Thermal management system

A thermal management system includes a first heat source assembly including a first heat source exchanger, a first thermal fluid inlet line extending to the first heat source exchanger, and a first thermal fluid outlet line extending from the first heat source exchanger; a second heat source assembly including a second heat source exchanger, a second thermal fluid inlet line extending to the second heat source exchanger, and second a thermal fluid outlet line extending from the second heat source exchanger; a shared assembly including a thermal fluid line and a heat sink exchanger, the shared assembly defining an upstream junction in fluid communication with the first thermal fluid outlet line and second thermal fluid outlet line and a downstream junction in fluid communication with the first thermal fluid inlet line and second thermal fluid inlet line; and a controller configured to selectively fluidly connect the first heat source assembly or the second heat source assembly to the shared assembly.

FIELD

The present subject matter relates generally to a thermal management system and a method for operating the same.

BACKGROUND

A gas turbine engine typically includes a fan and a turbomachine. The turbomachine generally includes an inlet, one or more compressors, a combustor, and at least one turbine. The compressors compress air which is channeled to the combustor where it is mixed with fuel. The mixture is then ignited for generating hot combustion gases. The combustion gases are channeled to the turbine(s) which extracts energy from the combustion gases for powering the compressor(s), as well as for producing useful work to propel an aircraft in flight and/or to power a load, such as an electrical generator.

In at least certain embodiments, the turbomachine and fan are at least partially surrounded by an outer nacelle. With such embodiments, the outer nacelle defines a bypass airflow passage with the turbomachine. Additionally, the turbomachine is supported relative to the outer nacelle by one or more outlet guide vanes/struts. During operation of the gas turbine engine, various systems may generate a relatively large amount of heat. Thermal management systems of the gas turbine engine may collect heat from one or more of these systems to maintain a temperature of such systems within an acceptable operating range. The thermal management systems may reject such heat through one or more heat exchangers.

However, the inventors of the present disclosure have found that further benefits may be achieved by operating the thermal management system to selectively add or remove heat from various systems or locations of the gas turbine engine. Accordingly, a system and/or method for operating a thermal management system in a manner to increase an efficiency of the gas turbine engine would be useful.

BRIEF DESCRIPTION

In one exemplary aspect of the present disclosure, a gas turbine engine is provided. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section arranged in series flow; and a thermal management system operable with at least one of the compressor section, the combustion section, the turbine section, or the exhaust section. The thermal management system includes a first heat source assembly including a first heat source exchanger, a first thermal fluid inlet line extending to the first heat source exchanger, and a first thermal fluid outlet line extending from the first heat source exchanger; a second heat source assembly including a second heat source exchanger, a second thermal fluid inlet line extending to the second heat source exchanger, and second a thermal fluid outlet line extending from the second heat source exchanger; a shared assembly including a thermal fluid line and a heat sink exchanger, the shared assembly defining an upstream junction in fluid communication with the first thermal fluid outlet line and second thermal fluid outlet line and a downstream junction in fluid communication with the first thermal fluid inlet line and second thermal fluid inlet line; and a controller configured to selectively fluidly connect the first heat source assembly or the second heat source assembly to the shared assembly.

In certain exemplary embodiments the first heat source exchanger is a cooled cooling air heat source exchanger, and wherein the second heat source exchanger is a waste heat recovery heat source exchanger in thermal communication with the turbine section, the exhaust section, or both.

In certain exemplary embodiments the first heat source exchanger is a waste heat recovery heat source exchanger, or a lubrication oil heat source exchanger.

In certain exemplary embodiments the heat sink exchanger of the shared assembly is a fuel heat sink exchanger, a bypass passage heat sink exchanger, a compressor discharge heat sink exchanger, a ram air heat sink exchanger, or a free stream heat sink exchanger.

In certain exemplary embodiments the thermal management system includes a valve positioned at the upstream junction of the shared assembly or at the downstream junction of the shared assembly, and wherein the controller is operably coupled to the valve for selectively fluidly connecting the first heat source assembly or the second heat source assembly to the shared assembly.

In certain exemplary embodiments the shared assembly includes a thermal fluid pump for providing a flow of thermal fluid through the shared assembly and the first heat source assembly when the controller fluidly connects the shared assembly to the first heat source assembly, and through the shared assembly and the second heat source assembly when the controller fluidly connects the shared assembly to the second heat source assembly.

In certain exemplary embodiments the thermal management system is configured to utilize a supercritical thermal transfer fluid, and wherein the shared assembly includes a supercritical thermal fluid pump for providing a flow of supercritical thermal fluid through the shared assembly and the first heat source assembly when the controller fluidly connects the shared assembly to the first heat source assembly, and through the shared assembly and the second heat source assembly when the controller fluidly connects the shared assembly to the second heat source assembly.

In certain exemplary embodiments the shared assembly includes a turbine in flow communication with the thermal fluid line for extracting energy from a thermal fluid flow through the thermal fluid line of the shared assembly.

In certain exemplary embodiments the gas turbine engine further includes one or more sensors for sensing data indicative of one or more parameters of the gas turbine engine, wherein the controller of the thermal management system is operably coupled to the one or more sensors, and wherein the controller is configured to selectively fluidly connect the first heat source assembly or the second heat source assembly to the shared assembly in response to the data sensed by the one or more sensors.

In certain exemplary embodiments the first heat source assembly defines a first maximum thermal fluid throughput, wherein the second heat source assembly defines a second maximum thermal fluid throughput, wherein the shared assembly defines a third maximum thermal fluid throughput, wherein the first maximum thermal fluid throughput is substantially equal to the second maximum thermal fluid throughput, and wherein the second maximum thermal fluid throughput is substantially equal to the third maximum thermal fluid throughput.

