Turbine engine system with fuel deoxygenation system and turbine power system

Abstract

A turbine engine system having a fuel deoxygenation system and a turbine power system is provided. In one aspect, the turbine engine system includes a turbine power system having an electrical generator operably coupled with a gas turbine engine. A fuel line provides fuel to the gas turbine engine. A fuel deoxygenation system is positioned along the fuel line for reducing an amount of oxygen in the fuel. A main fuel pump is positioned along the fuel line downstream of the fuel deoxygenation system. An electric motor drives the main fuel pump. The electrical generator of the turbine power system is operably coupled with the gas turbine engine and generates electrical power. The electrical power is provided to the electric motor and the fuel deoxygenation system. Heat is recovered from the turbine power system and the electric motor and imparted to the fuel provided to the gas turbine engine.

Description

Technical Field

[0001] This topic generally relates to a turbine engine system with a fuel deoxygenation system and a turbine electric system. Background Technology

[0002] Traditional aircraft propulsion systems consist of one or more gas turbine engines. These gas turbine engines typically comprise either a turbine or a core engine. The core engine typically comprises a compressor section, a combustion section, a turbine section, and an exhaust section in a sequential flow order. In operation, air is supplied to the inlet of the compressor section, where one or more axial compressors progressively compress the air until it reaches the combustion section. Fuel is mixed with the compressed air and burned within the combustion section to provide combustion gases. These combustion gases are then directed from the combustion section to the turbine section. The flow of combustion gases through the turbine section drives the turbine section and is then directed through the exhaust section, for example, into the atmosphere.

[0003] Some aircraft propulsion systems can be hybrid electric propulsion systems that include a turbine-powered generator system. Such systems can include a generator operatively coupled to a gas turbine engine. The generator can produce electrical energy. However, turbine-electric systems generate a significant amount of heat during operation. Fuel has been identified as an effective radiator to receive at least some of this heat during operation, at least in part due to its heat capacity and the increased efficiency that may result from burning fuel at higher temperatures during combustion. However, heating fuel without proper conditioning can lead to fuel “coking” or the formation of solid particles that can clog certain components of the fuel system, such as fuel nozzles. Reducing the amount of oxygen in the fuel can effectively reduce the likelihood of fuel coking exceeding unacceptable levels. Therefore, fuel deoxygenation systems can be provided to reduce the oxygen in the fuel. However, components of such fuel deoxygenation systems may require significant amounts of electricity (for pumping and heaters), and the packaged volume and mass of such components increase the weight of the aircraft with the gas turbine engine mounted. Traditionally, there has been no cooperation between the turbine-powered generator system and the fuel deoxygenation system, leading to system inefficiency and adverse consequences.

[0004] Therefore, an engine system that addresses one or more of the aforementioned challenges would be useful. Summary of the Invention

[0005] Various aspects of this disclosure relate to distributed control systems and methods for controlling turbines. Aspects and advantages of the invention will be set forth in part in the description which follows, or may be apparent from the description, or may be learned by practice of the invention.

[0006] In one aspect, an engine system is provided. The engine system includes a turbine electric system having a gas turbine engine and one or more electrical components. At least one of the one or more electrical components is operable to generate electricity. The engine system also includes a fuel line for supplying fuel to the gas turbine engine. Furthermore, the engine system includes a fuel conditioning system positioned along the fuel line and operable to regulate the fuel. The fuel conditioning system is operable to receive electricity from the turbine electric system. Additionally, the engine system includes a main fuel pump operable to move fuel along the fuel line. Furthermore, the engine system includes a heat exchanger positioned along the fuel line. Furthermore, the engine system includes a heat recovery loop along which a working fluid is operable, the heat recovery loop being at least partially positioned to have a heat exchange relationship with one or more electrical components of the turbine electric system, such that the one or more electrical components impart heat energy to the working fluid moving along the heat recovery loop, the heat recovery loop also being at least partially positioned to have a heat exchange relationship with the fuel line at the heat exchanger, such that the working fluid imparts heat energy to the fuel moving along the fuel line.

[0007] In another aspect, an engine system is provided. The engine system includes a turbine electric system having a gas turbine engine and one or more electrical components, including a generator operatively coupled to the gas turbine engine. The generator is operable to generate electricity. The engine system also includes a fuel line for supplying fuel to the gas turbine engine. Furthermore, the engine system includes a fuel deoxygenation system located along the fuel line and operable to reduce the amount of oxygen in the fuel. The fuel deoxygenation system is operable to receive electricity from the turbine electric system. Additionally, the engine system includes a main fuel pump located downstream of the fuel deoxygenation system along the fuel line. The main fuel pump is operable to move fuel along the fuel line. The engine system also includes a heat exchanger located along the fuel line. In addition, the engine system includes a heat recovery loop along which a working fluid can move. The heat recovery loop is at least partially positioned to have a heat exchange relationship with one or more electrical components of the turbine electrical system, such that the one or more electrical components impart heat energy to the working fluid moving along the heat recovery loop. The heat recovery loop is also at least partially positioned to have a heat exchange relationship with a fuel line at a heat exchanger, such that the working fluid imparts heat energy to fuel moving along the fuel line.

[0008] In another aspect, an engine system is provided. The engine system includes a turbine electric system having a gas turbine engine and one or more electrical components, including a generator operatively coupled to the gas turbine engine, the generator being operable to generate electricity. Furthermore, the engine system includes a fuel line for supplying fuel to the gas turbine engine. Additionally, the engine system includes a fuel deoxygenation system located along the fuel line and operable to reduce the amount of oxygen in the fuel. The fuel deoxygenation system is operable to receive electricity from the turbine electric system. Furthermore, the engine system includes a main fuel pump system having a main fuel pump and an electric motor operatively coupled to the main fuel pump to drive the main fuel pump. The main fuel pump is located downstream of the fuel deoxygenation system along the fuel line. The electric motor is operable to receive electricity from the turbine electric system. Furthermore, the engine system includes an upstream heat exchanger located upstream of the fuel deoxygenation system along the fuel line and a downstream heat exchanger located downstream of the fuel deoxygenation system along the fuel line. Furthermore, the engine system includes a first heat recovery loop along which a first working fluid is movable. The first heat recovery circuit is at least partially positioned to exchange heat with one or more electrical components of the turbine electrical system, such that the one or more electrical components impart heat energy to the first working fluid. The first heat recovery circuit is also at least partially positioned to exchange heat with a fuel line at an upstream heat exchanger, such that the first working fluid imparts heat energy to fuel moving along the fuel line. Furthermore, the engine system includes a second heat recovery circuit along which a second working fluid is movable. The second heat recovery circuit is at least partially positioned to exchange heat with an electric motor, such that the electric motor imparts heat energy to the second working fluid. The second heat recovery circuit is also at least partially positioned to exchange heat with a fuel line at a downstream heat exchanger, such that the second working fluid imparts heat energy to fuel moving along the fuel line.

