Patent Description:
A turbofan engine typically includes a fan section, a compressor section, a combustor section and a turbine section. Air entering the compressor section is compressed and delivered into the combustion section where it is mixed with fuel and ignited to generate a high-energy exhaust gas flow. The high-energy exhaust gas flow expands through the turbine section to drive the compressor and the fan section.

Electric power for the engine is typically provided by a motor/generator driven through a tower shaft driven by a main engine shaft. Motor/generators and electric motors are typically stand-alone devices that are coupled to an external accessory gearbox. Alternate motor/generator and motor configurations and placements may provide increased engine efficiencies and accommodate increasing demands for electric power.

<CIT> discloses a passive cooling system for an auxiliary power unit (APU) installation on an aircraft. The system is for an auxiliary power unit having at least a compressor portion of a gas turbine engine and an oil cooler contained separately within a nacelle.

<CIT> discloses a system and a method for cooling a tail-cone mounted generator according to the state of the art.

According to an aspect of the invention, there is provided a cooling system of a turbine engine as claimed in claim <NUM>.

According to a further aspect of the invention, there is provided a method of using the cooling system as claimed in claim <NUM>.

An ejector assembly for a cooling system of a gas turbine engine is disclosed herein. The ejector assembly may comprise: a tail cone having a tail cone outlet in fluid communication with a cooling air flow of the cooling system; an ejector body defining a mixing section, a constant area section, and a diffuser section; and a nozzle section in fluid communication with an exhaust air flow of the gas turbine engine, the ejector assembly configured to entrain the cooling air flow via the exhaust air flow.

In various embodiments, the nozzle section is defined by a nozzle portion of the ejector body and the tail cone. The ejector body may further comprise a scoop defining an inlet to the nozzle section. A throat of the nozzle section is disposed forward of the tail cone outlet. The cooling air flow may be from an external air source disposed radially outward from a bypass air flow path of the gas turbine engine. The tail cone may comprise a scoop configured to divert the exhaust air flow of the gas turbine engine internal to the tail cone. The tail cone may further comprise a channel extending through the tail cone and in fluid communication with the exhaust air flow, the channel defining a throat at a nozzle portion of the channel. A cooling air flow path may be defined radially outward from the channel and between the channel and the ejector body. The ejector body may be coupled to the tail cone at the tail cone outlet. A cooling assembly may include the ejector assembly, the electric motor disposed in the tail cone, a conduit in fluid communication with the electric motor and the ejector assembly, and a plurality of conductive cables extending through the conduit and coupled to the electric motor. The cooling air flow may be configured to cool the plurality of conductive cables.

A method of exhausting a cooling air flow from a tail cone of a gas turbine engine is disclosed herein. The method may comprise: diverting an exhaust air flow from the gas turbine engine; choking the exhaust air flow forward of an outlet of the tail cone; and entraining the cooling air flow from the outlet of the tail cone.

In various embodiments, the exhaust air flow is disposed radially outward of the cooling air flow. Entraining the cooling air flow may further comprise pulling the cooling air flow through the outlet of the tail cone. The exhaust air flow may be diverted via a scoop proximate a nozzle of the gas turbine engine. The method may further comprise flowing the cooling air flow over a plurality of conductive power cables prior to entraining the cooling air flow. The method may further comprise pulling the cooling air flow from an external source prior to flowing the cooling air flow over the plurality of conductive power cables.

A cooling system of a gas turbine engine is disclosed herein. The cooling system may comprise: a tail cone having a tail cone outlet; an electric motor disposed in the tail cone; a conduit; a plurality of cables extending from the electric motor, the plurality of cables disposed at least partially in the conduit; a cooling source in fluid communication with the conduit, the cooling source configured to flow a cooling air flow through the conduit to cool the plurality of cables; and an ejector body coupled to the tail cone, the ejector body configured to entrain the cooling air flow through the tail cone outlet.

In various embodiments, the ejector body has a nozzle section defining a choke area between the tail cone and the ejector body. The cooling source may include an electric fan. The conduit may be in fluid communication with the electric fan. The tail cone may comprise a scoop configured to divert a portion of an exhaust air flow from the gas turbine engine, the exhaust air flow configured to entrain the cooling air flow.

The detailed description of exemplary embodiments herein makes reference to the accompanying drawings, which show exemplary embodiments by way of illustration. While these exemplary embodiments are described in sufficient detail to enable those skilled in the art to practice the exemplary embodiments of the disclosure, it should be understood that other embodiments may be realized and that logical changes and adaptations in design and construction may be made in accordance with this disclosure and the teachings herein. Thus, the detailed description herein is presented for purposes of illustration only and not limitation.

Also, any reference to attached, fixed, connected or the like may include permanent, removable, temporary, partial, full and/or any other possible attachment option. Surface cross hatching lines may be used throughout the figures to denote different parts but not necessarily to denote the same or different materials.