In an exemplary aspect of the present disclosure, a method is provided of operating a thermal management system for a gas turbine engine. The method includes providing a thermal transfer fluid through a shared assembly of the thermal management system and to a first heat source assembly of the thermal management system, the shared assembly including a heat sink exchanger; sensing data indicative of a gas turbine engine operating parameter; and providing the thermal transfer fluid through the shared assembly of the thermal management system and to a second heat source assembly of the thermal management system in response to sensing data indicative of the gas turbine engine parameter.

In certain exemplary aspects sensing data indicative of the gas turbine engine parameter includes sensing data indicative of a temperature parameter of the gas turbine engine.

For example, in certain exemplary aspects sensing data indicative of the temperature parameter of the gas turbine engine includes sensing data indicative of the temperature parameter passing a predetermined threshold.

In certain exemplary aspects providing the thermal transfer fluid through the shared assembly of the thermal management system and to the first heat source assembly of the thermal management system includes providing substantially all of the thermal transfer fluid from the shared assembly of the thermal management system to the first heat source assembly of the thermal management system.

For example, in certain exemplary aspects providing the thermal transfer fluid through the shared assembly of the thermal management system and to the second heat source assembly of the thermal management system includes providing substantially all of the thermal transfer fluid from the shared assembly of the thermal management system to the second heat source assembly of the thermal management system.

In certain exemplary aspects providing the thermal transfer fluid through the shared assembly of the thermal management system and to the second heat source assembly of the thermal management system includes actuating a valve positioned at an upstream junction of the shared assembly or at a downstream junction of the shared assembly to divert the flow of thermal transfer fluid.

In certain exemplary aspects the method further includes increasing a pressure, a flow rate, or both of the thermal transfer fluid through the shared assembly using a thermal fluid pump of the shared assembly in fluid communication with a thermal fluid line of the shared assembly.

In certain exemplary aspects sensing data indicative of the gas turbine engine parameter includes sensing data indicative of an operating condition of the gas turbine engine.

In certain exemplary aspects the first heat source assembly includes a heat source heat exchanger thermally coupled to a cooled cooling air system of the gas turbine engine, and wherein the second heat source assembly includes a waste heat recovery heat source exchanger thermally coupled to a turbine section of the gas turbine engine, an exhaust section of the gas turbine engine, or both.

In certain exemplary aspects providing the thermal transfer fluid through the shared assembly of the thermal management system and to the first heat source assembly of the thermal management system includes preventing a flow of thermal transfer fluid through the second heat source assembly, and wherein providing the thermal transfer fluid through the shared assembly of the thermal management system and to the second heat source assembly of the thermal management system includes preventing a flow of thermal transfer fluid through the first heat source assembly.

DETAILED DESCRIPTION

Referring now to the drawings, wherein identical numerals indicate the same elements throughout the figures,FIG. 1is a schematic, cross-sectional view of a gas turbine engine in accordance with an exemplary embodiment of the present disclosure. More particularly, for the embodiment ofFIG. 1, the gas turbine engine is a high-bypass turbofan jet engine10, referred to herein as “turbofan engine10.” As shown inFIG. 1, the turbofan engine10defines an axial direction A (extending parallel to a longitudinal centerline12provided for reference) and a radial direction R. In general, the turbofan engine10includes a fan section14and a turbomachine16disposed downstream from the fan section14.

For the embodiment depicted, the fan section14includes a variable pitch fan38having a plurality of fan blades40coupled to a disk42in a spaced apart manner. As depicted, the fan blades40extend outwardly from disk42generally along the radial direction R. Each fan blade40is rotatable relative to the disk42about a pitch axis P by virtue of the fan blades40being operatively coupled to a suitable actuation member44configured to collectively vary the pitch of the fan blades40in unison. The fan blades40, disk42, and actuation member44are together rotatable about the longitudinal axis12by LP shaft36across a power gear box46. The power gear box46includes a plurality of gears for stepping down the rotational speed of the LP shaft36to a more efficient rotational fan speed.

During operation of the turbofan engine10, a volume of air58enters the turbofan10through an associated inlet60of the nacelle50and/or fan section14. As the volume of air58passes across the fan blades40, a first portion of the air58as indicated by arrows62is directed or routed into the bypass airflow passage56and a second portion of the air58as indicated by arrow64is directed or routed into the LP compressor22. The ratio between the first portion of air62and the second portion of air64is commonly known as a bypass ratio.

The pressure of the second portion of air64is then increased as it is routed through the high pressure (HP) compressor24and into the combustion section26, where it is mixed with fuel and burned to provide combustion gases66. Subsequently, the combustion gases66are routed through the HP turbine28and the LP turbine30, where a portion of thermal and/or kinetic energy from the combustion gases66is extracted.

The combustion gases66are then routed through the jet exhaust nozzle section32of the turbomachine16to provide propulsive thrust. Simultaneously, the pressure of the first portion of air62is substantially increased as the first portion of air62is routed through the bypass airflow passage56before it is exhausted from a fan nozzle exhaust section76of the turbofan10, also providing propulsive thrust.