[0009] These and other features, aspects, and advantages of the invention will become more readily understood with reference to the following description and the appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention. Attached Figure Description

[0010] The specification sets forth a complete and feasible disclosure of the invention for those skilled in the art, including its best mode, and refers to the accompanying drawings, wherein:

[0011] Figure 1 A schematic cross-sectional view of an aviation gas turbine engine according to an example embodiment of this subject is provided;

[0012] Figure 2A schematic system diagram of a turbine engine system according to an example embodiment of this subject is provided;

[0013] Figure 3 A schematic system diagram of another turbine engine system according to an example embodiment of this subject is provided;

[0014] Figure 4 A schematic system diagram of yet another turbine engine system according to an example embodiment of this subject is provided; and

[0015] Figure 5 Example carriers are provided based on example embodiments of this topic. Detailed Implementation

[0016] Reference will now be made in detail to the present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. Detailed descriptions use numbers and letters to designate features in the drawings. Similar or analogous reference numerals in the drawings and description have been used to designate similar or analogous portions of the invention. As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the individual components. The terms “upstream” and “downstream” refer to the relative flow direction of fluid flow in a fluid path. For example, “upstream” refers to the flow direction from which the fluid flows, and “downstream” refers to the flow direction to which the fluid flows.

[0017] The heat transfer or heat exchange relationships described herein may include thermal connectivity via conduction and / or convection. A heat transfer relationship may include a conductive relationship in which heat transfer is provided by conduction (e.g., thermal diffusion) between solids and / or between a solid and a fluid. Furthermore, or alternatively, a heat transfer relationship may include a thermal convection relationship in which heat transfer is provided by convection between a fluid and a solid (e.g., heat transfer via a large flow of fluid). It should be understood that convection generally includes a combination of conduction (e.g., thermal diffusion) and convection (e.g., heat transfer via a large flow of fluid). As used herein, reference to heat exchange relationships may include conduction and / or convection.

[0018] This disclosure relates to engine systems with optimized architectures, wherein a turbine electric system, a main fuel pump system, and a fuel deoxygenation system are combined in an efficient cooperative arrangement. The turbine electric system includes a generator operatively coupled to the gas turbine engine. The generator is operable to generate electricity. The generated electrical energy is supplied to the electrical components of the fuel deoxygenation system and an electric motor operable to drive the main fuel pump, as well as other possible electrical loads. In some embodiments, the electric motor synchronously drives an auxiliary or fuel deoxygenation pump together with the main fuel pump. Furthermore, engine fuel is used by the engine turbine electric system as a cooling medium or radiator to provide cooling. The fuel deoxygenation system improves acceptable fuel temperatures or the fuel's heat dissipation capacity, which enhances the cooling of the electrical components of the turbine electric system.

[0019] Figure 1 A schematic cross-sectional view of an aviation gas turbine engine according to an example embodiment of this subject is provided. This engine can be incorporated into an aircraft. For the depicted embodiment, the engine is configured as a high-bypass turbofan engine 100. Figure 1 As shown, the turbofan engine 100 defines an axial direction A (extending parallel to the longitudinal centerline or axis 101 provided for reference), a radial direction R, and a circumferential direction (extending around the longitudinal centerline 101). Although the turbofan 100 is described below and Figure 1 The illustration is a representative example of an aircraft turbofan; however, it should be understood that the subject matter of this disclosure can be applied to other suitable types of engines and turbines. For example, the subject matter of this disclosure can be applied to other suitable turbine engines or in combination with other suitable turbine engines, such as steam and other gas turbine engines, including but not limited to turbojet engines, turboprop engines, turboshaft engines, aeroderivatives, auxiliary power units, etc.

[0020] like Figure 1As shown, the turbofan 100 includes a fan section 102 and a turbine or core engine 104 disposed downstream of the fan section 102. An exemplary core engine 104 includes a substantially tubular outer casing 106 defining an annular core inlet 108. The casing 106 encloses, in a series flow relationship: a compressor section including a supercharger or low-pressure (LP) compressor 110 and a high-pressure (HP) compressor 112; a combustion section 114; a turbine section including a high-pressure (HP) turbine 116 and a low-pressure (LP) turbine 118; and an exhaust nozzle section 120. The compressor section, combustion section 114, and turbine section together at least partially define a core airflow path 121 extending from the annular core inlet 108 to the exhaust nozzle section 120. The turbofan engine 100 also includes one or more drive shafts. More specifically, the turbofan engine 100 includes a high-pressure (HP) shaft or spool 122 that drives an HP turbine 116 to an HP compressor 112, and a low-pressure (LP) shaft or spool 124 that drives an LP turbine 118 to an LP compressor 110.

[0021] Fan section 102 includes a fan 126 having a plurality of fan blades 128 spaced apart and coupled to disk 130. The fan blades 128 and disk 130 can rotate together about longitudinal axis 101 via LP shaft 124. Disk 130 is covered by a rotatable front hub or swivel 132 aerodynamically profiled to facilitate airflow through the plurality of fan blades 128. Additionally, an annular fan housing or outer nacelle 134 is provided circumferentially surrounding at least a portion of fan 126 and / or core engine 104. Nacelle 134 is supported relative to core engine 104 by a plurality of circumferentially spaced outlet guide vanes 136. A downstream section 138 of nacelle 134 extends above and outside core engine 104 to define a bypass airflow passage 140 therebetween.

[0022] Still referencing Figure 1 In this embodiment, generator 160 is operatively connected to LP shaft 124. In other embodiments, generator 160 may be operatively connected to HP shaft 122. Both generator 160 and turbine fan 100 are components of a turbine power system. As will be understood, rotation of LP shaft 124 causes generator 160 to generate electricity. The electricity can be supplied to various power-consuming devices via power bus 162. The electricity can be regulated by various power conditioning devices (e.g., power converters), such as converting alternating current (AC) to direct current (DC).

[0023] The turbofan engine 100 also includes a fuel delivery system 170, which includes a fuel supply section 172 (e.g., a carrier fuel tank), a fuel line 174 that may include one or more fuel lines, a fuel deoxygenation system 176 positioned along the fuel line 174, and a main fuel pump system 178 positioned along the fuel line 174. As shown, the fuel delivery system supplies fuel from the fuel supply section 172 to the combustion section 114 of the core engine 104 of the turbofan engine 100. The combustion section 114 includes a plurality of fuel nozzles 152, which, in the illustrated embodiment, are arranged circumferentially around a centerline axis 101. The main fuel pump system 178 may include an electric motor for driving a main fuel pump operable to move fuel along the fuel line 174 to the fuel nozzles 152. The main fuel pump may be a variable-speed fuel pump, which can eliminate or minimize the need for a fuel bypass path. Electricity generated by a generator 160 can be directed to the electric motor via a power bus 162 to drive the main fuel pump.

[0024] The fuel deoxygenation system 176 is operable to reduce the free oxygen content of the fuel delivered to the combustion zone 114, and more specifically to the fuel nozzle 152. The fuel deoxygenation system 176 may include one or more fuel oxygen reduction units. Each fuel oxygen reduction unit may include one or more electrically powered components, such as electric heaters, sensors, controllers, etc. Electricity generated by the generator 160 can be directed to the electrically powered components of the fuel deoxygenation system 176 via the power bus 162. Furthermore, each fuel oxygen reduction unit may include one or more mechanically powered components, such as fuel pumps, gas pumps, fuel / gas separators, and / or other rotating components. In some embodiments, one or more mechanically powered components of the fuel deoxygenation system 176 may be synchronously driven by an electric motor driving the main fuel pump, or may be driven by a single fuel deoxygenation electric motor or multiple electric motors. Electricity generated by the generator 160 can be directed to the fuel deoxygenation electric motor via the power bus 162.