Throughout the present disclosure, like reference numbers denote like elements. Accordingly, elements with like element numbering may be shown in the figures, but may not necessarily be repeated herein for the sake of clarity. Surface shading lines and/or cross-hatching may be used throughout the figures to denote different parts but not necessarily to denote the same or different materials.

Aft includes the direction associated with the tail (e.g., the back end) of an aircraft, or generally, to the direction of exhaust of a gas turbine engine. Forward includes the direction associated with the intake (e.g., the front end) of a gas turbine engine.

A first component that is "radially outward" of a second component means that the first component is positioned at a greater distance away from a central longitudinal axis of the gas turbine engine. A first component that is "radially inward" of a second component means that the first component is positioned closer to the engine central longitudinal axis than the second component. The terminology "radially outward" and "radially inward" may also be used relative to references other than the engine central longitudinal axis.

With reference to <FIG>, a nacelle <NUM> for a gas turbine engine is illustrated according to various embodiments. Nacelle <NUM> may comprise an inlet <NUM>, a fan cowl <NUM>, and a thrust reverser <NUM>. Nacelle <NUM> may be coupled to a pylon <NUM>. Pylon <NUM> may mount nacelle <NUM>, and a gas turbine engine located within nacelle <NUM>, to an aircraft wing or aircraft body. In various embodiments, an exhaust system <NUM> may extend from the gas turbine engine mounted within nacelle <NUM>.

<FIG> illustrates a cross-sectional view of a gas turbine engine <NUM> located within nacelle <NUM>, in accordance with various embodiments. Gas turbine engine <NUM> may include a core engine <NUM>. Core engine <NUM> may include an inlet section <NUM>, a compressor section <NUM>, a combustor section <NUM>, and a turbine section <NUM>. In operation, a fan <NUM> drives fluid (e.g., air) along a bypass flow-path B while compressor section <NUM> can drive air along a core flow-path C for compression and communication into combustor section <NUM> then expansion through turbine section <NUM>. In various embodiments, core engine <NUM> generally comprises a low speed spool and a high speed spool mounted for rotation about an engine central longitudinal axis A-A'. Low speed spool may generally comprise a shaft that interconnects fan <NUM>, a low pressure compressor <NUM>, and a low pressure turbine <NUM>. The high speed spool may comprise a shaft that interconnects a high pressure compressor <NUM> and high pressure turbine <NUM>. A combustor may be located between high pressure compressor <NUM> and high pressure turbine <NUM>. As used herein, a "high pressure" compressor or turbine experiences a higher pressure than a corresponding "low pressure" compressor or turbine. Although depicted gas turbine engine <NUM> is illustrated as a turbofan engine herein, it should be understood that the concepts described herein are not limited in use to turbofans as the teachings may be applied to other types of engines including turboprop and turboshaft engines. Although core engine <NUM> may be depicted as a two-spool architecture herein, it should be understood that the concepts described herein are not limited in use to two-spool gas turbine engines as the teachings may be applied to other types of engines including engines having more than or less than two spools.

Core engine <NUM> drives fan <NUM> of gas turbine engine <NUM>. The air flow in core flow path C may be compressed by low pressure compressor <NUM> then high pressure compressor <NUM>, mixed and burned with fuel in the combustor section <NUM>, then expanded through high pressure turbine <NUM> and low pressure turbine <NUM>. Turbines <NUM>, <NUM> rotationally drive their respective low speed spool and high speed spool in response to the expansion. Bypass air flow B, driven by fan <NUM>, flows in the aft direction through bypass flow path <NUM>. At least a portion of bypass flow path <NUM> may be defined by nacelle <NUM> and an inner fixed structure (IFS) <NUM>.

An upper bifurcation <NUM> and a lower bifurcation <NUM> may extend radially between the nacelle <NUM> and IFS <NUM> in locations opposite one another. Engine components such as wires and fluids, for example, may be accommodated in upper bifurcation <NUM> and lower bifurcation <NUM>. IFS <NUM> surrounds core engine <NUM> and provides core compartment <NUM>. Various components may be provided in core compartment <NUM> such as fluid conduits and/or compressed air ducts. For example, a portion BCORE of bypass air flow B may flow between core engine <NUM> and IFS <NUM> in core compartment <NUM>. A fan case <NUM> may surround fan <NUM>. Fan case <NUM> may be housed within nacelle <NUM>. Fan case <NUM> may provide a mounting structure for securing gas turbine engine <NUM> to pylon <NUM>, with momentary reference to <FIG>. According to various embodiments, one or more fan exit guide vanes <NUM> may extend radially between core engine <NUM> and fan case <NUM>.

Exhaust system <NUM> is located aft of turbine section <NUM>. Core air flow C flows through core engine <NUM> and is expelled through an exhaust outlet <NUM> of exhaust system <NUM>. Exhaust outlet <NUM> may comprise an aerodynamic tail cone <NUM>. A primary nozzle <NUM> may be located radially outward of tail cone <NUM>. Primary nozzle <NUM> and tail cone <NUM> may define exhaust outlet <NUM>. Exhaust outlet <NUM> provides an exhaust path for core air flow C exiting turbine section <NUM> of core engine <NUM>. A secondary nozzle may be located radially outward of primary nozzle <NUM>. Primary nozzle <NUM> and the secondary nozzle may define an exit flow path for bypass air flow B exiting core compartment <NUM> and/or bypass flow path <NUM>. A plurality of turbine exit guide vanes (TEGVs) <NUM> may be located circumferentially about engine central longitudinal axis A-A' and proximate an aft end <NUM> of low pressure turbine <NUM>.