Further, the exemplary turbofan engine10includes a controller82operably connected at least to one or more engine sensors84. The one or more engine sensors84may be configured to sense data indicative of parameters of the turbofan engine10(the term “parameter” with respect to such turbofan engine10broadly referring to, e.g., one or more of a compressor exit pressure and/or temperature, a turbine inlet temperature, a rotational speed of the high speed components/HP shaft34, a rotational speed of the low pressure components/LP shaft36, etc., as well as a flight schedule parameter, such as throttle position, altitude, flight phase, etc.). The controller82may also be configured to receive data, such as command data, from one or more users or operators of the turbofan engine10(such as a pilot). Based on this data received indicative of the parameters, either by the users or operators, or by the one or more sensors84, the controller82may be configured to determine various gas turbine engine operating parameters, and/or an operating condition of the turbofan engine10, such as a climb operating condition, a cruise operating condition, an idle operating condition, etc. The controller82may be configured in the same manner as the exemplary control system/controller108described below with reference toFIG. 2.

Moreover, it will be appreciated that the exemplary turbofan engine10further includes various accessory systems to aid in the operation of the turbofan engine10and/or an aircraft including the turbofan engine10. For example, the exemplary turbofan engine10further includes a cooled cooling air (CCA) system80(sometimes also referred to as a “compressor cooling air system”) for cooling air from one or both of the HP compressor24or LP compressor22, and providing such cooled air to one or both of the HP turbine28or LP turbine30, or alternatively to an aft portion of the HP compressor24. For example, the cooled cooling air system80may include a cooling duct and a heat exchanger for providing such functionality (see, e.g.,FIG. 3, below).

In addition, the exemplary turbofan engine10depicted inFIG. 1includes a fuel delivery system86for providing a fuel flow to the combustion section26of the turbomachine16and a lubrication oil system88. For the embodiment shown, the fuel delivery system86generally includes a fuel tank90, one or more fuel lines92extending from the fuel tank90to the combustion section26, and a fuel pump94positioned in flow communication with the one or more fuel lines92for increasing a pressure and/or flow rate of the fuel flow therethrough. Further, it will be appreciated that the lubrication oil system88of the exemplary turbofan engine10may be configured in a similar manner to known systems, whereby the lubrication oil system88provides a lubrication oil to one or more bearings of the turbofan engine10, lubricating such bearings, and reducing a temperature of such bearings. For example, the lubrication oil system88may include one or more pumps, tanks, etc., labeled generally as numeral89, to facilitate such functionality.

Prior turbofan engines10and/or aircraft have included individual heat exchangers for each of these accessory systems to remove heat from, e.g., air and/or lubrication in such systems. However, aspects of the present disclosure may include a thermal management system100(seeFIG. 2) for transferring heat from such accessory systems selectively based, e.g., on an engine parameter or engine operating condition, to more efficiently remove such heat and/or utilize such heat and more efficiently utilize the components included (e.g., the heat sink heat exchangers). In such a manner, as will be explained further below, the turbofan engines10may operate these components of the thermal management system100on an “as needed” basis and may not require redundant components for doing so.

It should be appreciated, however, that the exemplary turbofan engine10depicted inFIG. 1is by way of example only, and that in other exemplary embodiments, aspects of the present disclosure may additionally, or alternatively, be applied to any other suitable gas turbine engine. For example, in other exemplary embodiments, the turbofan engine10may include any suitable number of compressors, turbines (such as an intermediate turbine in addition to an LP and HP turbine), shafts/spools (e.g., two spools, three spools), etc. Further, in certain exemplary embodiments, aspects of the present disclosure may further apply to any other suitable aeronautical gas turbine engine, such as a turbojet engine, turboshaft engine, turboprop engine, etc., whether operated as a subsonic gas turbine engine (i.e., configured to operate mainly at subsonic flight speeds) or as a supersonic gas turbine engine (i.e., configured to operate mainly at supersonic flight speeds). Additionally, in still other exemplary embodiments, the exemplary turbofan engine10may include or be operably connected to any other suitable accessory systems. Additionally, or alternatively, the exemplary turbofan engine10may not include or be operably connected to one or more of the accessory systems discussed above.

Referring now toFIG. 2, a schematic diagram is provided of a thermal management system100in accordance with an exemplary embodiment of the present disclosure for incorporation at least partially into a gas turbine engine, such as the exemplary turbofan engine10ofFIG. 1. More specifically, although depicted in isolation from a gas turbine engine inFIG. 2, it will be appreciated that the exemplary thermal management system100is operable with at least one of a compressor section, a combustion section (such as combustion section26ofFIG. 1), a turbine section, or an exhaust section (such as exhaust section32ofFIG. 1) of the gas turbine engine within which it is installed (see also, e.g.,FIG. 3).

As shown, the thermal management system100generally includes a first heat source assembly102, a second heat source assembly104, a shared assembly106and a controller108. Each of these aspects is described in greater detail below.

For the embodiment shown, the first heat source assembly102includes a first heat source exchanger110, a first thermal fluid inlet line112extending to the first heat source exchanger110, and a first thermal fluid outlet line114extending from the first heat source exchanger110. In such a manner, when a thermal fluid flow is directed to the first heat source assembly102, such thermal fluid flow may be received through the first thermal fluid inlet line112, provided to the first heat source exchanger110from the first of thermal fluid inlet line112, and subsequently provided to the first thermal fluid outlet line114from the first heat source exchanger110.

Similarly for the embodiment shown, the second heat source assembly104includes a second heat source exchanger116, a second thermal fluid inlet line118extending to the second heat source exchanger116, and a second thermal fluid outlet line120extending from the second heat source exchanger116. In such a manner, when a thermal fluid flow is directed to the second heat source assembly104, such thermal fluid flow may be received through the second thermal fluid inlet line118, provided to the second heat source exchanger116from the second of thermal fluid inlet line118, and subsequently provided to the second thermal fluid outlet line120from the second heat source exchanger116.