[0025] In addition, a heat recovery loop 180 is provided along which the working fluid flows to recover heat generated by electrical components of the turbine power generation system, such as heat generated by generator 160, power conditioning devices, switches, etc. The heat recovery loop 180 may include one or more open-loop and / or closed-loop circuits. The heated working fluid is directed to one or more heat exchangers that facilitate heat transfer between the relatively hot working fluid flowing along the heat recovery loop 180 and the fuel flowing along the fuel line 174. In some embodiments, the working fluid flowing along the heat recovery loop 180 recovers heat from the electric motor of the main fuel pump system 178. The heated working fluid may be directed to one or more heat exchangers that facilitate heat transfer between the relatively hot working fluid flowing along the heat recovery loop 180 and the fuel flowing along the fuel line 174. Therefore, Figure 1 The present invention provides a turbine engine system in which the main fuel pump system 178 and the fuel deoxygenation system 176 are powered or driven by a turbine electric system, and the fuel delivered to the combustion section 114 of the turbine fan 100 is used as a cooling medium or radiator for the electrical components of the turbine electric system. Various turbine engine system architectures are provided below, in which the turbine electric system, the main fuel pump system, and the fuel deoxygenation system are combined in an efficient cooperative arrangement.

[0026] Figure 2 A schematic system diagram of a turbine engine system 200 according to an example embodiment of this subject is provided. Figure 2 The turbine engine system 200 can be installed on or included on the carrier, for example Figure 5 Any of the carriers shown. As shown, the turbine engine system 200 includes a turbine electrical system 220, which includes a gas turbine engine 210, a fuel deoxygenation system 240, and a main fuel pump system 250. For example, the gas turbine engine 210 may be an aviation gas turbine engine mounted on an aircraft. For example, the gas turbine engine 210 may be... Figure 1 The turbofan 100. As will be understood, the gas turbine engine 210 is operable to output mechanical power, for example, which can be used to generate thrust for its associated aircraft.

[0027] In addition, for Figure 2In the illustrated embodiment, the mechanical power output by the gas turbine engine 210 causes the generator 224 of the turbine electrical system 220 to convert the mechanical energy provided by the gas turbine engine 210 into electrical energy. Therefore, the generator 224 can ultimately output electrical power. The electrical power output by the generator 224 can be provided to or otherwise directed to various components of the turbine engine system 200 and other loads on the aircraft. The generator 224 can be a standalone generator or a combination of an electric motor and a generator. The generator 224 is operatively coupled to the gas turbine engine 210. As an example, the generator 224 can be coupled to the LP shaft or spool of the gas turbine engine 210. As another example, the generator 224 can be coupled to the HP shaft or spool of the gas turbine engine 210. In other embodiments, the generator 224 can be coupled to other suitable rotating components.

[0028] The turbine power system 220 has one or more electrical components 222. The one or more electrical components 222 include a generator 224 and other components. For example, such as... Figure 2 As shown, one or more electrical components 222 may include one or more power regulators 226 electrically connected to generator 224. Power regulators 226 may regulate the power in any suitable manner. As an example, power regulators 226 may include one or more rectifiers that convert alternating current (AC) generated by generator 224 into direct current (DC). One or more electrical components 222 of turbine power system 220 may also include other components such as electrical switches, one or more energy storage devices (e.g., batteries or battery packs), processing devices, etc. The power generated by generator 224 and regulated by one or more power regulators 226 may be supplied to power-consuming loads via power bus 228. It is worth noting that during operation, one or more electrical components 222 of turbine power system 220 generate a significant amount of heat. As will be explained further below, the heat generated by one or more electrical components 222 of turbine power system 220 may be provided to fuel recovery and ultimately rejected or supplied to fuel in gas turbine engine 210.

[0029] The turbine electrical system 220 includes a fuel line 230 for supplying fuel to the gas turbine engine 210, for example, to one or more fuel nozzles in the combustor that directs fuel into the gas turbine engine 210. Specifically, the fuel line 230 delivers fuel from a fuel supply unit, such as a carrier fuel supply unit 232, to the gas turbine engine 210. The fuel line 230 may be a single line or may include multiple lines or conduits in fluid communication.

[0030] A fuel conditioning system is located along fuel line 230. Typically, a fuel conditioning system is operable to regulate fuel. In this embodiment, the fuel conditioning system is a fuel deoxygenation system 240. Typically, the fuel deoxygenation system 240 reduces the amount of oxygen in the fuel. In this way, the possibility or risk of the fuel “coking” beyond an unacceptable amount when heated is reduced. The fuel deoxygenation system 240 may include one or more electrical components 242 that require electricity, such as one or more electric heaters 244, sensors, controllers, electric motors, etc. The electric heaters 244 may apply heat or impart thermal energy to the fuel. Electricity generated by generator 224 may be supplied to the electrical components 242 of the fuel deoxygenation system 240, including the electric heaters 244. The fuel deoxygenation system 240 also includes one or more mechanical components 245 that require mechanical power, such as a fuel deoxygenation pump 246, a gas pump, a fuel / gas separator, and / or other rotating components. The fuel deoxygenation pump 246 is operable to move fuel through the fuel deoxygenation system 240. The fuel deoxygenation pump 246 can control the volume and mass of fuel flowing through the fuel deoxygenation system 240. For example, the fuel deoxygenation pump 246 can be electrically driven or mechanically driven. Figure 2 As shown, the fuel leaves the fuel deoxygenation system 240 as regulated or deoxygenated fuel.

[0031] The main fuel pump system 250 includes a main fuel pump 254 and an electric motor 252 for driving the main fuel pump 254. The main fuel pump 254 is located downstream of the fuel deoxygenation system 240 along the fuel line 230. The main fuel pump 254 is operable to move fuel along the fuel line 230. Figure 2 As shown, the main fuel pump 254 can pump or move fuel downstream to one or more fuel loads 234. The fuel load 234 can include any fuel-consuming device, machine, or system. For example, the fuel load 234 can include the burner of the gas turbine engine 210, one or more servo systems, etc. An electric motor 252 is operatively coupled to the main fuel pump 254. For example, the electric motor 252 can be driven by, for example,... Figure 2 The rotatable shaft shown is mechanically connected to the main fuel pump 254. An electric motor 252 is operable to drive the main fuel pump 254. Electricity generated by the generator 224 is supplied to the electric motor 252, for example, via power bus 228. The electric motor 252 can utilize the supplied electricity to drive the main fuel pump 254. In some embodiments, the main fuel pump 254 is an electrically driven variable-speed fuel pump. In this way, a fuel bypass circuit is not required or is minimally required. The speed of the main fuel pump 254 can be varied by controlling the electric motor 252, at least in part, based on the required thrust or output of the gas turbine engine and other factors. A controller or other suitable control device is used to control the output of the electric motor 252 and thus the speed of the main fuel pump 254.

