding claim, further comprising a prime mover having an open rotor, the plurality of power devices being configured as electric heaters and being configured to prevent ice formation on the open rotor.

[0124] A power switching system for an ice protection system according to any one of the preceding claims, wherein the auxiliary operation mode is initiated by at least one of the following: (1) a user input; (2) an operating condition of the open rotor; or (3) a command received by the power controller from another controller.

[0125] A power switching system for an ice protection system according to any one of the preceding claims, wherein the power controller is configured to receive an operating condition input and determine whether to operate in the normal operation mode or the auxiliary operation mode based on the operating condition input.

[0126] A power switching system for an ice protection system according to any one of the preceding claims, wherein the operating condition input includes at least one of a power level, ice detection, on-wheel weight, and landing gear lever position.

[0127] A power switching system for an ice protection system according to any one of the preceding claims, wherein the power level is at least one of a power level angle, a throttle position, a propeller pitch setting, and a fuel / air mixture setting.

[0128] A power switching system for an ice protection system according to any one of the preceding claims, wherein the normal operation mode includes (1) normal mode - power supply, wherein a first subset of the power devices and a second subset of the power devices are prohibited from being powered by the main power supply simultaneously, and (2) normal mode - charging, wherein the main power is supplied to the auxiliary power supply to charge the auxiliary power supply, and the main power is not supplied to any of the plurality of power devices.

[0129] A method of switching power for an ice protection system, the method comprising: operating a plurality of power devices configured to generate an electrical response to remove ice from an aircraft surface when powered by main power from a main power supply, the plurality of power devices including a first subset of power devices and a second subset of power devices; during a nominal operation mode, alternately powering the first subset of power devices and the second subset of power devices with the main power such that the first subset of power devices is not powered by the main power simultaneously with the second subset of power devices; and during an auxiliary operation mode, selectively powering one of the first subset of power devices or the second subset of power devices with auxiliary power from an auxiliary power supply when the other of the first subset of power devices or the second subset of power devices is receiving the main power from the main power supply.

[0130] The method according to the preceding claim further comprises operating a prime mover configured as a propulsion power source of an aircraft, the prime mover including an open rotor having a plurality of fan blades, each of the plurality of fan blades including at least one power device from the plurality of power devices.

[0131] The method according to any one of the preceding claims, wherein the alternation is based on a timer.

[0132] The method according to any one of the preceding claims further comprises initiating the auxiliary operation mode based on at least one of: (1) a user input; (2) an operating condition of the open rotor; or (3) a command received by the power controller from another controller.

[0133] The method according to any one of the preceding claims, wherein the alternation is prohibited during the auxiliary operation mode.

[0134] This written description uses examples to disclose the present disclosure, including the best mode, and also enables those skilled in the art to practice the present disclosure, including making and using any device or system and performing any incorporated method. 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. If these other examples include structural elements that are identical to the literal language of the claims or if they include equivalent structural elements that are not materially different from the literal language of the claims, then these other examples are intended to be within the scope of the claims.

Claims

1. An electric power switching system for an anti-icing system, characterized in that, The power switching system includes: A main power source configured to provide main power; A plurality of power devices electrically coupled to the main power, each of the plurality of power devices including a heating element configured to remove ice from the surface of the aircraft, the plurality of power devices including a first subset of power devices and a second subset of power devices; A power controller having a normal operation mode configured to supply the main power to the first subset of power devices and, when supplying the main power to the first subset of power devices, prohibit the delivery of the main power to the second subset of power devices; and An auxiliary power source configured to provide auxiliary power; Wherein the power controller further includes an auxiliary operation mode configured to supply the main power or the auxiliary power, or both, to the first subset of power devices and, simultaneously, supply the main power or the auxiliary power, or both, to the second subset of power devices.

2. The power switching system for an anti-icing system according to claim 1, characterized in that Wherein, If only one of the main power or the auxiliary power is supplied to either the first subset of power devices or the second subset of power devices, the auxiliary operation mode is configured to supply the main power to the first subset of power devices and supply the auxiliary power to the second subset of power devices.

3. The power switching system for an anti-icing system according to claim 1, characterized in that, Wherein, The plurality of power devices are electric heaters.

4. The power switching system for an anti-icing system according to claim 1, characterized in that, Further includes a prime mover configured as a propulsion power source of the aircraft.

5. The power switching system for an anti-icing system according to claim 4, characterized in that, Wherein, The prime mover includes an open rotor having a plurality of open rotor blades, each open rotor blade including at least one of the plurality of power devices.

6. The power switching system for an anti-icing system according to claim 1, characterized in that, Wherein, The normal operation mode is further configured to alternate between the following configurations: (1) a first configuration in which the power controller is configured to supply the main power to the first subset of power devices and prohibit the delivery of the main power to the second subset of power devices; and (2) a second configuration in which the power controller is configured to supply the main power to the second subset of power devices and prohibit the delivery of the main power to the first subset of power devices.

7. The power switching system for an anti-icing system according to claim 6, characterized in that, Wherein, The normal operation mode is further configured to alternate between the first configuration and the second configuration based on a timer, wherein the power controller responds to a timer output from the timer such that the power controller alternates between the first configuration and the second configuration in the normal operation mode based on the timer output.

8. The power switching system for an anti-icing system according to claim 1, characterized in that, Wherein, The power controller is configured to supply the main power to the first subset of power devices and supply the auxiliary power to the second subset of power devices throughout the auxiliary operation mode.

9. A power switching system for an ice protection system, characterized in that, The power switching system includes: A main power source configured to provide main power; An auxiliary power source configured to provide auxiliary power; A plurality of electrical devices, the plurality of electrical devices being electrically coupled to the main power, each of the plurality of electrical devices including a heating element configured to remove ice from an aircraft surface, the plurality of electrical devices including a first subset of electrical devices and a second subset of electrical devices; and A power controller having a normal operating mode and an auxiliary operating mode, the normal operating mode being configured to prohibit the first subset of electrical devices and the second subset of electrical devices from being powered by the main power source simultaneously, the auxiliary operating mode being configured to supply the main power or the auxiliary power, or both, to the first subset of electrical devices and simultaneously supply the main power or the auxiliary power, or both, to the second subset of electrical devices.

10. The power switching system for an anti-icing system according to claim 9, wherein, Further includes a prime mover having an open rotor, the plurality of electrical devices being configured as electric heaters and being configured to prevent icing on the open rotor.

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