As will be discussed below, e.g., with reference toFIGS. 3 and 4, the first heat source exchanger110and second heat source exchanger116may each be thermally coupled to one or more components of the gas turbine engine with which the thermal management system100is installed. For example, referring briefly back toFIG. 1, in at least certain exemplary embodiments the first heat source exchanger110and/or the second heat source exchanger116may be configured as a waste heat recovery heat source exchanger (such as an exhaust waste heat recovery heat source exchanger in thermal communication with a turbine section, an exhaust section32, or both, or alternatively as an under-cowl waste heat recovery heat source exchanger in thermal communication with an area underneath a cowling18of the turbomachine16and radially outward of a core air flowpath37of the turbomachine16), a lubrication oil heat source exchanger (e.g., in thermal communication with a lubrication oil system88), a cooled cooling air heat source exchanger (e.g., in thermal communication with a cooled cooling air system80), etc.

Referring still toFIG. 2, the shared assembly106of the exemplary thermal management system100includes a thermal fluid line120and a heat sink exchanger122thermally coupled to the thermal fluid line120. The heat sink exchanger122of the shared assembly106of the thermal management system100may be thermally coupled to any suitable heat sink of the gas turbine engine. For example, referring again briefly back toFIG. 1, and as will be described in greater detail below with reference to, e.g.,FIGS. 3 and 4, in at least certain exemplary aspects the heat sink exchanger122of the shared assembly106may be configured as a fuel heat sink exchanger (e.g., in thermal communication with a fuel delivery system86), a bypass passage heat sink exchanger (e.g., in thermal communication with an airflow through a bypass passage56), a compressor discharge heat sink exchanger (e.g., in thermal communication with a downstream section of a compressor section), a ram air heat sink exchanger (e.g., in thermal communication with a ram airflow of the aircraft or gas turbine engine, such as in a military aircraft or engine), or a free stream heat sink exchanger (such as of a three stream gas turbine engine typically found in military applications), etc.

Additionally, in certain exemplary embodiments, the shared assembly106may include a plurality of heat sink exchangers122arranged in series, parallel, or a combination thereof. With such a configuration, e.g., wherein the shared assembly106includes a plurality of heat sink exchangers122, the system100may further be configured to bypass one or more of the heat sink exchangers122based on an operating condition of the aircraft or engine. For example, the system100may bypass a fan stream heat sink exchanger during high fuel flow rate conditions (e.g., takeoff or climb conditions) such that a fuel heat sink exchanger receives a majority of the heat, and further at relatively low fuel flow rate conditions (e.g., descent or idle conditions) may either bypass the fuel heat sink exchanger or may utilize the fuel heat sink exchanger and the fan stream heat sink exchanger (or other secondary heat sink exchanger).

Further, referring toFIG. 2, the exemplary thermal fluid line120generally extends between, and defines at least in part, an upstream junction124and a downstream junction126. The upstream junction124, or rather, the thermal fluid line120of the shared assembly106at the upstream junction124, is in fluid communication with the first thermal fluid outlet line114and the second thermal fluid outlet line120. Further, the downstream junction126, or rather, the thermal fluid line120of the shared assembly106at the downstream junction126, is in fluid communication with the first thermal fluid inlet line112and the second thermal fluid inlet line118. In such a manner, it will be appreciated that during operation, a thermal fluid flow may be provided to the thermal fluid line120of the shared assembly106at the upstream junction124from the first thermal fluid outlet line114, the second thermal fluid outline, or both. Similarly, the thermal fluid flow through thermal fluid line120of the shared assembly106may be provided to the first thermal fluid inlet line112, the second thermal fluid inlet line118, or both, at the downstream junction126.

More specifically, for the embodiment shown, the thermal management system100includes a valve positioned at the upstream junction124of the shared assembly106or at the downstream junction126of the shared assembly106. As will be explained in greater detail below, the controller108is operably coupled to the valve for selectively fluidly connecting the first heat source assembly102or the second heat source assembly104to the shared assembly106. More specifically, still, for the embodiment shown the thermal management system100includes a first valve128positioned at the upstream junction124and a second valve130positioned at the downstream junction126. In such a manner, it will be appreciated that the first valve128is fluidly coupled to the first thermal fluid outlet line114(at a first inlet), the second thermal fluid outlet line120(at a second inlet), and the thermal fluid line120of the shared assembly106(at an outlet); and the second valve130is fluidly coupled to the thermal fluid line120of the shared assembly106(at an inlet), the first thermal fluid inlet line112(at a first outlet), and the second thermal fluid inlet line118(at a second outlet).

Each of the first valve128and the second valve130is, for the embodiment shown, operably coupled to the controller108, such that the controller108may actuate the first valve128, the second valve130, or both, to selectively fluidly connect the first heat source assembly102or the second heat source assembly104to the shared assembly106. In such a manner, it will be appreciated that the first valve128, the second valve130, or both, may be variable throughput valves capable of varying a fluid flow, e.g., from two inputs to a single output (e.g., the first valve128), or from a single input between two outputs (e.g., the second valve130). In certain exemplary embodiments the first valve128or the second valve130may be configured to vary a thermal fluid flow between two inlets (e.g., first valve128) or two outlets (e.g., second valve130) at a ratio of 1:0 (i.e., 100% through a first inlet/outlet and 0% through a second inlet/outlet) and 0:1. Additionally, or alternatively, the first valve128or the second valve130may be configured to vary the ratio of thermal fluid flow to one or more intermediate positions.