[0032] Furthermore, in this embodiment, the electric motor 252 is operatively connected to the fuel deoxygenation pump 246. For example, the electric motor 252 can be connected via, as... Figure 2 The rotatable shaft shown is mechanically connected to the fuel deoxygenation pump 246. The main fuel pump 254 and the fuel deoxygenation pump 246 may be mechanically connected directly or indirectly to the same shaft or to different shafts mechanically connected to each other. In this regard, the electric motor 252 can use the provided electricity to synchronously drive the main fuel pump 254 and the fuel deoxygenation pump 246. Therefore, the main fuel pump 254 and the fuel deoxygenation pump 246 may be electrically driven pumps. As mentioned above, the main fuel pump 254 may be a variable speed fuel pump. Since both the fuel deoxygenation pump 246 and the main fuel pump 254 are operatively connected to the electric motor 252 in this embodiment, the fuel deoxygenation pump 246 may also be a variable speed fuel pump. In addition to the main fuel pump 254, by utilizing the electric motor 252 to drive the fuel deoxygenation pump 246, the overall package volume and weight of the turbine engine system 200 can be minimized. In some embodiments, in addition to the fuel deoxygenation pump 246, other mechanical components 245 of the fuel deoxygenation system 240 may be operatively connected to and synchronously driven by the electric motor 252. In some embodiments, all rotating mechanical components 245 may be driven by an electric motor 252. In alternative embodiments, the main fuel pump 254 and / or the fuel deoxygenation pump 246 may be mechanically driven pumps.

[0033] The turbine engine system 200 includes one or more heat exchangers. In this embodiment, the turbine engine system 200 includes a plurality of heat exchangers, including an upstream heat exchanger 260 positioned along fuel line 230 upstream of fuel deoxygenation system 240, a first downstream heat exchanger 262 positioned along fuel line 230 downstream of fuel deoxygenation system 240, and a second downstream heat exchanger 264 positioned along fuel line 230 downstream of fuel deoxygenation system 240 and main fuel pump 254. The upstream heat exchanger 260 is positioned along fuel line 230 upstream of the first downstream heat exchanger 262. The first downstream heat exchanger 262 is positioned along fuel line 230 upstream of the second downstream heat exchanger 264.

[0034] The turbine engine system 200 also includes a heat recovery loop 270 along which the working fluid WF can move. The heat recovery loop 270 can be open-loop or closed-loop and can be a single loop or contain multiple loops. The working fluid WF can be any suitable type of working fluid. As an example, the working fluid WF can be oil. Figure 2As shown, the heat recovery circuit 270 is at least partially positioned to have a heat exchange relationship with one or more electrical components 222 of the turbine electrical system 220, such that the one or more electrical components 222 impart thermal energy to the working fluid WF moving along the heat recovery circuit 270. In other words, the heat recovery circuit 270 is positioned such that the working fluid WF flowing along the heat recovery circuit 270 can receive at least a portion of the heat generated by the one or more electrical components 222 of the turbine electrical system 220. As a result, the electrical components 222 of the turbine electrical system 220 can be cooled.

[0035] like Figure 2 As further shown, the heat recovery loop 270 is also at least partially positioned to have a heat exchange relationship with the fuel line 230, such that the working fluid WF imparts heat energy to the fuel moving along the fuel line 230. The heat recovery loop 270 may be positioned to have a heat exchange relationship with the fuel line 230 at various heat exchangers 260, 262, 264. In particular, for this embodiment, the heat recovery loop 270 is at least partially positioned to have a heat exchange relationship with the fuel line 230 at the upstream heat exchanger 260, such that the working fluid WF flowing along the heat recovery loop 270 imparts heat energy to the fuel moving along the fuel line 230 upstream of the fuel deoxygenation system 240. In this way, the fuel can be heated upstream of the fuel deoxygenation system 240. The temperature of the fuel at the inlet of the fuel deoxygenation system 240 is lower than the temperature at which it leaves as deoxygenated fuel at the outlet of the fuel deoxygenation system 240. Compared to imparting heat to the fuel downstream of the fuel deoxygenation system 240, imparting heat to the fuel upstream of the fuel deoxygenation system 240 can achieve a greater temperature rise in the fuel, especially when the heated working fluid WF is a low-mass heat source.

[0036] Furthermore, in this embodiment, the heat recovery loop 270 is at least partially positioned to have a heat exchange relationship with the fuel line 230 at the first downstream heat exchanger 262, such that the working fluid WF imparts heat energy to the fuel moving along the fuel line 230 downstream of the fuel deoxygenation system 240. In this way, the temperature of the fuel can be further increased or better maintained downstream of the fuel deoxygenation system 240 (e.g., by offsetting heat losses). Additionally, in this embodiment, the heat recovery loop 270 is also at least partially positioned to have a heat exchange relationship with the electric motor 252, such that the electric motor 252 imparts heat energy to the working fluid WF moving along the heat recovery loop 270. In this respect, the working fluid WF heated by the heat generated by the electric motor 252 can be guided through the first downstream heat exchanger 262. As described above, the heated working fluid WF imparts heat energy to the fuel moving along the fuel line 230 at the first downstream heat exchanger 262.

[0037] Furthermore, in this embodiment, the heat recovery loop 270 is at least partially positioned to have a heat exchange relationship with the fuel line 230 at the second downstream heat exchanger 264, such that the working fluid WF imparts heat energy to the fuel moving along the fuel line 230 downstream of the fuel deoxygenation system 240 and the main fuel pump 254. In this way, the temperature of the fuel can be further increased or better maintained downstream of the main fuel pump 254 (e.g., by offsetting heat losses). By providing heat to the fuel downstream of the main fuel pump 254, fuel heat loss between the main fuel pump 254 and the fuel load 234 can be minimized. As described above, the heat recovery loop 270 is also at least partially positioned to have a heat exchange relationship with the electric motor 252, such that the electric motor 252 imparts heat energy to the working fluid WF moving along the heat recovery loop 270. In this respect, the working fluid WF heated by the heat generated by the electric motor 252 can be guided through the second downstream heat exchanger 264. As described above, the heated working fluid WF imparts heat energy to the fuel moving along the fuel line 230 at the second downstream heat exchanger 264.

[0038] The architecture of the turbine engine system 200, in which the turbine electric system 220, the main fuel pump system 250, and the fuel deoxygenation system 240 are arranged in a cooperative manner, offers numerous advantages and benefits. For example, the generator 224 of the turbine electric system 220 can provide power to the electrical components 242 of the fuel deoxygenation system 240, including the electric motor 252 driving the main fuel pump 254, and in this embodiment, the fuel deoxygenation pump 246 and / or other mechanical components 245 of the fuel deoxygenation system 240. The generator 224 can also generate power for other electrical loads, such as one or more aircraft systems to which the gas turbine engine 210 is mounted. The turbine electric system 220 can generate and provide power to the fuel deoxygenation system 240 and the main fuel pump system 250 without increasing the size of the generator 224 components or other components of the turbine electric system 220.

[0039] Furthermore, using the fuel deoxygenation system 240 to deoxygenate the fuel allows it to absorb more heat before combustion in the combustor of the gas turbine engine 210, with little or no risk of fuel coking. In this respect, the fuel can act as a radiator to absorb heat generated by components of the turbine electrical system 220 and other engine systems (e.g., the lubrication system). This increased ability of the fuel to absorb heat provides enhanced cooling capacity for one or more electrical components 222 of the turbine electrical system 220 and other systems of the gas turbine engine 210.

[0040] Furthermore, besides the main fuel pump 254, the overall package volume and mass of the turbine engine system 200 can be minimized by utilizing an electric motor 252 to drive one or more mechanical components 245, such as the fuel deoxygenation pump 246. This allows the electric motor 252 to synchronously drive the main fuel pump 254 and the mechanical components 245, such as the fuel deoxygenation pump 246. Moreover, since the main fuel pump 254 is driven by the electric motor 252, the main fuel pump 254 is decoupled from the gas turbine engine 210. Therefore, the main fuel pump 254 can, but is not required to, be synchronized with the speed of the gas turbine engine 210. Furthermore, for electrically driven pumps, minimal or no fuel bypass is needed around the main fuel pump 254. This reduces the mass and package size of the turbine engine system 200.

[0041] Figure 2 The turbine engine system 200 is shown having a specific system architecture according to one example embodiment of this subject matter. However, in other embodiments, the turbine engine system 200 may have other suitable configurations.

[0042] As an example, in some embodiments, the turbine engine system 200 may include an upstream heat exchanger 260 and a first downstream heat exchanger 262, but not a second downstream heat exchanger 264. Thus, in such an embodiment, the heat recovery loop 270 has a heat exchange relationship with the fuel line 230 at the upstream heat exchanger 260 upstream of the fuel deoxygenation system 240 and at the first downstream heat exchanger 262, and therefore with the fuel flowing therein, the first downstream heat exchanger 262 being located downstream of the fuel deoxygenation system 240 and upstream of the main fuel pump 254 along the fuel line 230.

[0043] As another example, in some embodiments, the turbine engine system 200 may include an upstream heat exchanger 260 and a second downstream heat exchanger 264, but not a first downstream heat exchanger 262. Thus, in such an embodiment, the heat recovery loop 270 has a heat exchange relationship with the fuel line 230 upstream of the fuel deoxygenation system 240 at the upstream heat exchanger 260 and at the second downstream heat exchanger 264, and therefore with the fuel flowing therein, the second downstream heat exchanger 264 being located downstream of the fuel deoxygenation system 240 and the main fuel pump 254 along the fuel line 230.

[0044] As yet another example, in some embodiments, the turbine engine system 200 may include a first downstream heat exchanger 262 and a second downstream heat exchanger 264, but not an upstream heat exchanger 260. Thus, in such an embodiment, the heat recovery loop 270 has a heat exchange relationship with the fuel line 230 downstream of the fuel deoxygenation system 240 at the first downstream heat exchanger 262 and at the second downstream heat exchanger 264, and therefore with the fuel flowing therein. The first downstream heat exchanger 262 is located downstream of the fuel deoxygenation system 240 and upstream of the main fuel pump 254 along the fuel line 230, and the second downstream heat exchanger 264 is downstream of the main fuel pump 254 but not upstream of the fuel deoxygenation system 240.

[0045] As another example, in some embodiments, the turbine engine system 200 may include an upstream heat exchanger 260, but not a first downstream heat exchanger 262 or a second downstream heat exchanger 264. Thus, in such an embodiment, the heat recovery loop 270 has a heat exchange relationship with the fuel line 230 upstream of the fuel deoxygenation system 240, rather than downstream of the fuel deoxygenation system 240, and therefore with the fuel flowing therein.

[0046] As yet another example, in some embodiments, the turbine engine system 200 may include a second downstream heat exchanger 264, but not the upstream heat exchanger 260 or the first downstream heat exchanger 262. Thus, in such an embodiment, the heat recovery loop 270 has a heat exchange relationship with the fuel line 230 at the second downstream heat exchanger 264, downstream of the main fuel pump system 250 but not upstream of the fuel deoxygenation system 240 or between the fuel deoxygenation system 240 and the main fuel pump 254, and therefore with the fuel flowing therein.

[0047] As a further example, in some embodiments, the turbine engine system 200 may include a first downstream heat exchanger 262 but not an upstream heat exchanger 260 or a second downstream heat exchanger 264. Thus, in such an embodiment, the heat recovery loop 270 has a heat exchange relationship with the fuel line 230 at the first downstream heat exchanger 262, between the fuel deoxygenation system 240 and the main fuel pump 254 but not upstream of the fuel deoxygenation system 240 or downstream of the main fuel pump 254, and therefore with the fuel flowing therein.

[0048] Figure 3 A schematic system diagram of another turbine engine system 200 according to an example embodiment of this subject is provided. In addition to those provided below, Figure 3 The turbo engine system 200 provided by China is compatible with Figure 2 It is constructed in the same manner shown and described in the accompanying text. Figure 3 The turbine engine system 200 can be installed on or included on the carrier, for example Figure 5 Any of the carriers shown.

[0049] In this embodiment, the fuel deoxygenation system 240 includes a fuel deoxygenation motor 248, which is operatively coupled to one or more mechanical components 245 (e.g., a fuel deoxygenation pump 246). For example, the fuel deoxygenation motor 248 may be mechanically coupled to the fuel deoxygenation pump 246 via a rotatable shaft, such as... Figure 3 As shown. A fuel deoxygenation motor 248 is operable to drive a fuel deoxygenation pump 246. Electricity generated by a generator 224 is supplied to the fuel deoxygenation motor 248, for example, via a power bus 228. The fuel deoxygenation motor 248 can utilize the supplied electricity to drive the fuel deoxygenation pump 246 and other mechanical components 245 operably connected thereto. In some embodiments, the fuel deoxygenation pump 246 is an electrically driven variable-speed fuel pump. The fuel deoxygenation motor 248 can be controlled to change the speed of the fuel deoxygenation pump 246. A controller or other suitable control device is used to control the output of the fuel deoxygenation motor 248, and thus control the speed of the fuel deoxygenation pump 246 and / or other mechanical components 245 connected thereto.

[0050] Therefore, for Figure 3 The turbine engine system 200 shown, including the fuel deoxygenation pump 246 and / or other mechanical components 245 and the main fuel pump 254, is electrically driven by their respective individual motors. At this point, the mechanical components 245, including the fuel deoxygenation pump 246 and the main fuel pump 254, are mechanically separated. Therefore, the fuel deoxygenation pump 246 (and other mechanical components 245) and the main fuel pump 254 can be driven by their respective motors at different speeds. Among other benefits, this allows for customized pumping speed schedules for each pump.

[0051] Figure 4 A schematic system diagram of yet another turbine engine system 200 according to an example embodiment of this subject is provided. In addition to those provided below, Figure 4 The turbo engine system 200 provided by China is compatible with Figure 2 It is constructed in the same manner shown and described in the accompanying text. Figure 4 The turbine engine system 200 can be installed on or included on the carrier, for example Figure 5 Any of the carriers shown.

[0052] As indicated, the turbine engine system 200 includes a turbine electrical system 220 having a gas turbine engine 210 and one or more electrical components 222, the electrical components 222 including a generator 224 operatively coupled to the gas turbine engine 210. The generator 224 is operable to generate electricity. A fuel line 230 supplies fuel to a fuel load 234, such as the combustor of the gas turbine engine 210. A fuel deoxygenation system 240 is located along the fuel line 230 and operable to reduce the amount of oxygen in the fuel. The fuel deoxygenation system 240 is operable to receive electricity from the turbine electrical system 220.