Referring back to the other operations and features of the thermal management system100and referring still toFIG. 2, it will be appreciated that for the embodiment shown, thermal management system100is configured to operate in a loop consisting essentially of the first heat source assembly102and the shared assembly106, or alternatively in a loop consisting essentially of the second heat source assembly104and the shared assembly106. In such a manner, the thermal management system100may not be configured to fully operate the first heat source assembly102and second heat source assembly104simultaneously. More specifically, for the embodiment shown, the first heat source assembly102defines a first maximum thermal fluid throughput, the second heat source assembly104defines a second maximum thermal fluid throughput, and the shared assembly106defines a third maximum thermal fluid throughput. The first maximum thermal fluid throughput may be set by a diameter of the first thermal fluid inlet line112, a diameter of the first thermal fluid outlet line114, one or more flow characteristics of the first heat source exchanger110, or a combination thereof. Similarly, the second maximum thermal fluid throughput may be set by a diameter of the second thermal fluid inlet line118, a diameter of the second thermal fluid outlet line120, one or more flow characteristics of the second heat source exchanger110, or a combination thereof. Further, the third maximum thermal fluid throughput may be set by a diameter of the thermal fluid line120, one or more flow characteristics of the heat sink exchanger122, or a combination thereof.

For the embodiment depicted, the first maximum thermal fluid throughput is substantially equal to the second maximum thermal fluid throughput, and the second maximum thermal fluid throughput is substantially equal to the third maximum thermal fluid throughput. In such a manner, the shared assembly106of the thermal management system100may be configured to operate fully with the first heat source assembly102, or alternatively fully with the second heat source assembly104, but not fully with the first heat source assembly102and the second heat source assembly104.

Moreover, it will further be appreciated that for the embodiment depicted inFIG. 2, the shared assembly106further includes a thermal fluid pump132and a turbine134. The thermal fluid pump132is configured to provide a flow of thermal fluid through the first heat source assembly102and the shared assembly106when the shared assembly106is fluidly coupled to the first heat source assembly102(by the controller108, as will be explained below). Similarly, the thermal fluid pump132is configured to provide a flow of thermal fluid through the second heat source assembly104and the shared assembly106when the shared assembly106is fluidly coupled to the second heat source assembly104(again by the controller108, as will be explained below).

More specifically, still, for the embodiment shown the thermal management system100is configured to utilize a supercritical thermal transfer fluid, and the thermal fluid pump132of the shared assembly106is a supercritical thermal fluid pump. For example, the thermal management system100may utilize a supercritical CO2, or other supercritical thermal fluid. Utilization of a supercritical thermal fluid my allow for more efficient heat transfer with the thermal management system100. Further, since the thermal management system100utilizes shared assets (i.e., the shared assembly106) between the first and second heat source assemblies102,104, the thermal management system100may more fully utilize the more efficient heat transfer features throughout an entire flight envelope.

Alternatively, however, in other embodiments, the thermal management system100utilize any other suitable thermal transfer fluid. For example, in other embodiments, the thermal management system100may utilize a single phase thermal transfer fluid (configured to remain substantially in e.g., a liquid phase throughout operations), a phase change thermal transfer fluid, etc. For example, the thermal transfer fluid may be an oil, refrigerant, etc.

Further, as noted above, the exemplary shared assembly106includes a turbine134. The turbine134may be configured to extract energy from the thermal transfer fluid flow through the shared assembly106, and more specifically, through the thermal fluid line120of the shared assembly106. In certain exemplary embodiments, the turbine134may expand the thermal transfer fluid through such extraction of energy/rotational energy therefrom, and transfer such energy to, e.g., an electric machine to generate electrical power. Additionally, or alternatively, the turbine134may in other embodiments be mechanically coupled to the thermal fluid pump132, such that the pump132is configured as a turbopump.

Notably, it will be appreciated that for the embodiment shown, the thermal fluid pump132is positioned upstream of the heat sink exchanger122, and the heat sink exchanger122is positioned upstream of the turbine134, all within the shared assembly106, and more particularly, along the thermal fluid line120of the shared assembly106. In such a manner, it will be appreciated that the thermal fluid pump132may increase a pressure, a flowrate, and/or a temperature of the thermal transfer fluid, allowing for increased thermal transfer from the thermal fluid through the heat sink exchanger122to a particular heat sink. Further, the turbine134being positioned downstream of the heat sink exchanger122may further reduce the temperature of the thermal transfer fluid through the shared assembly106, prior to such thermal transfer fluid being utilized to accept heat from the first heat source assembly102, the second heat source assembly104, or both. Such may further increase an efficiency of the thermal management system100.

It should be appreciated, however, that in other exemplary embodiments, the thermal management system100may be configured in any other suitable manner. For example, in other embodiments, the pump132, heat sink exchanger122, and turbine134may be arranged in any other suitable flow order. Further, in other embodiments the shared assembly106may not include each of the features depicted, such as the turbine134, one of the valves128,130, etc.

Referring still toFIG. 2, as briefly noted above, the gas turbine engine, the thermal management system100, or both, further includes a plurality of sensors operably coupled to the controller108. The one or more sensors may include one or more gas turbine engine sensors84configured to sense data indicative of, e.g., operating conditions and/or operating parameters of the gas turbine engine, as well as one or more thermal management system sensors. Specifically, for the embodiment shown, the thermal management system100includes a first sensor136operable with the first heat source assembly102, a second sensor138operable with the second heat source assembly104, and a third sensor140and a fourth sensor142operable with the shared assembly106. The first sensor136may sense data indicative of a flow rate, a pressure, and/or a temperature of a thermal fluid flow through the first heat source assembly102; the second sensor138may similarly sense data indicative of a flow rate, a pressure, and/or a temperature of a thermal fluid flow through the second heat source assembly104; and the third sensor140and fourth sensor142may sense data indicative of a flow rate, a pressure, and/or a temperature of a thermal fluid flow through the shared assembly106.