[0053] The turbine engine system 200 also includes a main fuel pump system 250 having a main fuel pump 254 and an electric motor 252 operatively coupled to the main fuel pump 254 to drive it. The main fuel pump 254 is located downstream of the fuel deoxygenation system 240 along the fuel line 230. The electric motor 252 is operable to receive power from the turbine power system 220. Furthermore, the turbine engine system 200 includes an upstream heat exchanger 260 located upstream of the fuel deoxygenation system 240 along the fuel line 230 and at least one downstream heat exchanger located downstream of the fuel deoxygenation system 240 along the fuel line 230. In some embodiments, the downstream heat exchanger is a first downstream heat exchanger 262 located along the fuel line 230 between the fuel deoxygenation system 240 and the main fuel pump 254. In other embodiments, the downstream heat exchanger is a second downstream heat exchanger 264 located downstream of the main fuel pump 254 along the fuel line 230. In such an embodiment, the main fuel pump 254 is located downstream of the fuel deoxygenation system 240. In some embodiments, the turbine engine system 200 may include first and second downstream heat exchangers 262, 264.

[0054] It is worth noting that, in this embodiment, the turbine engine system 200 includes a first heat recovery circuit 270A and a separate second heat recovery circuit 270B. A first working fluid WF1 is movable along the first heat recovery circuit 270A. The first working fluid WF1 can be any suitable type of working fluid. As an example, the first working fluid WF1 can be oil. The first heat recovery circuit 270A is at least partially positioned to have a heat exchange relationship with one or more electrical components 222 of the turbine electrical system 220, such that the one or more electrical components 222 impart heat energy to the first working fluid WF1. The first heat recovery circuit 270A is also at least partially positioned to have a heat exchange relationship with the fuel line 230 at an upstream heat exchanger 260, such that the first working fluid WF1 imparts heat energy to the fuel moving along the fuel line 230.

[0055] The second working fluid WF2 may move along the second heat recovery loop 270B. The second working fluid WF2 can be any suitable type of working fluid. As an example, the second working fluid WF2 can be oil. The second heat recovery loop 270B is at least partially positioned to have a heat exchange relationship with the electric motor 252, such that the electric motor 252 imparts heat energy to the second working fluid WF2. The second heat recovery loop 270B is also at least partially positioned to have a heat exchange relationship with the fuel line 230 at one or more downstream heat exchangers, such that the second working fluid WF2 imparts heat energy to the fuel moving along the fuel line 230. As noted, the second heat recovery loop 270B may be at least partially positioned to have a heat exchange relationship with the fuel line 230 at a first downstream heat exchanger 262, a second downstream heat exchanger 264, or both.

[0056] Advantageously, the electric motor 252 driving the main fuel pump 254 and, in some embodiments, the fuel deoxygenation pump 246 and / or other mechanical components 245, can be positioned relatively close to the fuel line 230 (compared to the electrical components 222 of the turbine power system 220) and can generate a significant amount of heat. A second working fluid WF2 flowing along the second heat recovery loop 270B can recover heat from the electric motor 252, and due to the relatively short physical distance between the electric motor 252 and the fuel line 230 and the significant amount of heat generated by the electric motor 252, the second working fluid WF2 can be a relatively higher quality heat source compared to the first working fluid WF1, which recovers heat from the electrical components 222 of the turbine power system 220. Therefore, in Figure 4 In the illustrated embodiment, a first working fluid WF1, flowing along a first heat recovery loop 270A of the heat source and being of relatively low mass, imparts thermal energy to the fuel upstream of the fuel deoxygenation system 240, maximizing the impact of the recovered relatively low-mass heat source. Furthermore, a second working fluid WF2 (a relatively high-mass heat source compared to the first working fluid WF1), flowing along a second heat recovery loop 270B, imparts thermal energy to the fuel downstream of the fuel deoxygenation system 240. In this way, the recovered relatively high-mass heat source influences the fuel temperature as closely as possible to the fuel load 234, such as the combustor of the gas turbine engine 210.

[0057] Figure 5 An example vehicle 300 according to an exemplary embodiment of this subject matter is provided. The turbine engine system 200 of this disclosure can be implemented on aircraft, helicopters, automobiles, ships, submarines, trains, unmanned vehicles or drones and / or any other suitable vehicle. Although this disclosure is described herein with reference to an aircraft embodiment, it is intended to be illustrative only and not restrictive. Those skilled in the art will understand that the engine system of this disclosure can be implemented on other vehicles without departing from the scope of this disclosure.

[0058] While specific features of various embodiments may be shown in some figures but not in others, this is merely for convenience. Any feature of the figures may be referenced and / or claimed in accordance with the principles of this disclosure, in conjunction with any feature of any other figure.

[0059] This written description uses examples to disclose the invention, including the best mode, and also enables any person skilled in the art to practice the invention, including making and using any device or system and performing any combination of methods. The patent scope of the invention is defined by the claims, but may include other examples that would occur to a person skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

[0060] Other aspects of the invention are provided by the subject matter of the following provisions:

[0061] 1. An engine system comprising: a turbine electric system having a gas turbine engine and one or more electrical components, at least one of the electrical components being operable to generate electricity; a fuel line for supplying fuel to the gas turbine engine; a fuel conditioning system positioned along the fuel line and operable to regulate the fuel, the fuel conditioning system being operable to receive electricity from the turbine electric system; a main fuel pump operable to move fuel along the fuel line; a heat exchanger positioned along the fuel line; and a heat recovery loop, a working fluid being movable along the heat recovery loop, the heat recovery loop being at least partially positioned to have a heat exchange relationship with one or more electrical components of the turbine electric system, such that the one or more electrical components impart thermal energy to the working fluid moving along the heat recovery loop, the heat recovery loop also being at least partially positioned to have a heat exchange relationship with the fuel line at the heat exchanger, such that the working fluid imparts thermal energy to the fuel moving along the fuel line.

[0062] 2. An engine system according to any of the preceding clauses, wherein the heat exchanger is an upstream heat exchanger located upstream of the fuel conditioning system along the fuel line.

[0063] 3. An engine system according to any of the preceding clauses, wherein the heat exchanger is a downstream heat exchanger located downstream of the fuel conditioning system along the fuel line.

[0064] 4. An engine system according to any of the preceding clauses, wherein the heat exchanger is a downstream heat exchanger located downstream of the fuel conditioning system and the main fuel pump along the fuel line.

[0065] 5. An engine system according to any of the preceding clauses, wherein the heat exchanger is an upstream heat exchanger located upstream of the fuel conditioning system along the fuel line, and wherein the engine system further includes: a downstream heat exchanger located downstream of the fuel conditioning system along the fuel line, and wherein a heat recovery loop is at least partially positioned to have a heat exchange relationship with the fuel line at the downstream heat exchanger, such that the working fluid imparts thermal energy to the fuel moving along the fuel line.

[0066] 6. An engine system according to any of the preceding clauses, wherein the downstream heat exchanger is a first downstream heat exchanger located along the fuel line between the fuel conditioning system and the main fuel pump, and wherein the engine system further includes: a second downstream heat exchanger located along the fuel line downstream of the fuel conditioning system and the main fuel pump, and wherein a heat recovery loop is at least partially positioned to have a heat exchange relationship with the fuel line at the second downstream heat exchanger, such that the working fluid imparts thermal energy to the fuel moving along the fuel line.

[0067] 7. For any of the preceding clauses, the fuel conditioning system is a fuel deoxygenation system.

[0068] 8. An engine system according to any of the preceding clauses, wherein the fuel deoxygenation system has one or more heaters, the one or more heaters being operable to impart thermal energy to fuel moving along a fuel line, and wherein power generated by one or more electrical components of a turbine power system is supplied to the one or more heaters.

[0069] 9. An engine system according to any of the preceding clauses, further comprising: an electric motor operatively connected to and operable to drive a main fuel pump, the electric motor operable to receive power from a turbine electrical system, and wherein a fuel deoxygenation system has one or more mechanical components requiring mechanical power, and at least one of the one or more mechanical components is operatively connected to the electric motor.

[0070] 10. An engine system according to any of the preceding clauses, wherein the fuel deoxygenation system has a fuel deoxygenation pump and a fuel deoxygenation motor, the fuel deoxygenation pump being operable to move fuel through the fuel deoxygenation system, the fuel deoxygenation motor being operably connected to and operable to drive the deoxygenation pump, and wherein at least one of one or more electrical components operable to generate electricity generates electricity, which is supplied to the fuel deoxygenation motor.

[0071] 11. An engine system according to any of the preceding clauses, wherein the main fuel pump is a variable speed fuel pump.

[0072] 12. An engine system according to any of the preceding clauses, wherein one or more electrical components include a generator operatively connected to the gas turbine engine.

[0073] 13. An engine system according to any of the preceding clauses, further comprising: an electric motor operatively connected to and operable to drive a main fuel pump, the electric motor operable to receive power from a turbine electrical system, and wherein a heat recovery loop is at least partially positioned to have a heat exchange relationship with the electric motor, such that the electric motor imparts thermal energy to a working fluid moving along the heat recovery loop, and wherein the working fluid heated by the heat generated by the electric motor is guided through a heat exchanger, such that the working fluid heated by the electric motor imparts thermal energy to fuel moving along a fuel line at the heat exchanger.

[0074] 14. An engine system comprising: a turbine electric system having a gas turbine engine and one or more electrical components, the one or more electrical components including a generator operatively coupled to the gas turbine engine, the generator operable to generate electricity; a fuel line for supplying fuel to the gas turbine engine; a fuel deoxygenation system positioned along the fuel line and operable to reduce the amount of oxygen in the fuel, the fuel deoxygenation system operable to receive electricity from the turbine electric system; a main fuel pump positioned downstream of the fuel deoxygenation system along the fuel line and operable to move fuel along the fuel line; a heat exchanger positioned along the fuel line; and a heat recovery loop, a working fluid movable along the heat recovery loop, the heat recovery loop being at least partially positioned to have a heat exchange relationship with one or more electrical components of the turbine electric system, such that one or more electrical components impart thermal energy to the working fluid moving along the heat recovery loop, the heat recovery loop also being at least partially positioned to have a heat exchange relationship with the fuel line at the heat exchanger, such that the working fluid imparts thermal energy to the fuel moving along the fuel line.

[0075] 15. An engine system according to any of the preceding clauses, further comprising: an electric motor operatively connected to and operable to drive a main fuel pump, the electric motor operable to receive power from a turbine electrical system, and wherein the fuel deoxygenation system has a fuel deoxygenation pump operable to move fuel through the fuel deoxygenation system, and wherein the fuel deoxygenation pump is operatively connected to and driven by the electric motor.

[0076] 16. An engine system according to any of the preceding clauses, wherein the fuel deoxygenation system has a fuel deoxygenation pump and a fuel deoxygenation motor, the fuel deoxygenation pump being operable to move fuel through the fuel deoxygenation system, the fuel deoxygenation motor being operably connected to and operable to drive the deoxygenation pump, and wherein at least one of one or more electrical components operable to generate electricity generates electricity, which is supplied to the fuel deoxygenation motor.

[0077] 17. An engine system comprising: a turbine electric system having a gas turbine engine and one or more electrical components, the one or more electrical components including a generator operably coupled to the gas turbine engine, the generator being operable to generate electricity; a fuel line for supplying fuel to the gas turbine engine; a fuel deoxygenation system positioned along the fuel line and operable to reduce the amount of oxygen in the fuel, the fuel deoxygenation system being operable to receive electricity from the turbine electric system; a main fuel pump system having a main fuel pump and an electric motor operably coupled to the main fuel pump to drive the main fuel pump, the main fuel pump being positioned downstream of the fuel deoxygenation system along the fuel line, the electric motor being operable to receive electricity from the turbine electric system; an upstream heat exchanger positioned upstream of the fuel deoxygenation system along the fuel line; and a downstream heat exchanger... The heat exchanger is located downstream of the fuel deoxygenation system along the fuel line; a first heat recovery loop, along which a first working fluid is movable, is at least partially positioned to have a heat exchange relationship with one or more electrical components of the turbine power system, such that the one or more electrical components impart heat energy to the first working fluid, and the first heat recovery loop is also at least partially positioned to have a heat exchange relationship with the fuel line at an upstream heat exchanger, such that the first working fluid imparts heat energy to the fuel moving along the fuel line; and a second heat recovery loop, along which a second working fluid is movable, is at least partially positioned to have a heat exchange relationship with an electric motor, such that the electric motor imparts heat energy to the second working fluid, and the second heat recovery loop is also at least partially positioned to have a heat exchange relationship with the fuel line at a downstream heat exchanger, such that the second working fluid imparts heat energy to the fuel moving along the fuel line.

[0078] 18. An engine system according to any of the preceding clauses, wherein the downstream heat exchanger is located along the fuel line between the fuel deoxygenation system and the main fuel pump.

[0079] 19. An engine system according to any of the preceding clauses, wherein the downstream heat exchanger is located downstream of the main fuel pump along the fuel line.

[0080] 20. An engine system according to any of the preceding clauses, wherein the engine system is mounted on the carrier.

Claims

1. An engine system characterized by, Comprising: a turbine power system having a gas turbine engine and one or more electrical components, at least one of the one or more electrical components being operable to generate electrical power; a fuel line for providing fuel to the gas turbine engine; a fuel deoxygenation system positioned along the fuel line and operable to reduce an amount of oxygen in the fuel, the fuel deoxygenation system being operable to receive electrical power from the turbine power system; a main fuel pump operable to move the fuel along the fuel line; an electric motor operably coupled with the main fuel pump and operable to drive the main fuel pump, the electric motor being operable to receive electrical power from the turbine power system, wherein the electric motor is positioned relatively close to the fuel line and is capable of generating a substantial amount of heat; a heat exchanger positioned along the fuel line, the heat exchanger comprising: an upstream heat exchanger positioned along the fuel line upstream of the fuel deoxygenation system; a downstream heat exchanger positioned along the fuel line downstream of the fuel deoxygenation system; and a heat recovery circuit comprising: a first heat recovery circuit along which a first working fluid is moveable, the first heat recovery circuit being at least partially positioned in heat exchange relationship with the one or more electrical components of the turbine power system such that the one or more electrical components impart thermal energy to the first working fluid moving along the first heat recovery circuit, the first heat recovery circuit being further at least partially positioned in heat exchange relationship with the fuel line at the upstream heat exchanger such that the first working fluid imparts thermal energy to the fuel moving along the fuel line; and a second heat recovery circuit along which a second working fluid is moveable, the second heat recovery circuit being at least partially positioned in heat exchange relationship with the electric motor such that the electric motor imparts thermal energy to the second working fluid, the second heat recovery circuit being further at least partially positioned in heat exchange relationship with the fuel line at the downstream heat exchanger such that the second working fluid imparts thermal energy to the fuel moving along the fuel line.