As noted, the exemplary controller108depicted inFIG. 2is configured to receive the data sensed from the one or more sensors (sensors84,136,138,140,142for the embodiment shown) and, e.g., may make control decisions for the thermal management system100based on the received data.

In one or more exemplary embodiments, the controller108depicted inFIG. 2may be a stand-alone controller108for the thermal management system100, or alternatively, may be integrated into one or more of a controller for the gas turbine engine with which the thermal management system100is integrated, a controller for an aircraft including the gas turbine engine with which the thermal management system100is integrated, etc.

Referring particularly to the operation of the controller108, in at least certain embodiments, the controller108can include one or more computing device(s)144. The computing device(s)144can include one or more processor(s)144A and one or more memory device(s)144B. The one or more processor(s)144A can include any suitable processing device, such as a microprocessor, microcontroller, integrated circuit, logic device, and/or other suitable processing device. The one or more memory device(s)144B can include one or more computer-readable media, including, but not limited to, non-transitory computer-readable media, RAM, ROM, hard drives, flash drives, and/or other memory devices.

The one or more memory device(s)144B can store information accessible by the one or more processor(s)144A, including computer-readable instructions144C that can be executed by the one or more processor(s)144A. The instructions144C can be any set of instructions that when executed by the one or more processor(s)144A, cause the one or more processor(s)144A to perform operations. In some embodiments, the instructions144C can be executed by the one or more processor(s)144A to cause the one or more processor(s)144A to perform operations, such as any of the operations and functions for which the controller108and/or the computing device(s)144are configured, the operations for operating a thermal management system100(e.g, method200), as described herein, and/or any other operations or functions of the one or more computing device(s)144. The instructions144C can be software written in any suitable programming language or can be implemented in hardware. Additionally, and/or alternatively, the instructions144C can be executed in logically and/or virtually separate threads on processor(s)144A. The memory device(s)144B can further store data144D that can be accessed by the processor(s)144A. For example, the data144D can include data indicative of power flows, data indicative of engine/aircraft operating conditions, and/or any other data and/or information described herein.

The computing device(s)144can also include a network interface144E used to communicate, for example, with the other components of the thermal management system100, the gas turbine engine incorporating thermal management system100, the aircraft incorporating the gas turbine engine, etc. For example, in the embodiment depicted, as noted above, the gas turbine engine and/or thermal management system100includes one or more sensors for sensing data indicative of one or more parameters of the gas turbine engine, the thermal management system100, or both. The controller108the thermal management system100is operably coupled to the one or more sensors through, e.g., the network interface, such that the controller108may receive data indicative of various operating parameters sensed by the one or more sensors during operation. Further, for the embodiment shown the controller108is operably coupled to, e.g., the first valve128and the second valve130. In such a manner, the controller108may be configured to selectively fluidly connect the first heat source assembly102or the second heat source assembly104to the shared assembly106(i.e., through actuation of the first valve128, the second valve130, or both) in response to, e.g., the data sensed by the one or more sensors.

The network interface144E can include any suitable components for interfacing with one or more network(s), including for example, transmitters, receivers, ports, controllers, antennas, and/or other suitable components.

Referring now toFIG. 3, a simplified, schematic view of a gas turbine engine10including a thermal management system100in accordance with an exemplary aspect of the present disclosure is depicted. The exemplary thermal management system100ofFIG. 3may be configured in substantially the same manner as the exemplary thermal management system100ofFIG. 2, and the exemplary gas turbine10depicted inFIG. 3may be configured in substantially the same manner as the exemplary turbofan engine10described above with reference toFIG. 1, or in accordance with any other suitable gas turbine engine (e.g., a turbofan engine having any other suitable configuration, a turboshaft engine, a turboprop engine, a turbojet engine, etc.).

The exemplary gas turbine engine10ofFIG. 3generally includes a fan section14and a turbomachine16. The turbomachine16includes in serial flow order a compressor section having an LP compressor22and an HP compressor24, a combustion section26, a turbine section including an HP turbine28and an LP turbine30, and an exhaust section32. Moreover, the turbomachine16and fan section14are at least partially surrounded by an outer nacelle50, with the turbomachine16supported relative to the outer nacelle50through a plurality of outlet guide vanes52. The outer nacelle50defines a bypass airflow passage56with the turbomachine16. A first portion62of an airflow from the fan section14is provided through the turbomachine16as a core airflow, and a second64portion of the airflow from the fan section14is provided through the bypass airflow passage56as a bypass airflow.

In addition, the gas turbine engine10includes a cooled cooling air system80(sometimes also referred to as a “compressor cooling air system”) for providing air from one or both of the HP compressor24or LP compressor22, cooling such air, and providing such air to one or both of the HP turbine28or LP turbine30during operation of the gas turbine engine10(or alternatively to an aft portion of the HP compressor24). The cooling air system80includes one or more cooling passages81for ducting air from the compressor section to the turbine section, such that the cooling air system80may cool one or more components of the turbine section.

Further, the thermal management system100generally includes a first heat source assembly102, a second heat source assembly104, a shared assembly106, and a controller108. As discussed in greater detail above with reference toFIG. 2, the first heat source assembly102generally includes a first heat source exchanger110, a first thermal fluid inlet line112(not labeled for clarity), and a first thermal fluid outlet line114(not labeled for clarity). Additionally, the second heat source assembly104similarly includes a second heat source exchanger116, a second thermal fluid inlet line118(not labeled for clarity), and a second thermal fluid outlet line (not labeled for clarity). Further, the shared assembly106generally includes a thermal fluid line120and a heat sink exchanger122thermally coupled to the thermal fluid line120.

For the embodiment shown, the first heat source exchanger110of the first heat source assembly102is at least one of a cooled cooling air heat source exchanger (i.e., thermally coupled to, e.g., the one or more cooling passages81of the cooling air system80for cooling an airflow through the one or more cooling passages81), an exhaust waste heat recovery heat source exchanger (e.g., positioned at an aft end of the turbine section of the gas turbine engine10, within the exhaust section32of the gas turbine engine10, or both, for extracting heat from an airflow therethrough), a lubrication oil heat source exchanger (e.g., positioned in thermal communication with the lubrication oil system of the gas turbine engine10for extracting heat from a flow of lubrication oil therethrough), or an under-cowl waste heat recovery heat source exchanger (e.g., positioned within a cowling18of a turbomachine16of the gas turbine engine10for extracting heat therefrom). More specifically, for the embodiment ofFIG. 3, the first heat source exchanger110is a cooled cooling air heat source exchanger in thermal communication with the cooled cooling air system80and the second heat source exchanger116is a waste heat recovery heat source exchanger (or rather, an exhaust waste heat recovery heat source exchanger) in thermal communication with the turbine section, the exhaust section32, or both.

Further, for the embodiment shown the heat sink exchanger122of the shared assembly106is at least one of a fuel heat sink exchanger (e.g., a heat exchanger thermally coupled to the fuel delivery system for transferring heat to a fuel flow through the fuel delivery system), a bypass passage heat sink exchanger (e.g., a heat exchanger positioned within, or thermally coupled to, the bypass passage56of the gas turbine engine10for transferring heat to a bypass airflow through the bypass passage56), or a compressor discharge heat sink exchanger (i.e., a heat exchanger positioned at a downstream end of the compressor section and upstream of the combustion section26for transferring heat to the airflow through, or from, the downstream end of the compressor section of the gas turbine engine10). More specifically, for the embodiment shown, the heat sink exchanger122is a fuel heat sink exchanger.

Moreover, as discussed above, the controller108is configured to selectively fluidly connect the first heat source assembly102or the second heat source assembly104to the shared assembly106. In such a manner, the controller108may operate the thermal management system100such that the thermal management system100more efficiently utilizes its assets throughout a flight envelope. For example, during a first operating condition (e.g., cruise, decent, or some other mid- to low-power operating mode), the controller108of the thermal management system100may fluidly connect the first heat source assembly102with the shared assembly106, such that substantially all of a flow of thermal transfer fluid through the shared assembly106is provided to and circulated through the first heat source assembly102. In such a manner, the thermal management system100may effectively recapture waste heat through the exhaust section32of the gas turbine engine10and utilize that heat to create a more efficient combustion process by heating a fuel flow to the combustion section26. Subsequently, during a second operating condition (e.g., takeoff, climb, or some other high-power operating mode), the controller108of the thermal management system100may fluidly connect the second heat source assembly104with the shared assembly106, such that substantially all of a flow of thermal transfer fluid through the shared assembly106is provided to and circulated through the second heat source assembly104. In such a manner, the thermal management system100may effectively reduce a temperature of an airflow through the cooled cooling air system80of the gas turbine engine, to allow increased temperatures within the turbine section and consequently, higher power outlets of the gas turbine engine.

Notably, during the first operating mode, the cooled cooling air system80may not need the additional heat rejection to allow the additional power output of the engine10. Similarly, during the second operating mode, it may not be necessary (or it may at least be less important) to capture waste heat from the exhaust section32for short-term efficiency benefits. Accordingly, by utilizing the shared assembly104, which may be selectively fluidly connected to the first heat source assembly102and second heat source assembly104, the thermal management system100may operate with less non-utilized components throughout the entire flight envelope of the engine10, providing a lighter, more efficient, and more cost effective engine.

It will be appreciated, however, that in other embodiments, the gas turbine engine10, the thermal management system100, or both may have any other suitable configuration. For example, referring now toFIG. 4, it will be appreciated that in other embodiments, the first heat source exchanger110of the first heat source assembly102may be any other suitable heat source exchanger, the second heat source exchanger116of the second heat source assembly104may be any other suitable source exchanger, and further the heat sink exchanger122of the shared assembly106may be any other suitable heat sink exchanger. For example, for the embodiment depicted inFIG. 4, the first heat source exchanger110and/or the second heat source exchanger116may be configured as an exhaust waste heat recovery heat exchanger110A/116A, a lubrication oil heat source exchanger110B/116B (operable with a lubrication oil system of the gas turbine engine10), an under-cowl waste heat recovery heat source exchanger110C/116C, etc. Similarly, for the embodiment ofFIG. 4, the heat sink exchanger122may be, e.g., a fuel heat sink exchanger122A (operable with a fuel delivery system86of the gas turbine engine10), a bypass passage heat sink exchanger122B (e.g., coupled to, or integrated into, an outlet guide vane52), a compressor discharge heat sink exchanger122C, etc. Other configurations are contemplated as well. Moreover, in still other embodiments, the heat source exchanger110may be an intercooler heat source exchanger positioned within or upstream of the compressor section, such as upstream of the HP compressor24, or upstream of the LP compressor22.