2. The engine system of claim 1, wherein, wherein the downstream heat exchanger is positioned along the fuel line downstream of the fuel deoxygenation system and the main fuel pump.

3. The engine system of claim 1, wherein, wherein the downstream heat exchanger is a first downstream heat exchanger positioned along the fuel line between the fuel deoxygenation system and the main fuel pump, and wherein the engine system further comprises: a second downstream heat exchanger positioned along the fuel line downstream of the fuel deoxygenation system and the main fuel pump, and wherein the second heat recovery circuit is at least partially positioned in heat exchange relationship with the fuel line at the second downstream heat exchanger such that the second working fluid imparts thermal energy to the fuel moving along the fuel line.

4. The engine system of claim 1, wherein, wherein the fuel deoxygenation system has one or more heaters operable to impart heat energy to the fuel moving along the fuel line, and wherein the one or more heaters are provided with electrical power generated by the one or more electrical components of the turbine power system.

5. The engine system of claim 1, wherein, wherein the fuel deoxygenation system has one or more mechanical components requiring mechanical power, and wherein at least one of the one or more mechanical components is operably coupled with the electric motor.

6. The engine system of claim 1, wherein, wherein the fuel deoxygenation system has a fuel deoxygenation pump operable to move the fuel through the fuel deoxygenation system and a fuel deoxygenation motor operably coupled with the deoxygenation pump and operable to drive the deoxygenation pump, and wherein at least one of the one or more electrical components operable to generate electrical power generates electrical power that is provided to the fuel deoxygenation motor.

7. The engine system of claim 1, wherein, wherein the main fuel pump is a variable speed fuel pump.

8. An engine system characterized by, comprising: a turbine power system having a gas turbine engine and one or more electrical components including an electrical generator operably coupled with the gas turbine engine, the electrical generator being operable to generate electrical power; a fuel line for providing fuel to the gas turbine engine; a fuel deoxygenation system positioned along the fuel line and operable to reduce an amount of oxygen in the fuel, the fuel deoxygenation system being operable to receive electrical power from the turbine power system; a main fuel pump positioned along the fuel line downstream of the fuel deoxygenation system and operable to move the fuel along the fuel line; an electric motor operably coupled with the main fuel pump and operable to drive the main fuel pump, the electric motor being operable to receive electrical power from the turbine power system, wherein the electric motor is positioned relatively close to the fuel line and is capable of generating a substantial amount of heat; a heat exchanger positioned along the fuel line, the heat exchanger comprising: an upstream heat exchanger positioned along the fuel line upstream of the fuel deoxygenation system; a downstream heat exchanger positioned along the fuel line downstream of the fuel deoxygenation system; and a heat recovery circuit comprising: a first heat recovery circuit along which a first working fluid is moveable, the first heat recovery circuit being at least partially positioned in heat exchange relationship with the one or more electrical components of the turbine power system such that the one or more electrical components impart heat energy to the first working fluid moving along the first heat recovery circuit, the first heat recovery circuit being further at least partially positioned in heat exchange relationship with the fuel line at the upstream heat exchanger such that the first working fluid imparts heat energy to the fuel moving along the fuel line; and a second heat recovery circuit along which a second working fluid is moveable, the second heat recovery circuit being at least partially positioned in heat exchange relationship with the electric motor such that the electric motor imparts heat energy to the second working fluid moving along the second heat recovery circuit, the second heat recovery circuit being further at least partially positioned in heat exchange relationship with the fuel line at the downstream heat exchanger such that the second working fluid imparts heat energy to the fuel moving along the fuel line. a second heat recovery circuit along which a second working fluid is moveable, the second heat recovery circuit being at least partially positioned in a heat exchange relationship with the electric motor such that the electric motor imparts thermal energy to the second working fluid, the second heat recovery circuit being further at least partially positioned in a heat exchange relationship with the fuel line at the downstream heat exchanger such that the second working fluid imparts thermal energy to the fuel moving along the fuel line.

9. The engine system of claim 8, wherein, wherein the fuel deoxygenation system has a fuel deoxygenation pump operable to move the fuel through the fuel deoxygenation system, and wherein the fuel deoxygenation pump is operably coupled with and driven by the electric motor.

10. The engine system of claim 8, wherein, wherein the fuel deoxygenation system has a fuel deoxygenation pump operable to move the fuel through the fuel deoxygenation system and a fuel deoxygenation motor operably coupled with and operable to drive the deoxygenation pump, and wherein at least one of the one or more electrical components operable to generate electrical power generates electrical power that is provided to the fuel deoxygenation motor.

11. An engine system characterized by, comprising: a turbine power system having a gas turbine engine and one or more electrical components including a generator operably coupled with the gas turbine engine, the generator being operable to generate electrical power; a fuel line for providing fuel to the gas turbine engine; a fuel deoxygenation system positioned along the fuel line and operable to reduce an amount of oxygen in the fuel, the fuel deoxygenation system being operable to receive electrical power from the turbine power system; a main fuel pump system having a main fuel pump positioned along the fuel line downstream of the fuel deoxygenation system and an electric motor operably coupled with the main fuel pump to drive the main fuel pump, the electric motor being operable to receive electrical power from the turbine power system, wherein the electric motor is positioned relatively close to the fuel line and is capable of generating a substantial amount of heat; an upstream heat exchanger positioned along the fuel line upstream of the fuel deoxygenation system; a downstream heat exchanger positioned along the fuel line downstream of the fuel deoxygenation system; a first heat recovery circuit along which a first working fluid is moveable, the first heat recovery circuit being at least partially positioned in a heat exchange relationship with the one or more electrical components of the turbine power system such that the one or more electrical components impart thermal energy to the first working fluid, the first heat recovery circuit being further at least partially positioned in a heat exchange relationship with the fuel line at the upstream heat exchanger such that the first working fluid imparts thermal energy to the fuel moving along the fuel line; and and a second heat recovery circuit along which a second working fluid is moveable, the second heat recovery circuit being positioned at least partially in a heat exchange relationship with the electric motor such that the electric motor imparts thermal energy to the second working fluid, the second heat recovery circuit being further positioned at least partially in a heat exchange relationship with the fuel line at the downstream heat exchanger such that the second working fluid imparts thermal energy to the fuel moving along the fuel line.

12. The engine system of claim 11, wherein, wherein the downstream heat exchanger is positioned along the fuel line between the fuel deoxygenation system and the main fuel pump.

13. The engine system of claim 11, wherein, wherein the downstream heat exchanger is positioned along the fuel line downstream of the main fuel pump.

14. The engine system of claim 11, wherein, wherein the engine system is mounted to a vehicle. wherein the engine system is mounted to a vehicle.

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