Referring now toFIG. 5, a flow diagram of a method200for operating a thermal management system of a gas turbine engine is provided. In at least certain exemplary aspects, the method200may be utilized to operate one or more of the exemplary thermal management systems100described above with reference toFIGS. 1 through 4. However, in other exemplary aspects, the method200may be utilized to operate any other suitable thermal management system.

The method200generally includes at (202) providing a thermal transfer fluid through a shared assembly of the thermal management system and to a first heat source assembly of the thermal management system. The shared assembly includes a heat sink exchanger. Notably, for the exemplary aspect depicted inFIG. 5, providing the thermal transfer fluid through the shared assembly of the thermal management system and to the first heat source assembly of the thermal management system at (202) includes at (204) providing substantially all of the thermal transfer fluid from the shared assembly of the thermal management system to the first heat source assembly of the thermal management system. More specifically, for the exemplary aspect depicted inFIG. 5, providing the thermal transfer fluid through the shared assembly of the thermal management system and to the first heat source assembly of the thermal management system at (202) includes at (206) preventing a flow of thermal transfer fluid through a second heat source assembly.

The method200further includes at (208) sensing data indicative of a gas turbine engine operating parameter. In certain exemplary aspects, sensing data indicative of the gas turbine engine operating parameter at (208) includes at (210) sensing data indicative of an operating condition of the gas turbine engine. The operating condition of the gas turbine engine may be, e.g., an operating mode of the gas turbine engine or aircraft including the gas turbine engine, such as a takeoff operating mode, a climb operating mode, a cruise operating mode, a step climb operating mode, a descent operating mode, a taxiing operating mode, a throttle position, etc. Additionally, or alternatively, in certain exemplary aspects, such as the exemplary aspect depicted inFIG. 5, sensing data indicative of the gas turbine engine operating parameter at (208) includes at (212) sensing data indicative of a temperature parameter of the gas turbine engine. More specifically, for the exemplary aspect depicted, sensing data indicative of the temperature parameter the gas turbine engine at (212) includes at (214) sensing data indicative of the temperature parameter passing the predetermined threshold. For example, sensing data indicative of the temperature parameter passing a predetermined threshold may include sensing data indicative of the temperature parameter surpassing a predetermined threshold or falling below a predetermined threshold. By way of example only, in certain exemplary aspects, sensing data indicative of the temperature parameter passing a predetermined threshold may include sensing data indicative of, e.g., a compressor exit temperature increasing above a predetermined threshold, an exhaust temperature increasing above a predetermined threshold, one or both of the compressor exit temperature or exhaust temperature decreasing below a predetermined threshold, etc.

Notably, in one or more of the above exemplary aspects, sensing data indicative of a gas turbine engine operating parameter at (208) may include receiving data from one or more sensors within the gas turbine engine or otherwise operable with the gas turbine engine.

Referring still to the exemplary method200depicted inFIG. 5, the method200further includes at (216) providing the thermal transfer fluid through the shared assembly of the thermal management system and to the second heat source assembly of the thermal management system in response to sensing data indicative of the gas turbine engine operating parameter at (208). For the exemplary aspect depicted, providing the thermal transfer fluid through the shared assembly of the thermal management system and to the second heat source assembly of thermal management system at (216) includes at (218) providing substantially all of the thermal transfer fluid from the shared assembly of the thermal management system to the second heat source assembly of the thermal management system. More specifically, for the exemplary aspect depicted, providing the thermal transfer fluid through the shared assembly of the thermal management system and to the second heat source assembly of the thermal management system at (216) includes at (220) preventing the flow of thermal transfer fluid through the first heat source assembly.

Further, for the exemplary aspect depicted inFIG. 5, providing the thermal transfer fluid through the shared assembly of the thermal management system and to the second heat source assembly of the thermal management system at (216) includes at (222) actuating a valve positioned at an upstream junction of the shared assembly or at a downstream junction of the shared assembly to divert the flow of thermal transfer fluid. In such a manner, the valve may be actuated in response to the sensed data indicative of the gas turbine engine parameter to fluidly connect the shared assembly with the second heat source assembly as opposed to the first heat source assembly.

Notably, in at least certain exemplary aspects, the first heat source assembly may include a heat source heat exchanger thermally coupled to a cooled cooling air system of the gas turbine engine, and the second heat source assembly may include a waste heat recovery heat source exchanger thermally coupled to a turbine section gas turbine engine, an exhaust section of the gas turbine engine, or both. In such a manner, the method200may operate the thermal management system such that the shared assembly operates with the first heat source assembly (including the heat source heat exchanger thermally coupled to the cooled cooling air system) during, e.g., a high power operating mode/conditions of the gas turbine engine such that the gas turbine engine may provide cooler air to the turbine section allowing for higher temperature combustion and greater power generation. By contrast, the method200may operate the thermal management system such that the shared assembly operates with the second heat source assembly (including the waste heat recovery heat source exchanger) during, e.g., a cruise operating mode/condition or other relatively low-power operation modes/conditions of the gas turbine engine such that waste heat may be recovered and utilized to increase an efficiency of the gas turbine engine when the high-powered operations (requiring full use of the cooled cooling air systems) are not necessary.

Briefly, referring still to the exemplary method200depicted inFIG. 5, the method200may additionally include at (224) increasing a pressure, a flow rate, or both of the thermal transfer fluid through the shared assembly using a thermal fluid pump of the shared assembly in fluid communication with a thermal fluid line of the shared assembly.