In various embodiments, an electric motor <NUM> is disposed in tail cone <NUM>. The electric motor <NUM> may be mechanically coupled to a low speed spool in core engine <NUM>. Electric motor <NUM> may comprise an electric generator, an electric motor, a combination of the two, or the like. Electric motor <NUM> may be electrically coupled to a juncture box, or any other electrical device known in the art. The electrical device may be disposed radially outward from IFS <NUM> of gas turbine engine <NUM> in a wing <NUM> of an aircraft, in the pylon <NUM> of the aircraft, or the like. Conductive cables may extend from the electric motor <NUM> to the electric device external to gas turbine engine <NUM>. The conductive cables (e.g., copper wires or the like) may extend radially outward from electric motor <NUM> through a strut <NUM>, through the pylon <NUM> and to an electrical device in the wing <NUM>, or any other location external or internal to IFS <NUM>. The strut <NUM> extends from the tail cone <NUM> beyond the IFS <NUM>. The strut may be disposed aft of the aft end <NUM> of low pressure compressor turbine <NUM> and forward of exhaust outlet <NUM>. Due to the conductive cables proximity to exhaust outlet <NUM>, the conductive cables may experience relatively high temperatures from air flow in core air flow path C.

In various embodiments, the conductive cables may be disposed in a conduit <NUM> extending radially outward from tail cone <NUM> through strut <NUM> and into the pylon <NUM>. The conduit <NUM> may be fluidly coupled to an external air source by any method known in the art, such as a scoop, a vent, or the like. The external air source <NUM> may be disposed radially outward from nacelle <NUM>. In this regard, the external air source <NUM> may receive colder temperature air relative to bypass air flow B. Although external air source <NUM> is illustrated forward of the electric motor <NUM> on the pylon, the application is not limited in this regard. For example, in various embodiments, the external air source <NUM> may be aft of the electric motor <NUM>.

In various embodiments, bleed air from the core air flow path C may be diverted aft of the fan as a cooling source. However, bleed air may increase the mass flow and/or reduce efficiency of gas turbine engine <NUM>. To address this, ambient air may be pulled from external to gas turbine engine <NUM>, which may reduce or eliminate utilizing bleed air for the cooling of conductive power cables. In various embodiments, bypass air from bypass air flow path B may be diverted to act as a cooling source for cooling of conductive cables. However, bypass air may be limited to use while the gas turbine engine <NUM> is in operation. In this regard, bypass air may provide insufficient cooling after engine shutdown, or the like.

Referring now to <FIG>, a schematic view of a conductive cable cooling system <NUM>, in accordance with various embodiments, is illustrated. The conductive cable cooling system <NUM> comprises a plurality of conductive cables <NUM>. The conductive cables <NUM> are extending from an electric motor <NUM> disposed in a tail cone <NUM>. The electric motor <NUM> is operably coupled to a low speed spool <NUM> of a gas turbine engine (e.g., gas turbine engine <NUM> from <FIG>). The conductive cable cooling system <NUM> further comprises a strut <NUM> extending from a radially outer surface <NUM> of tail cone <NUM> to a radially inner surface <NUM> of pylon <NUM>. The strut <NUM> may comprise an outer strut shell <NUM> and an inner strut shell <NUM>. The outer strut shell <NUM> may be exposed to air flow from core air flow path C in <FIG> during operation of the gas turbine engine <NUM>. The conductive cable cooling system <NUM> may further comprise an air seal <NUM> disposed between inner strut shell <NUM> and outer strut shell <NUM>. In this regard, the air seal <NUM> may ensure that the plurality of conductive cables <NUM> are sealed from air from core air flow path C.

In various embodiments, the conductive cable cooling system <NUM> further comprises a conduit <NUM>. The conduit <NUM> may be configured to house the plurality of conductive cables <NUM> through strut <NUM>. The conduit <NUM> may be flexible or rigid. The conduit <NUM> may comprise a woven fiberglass sleeve, or the like. The conduit <NUM> may protect the plurality of conductive cables <NUM> from contacting strut <NUM> during operation of the gas turbine engine <NUM> from <FIG>. The conduit <NUM> may further provide a cooling passageway for cooling air to flow from the external air source <NUM> from <FIG>.

In various embodiments, the conductive cable cooling system <NUM> further comprises an electric fan <NUM> in fluid communication with the conduit <NUM> and a vent <NUM>. The electric fan <NUM> may be configured to actively cool the plurality of conductive cables <NUM>. The vent <NUM> may be configured to open or close. The electric fan <NUM> may be configured to receive cooling air flow from ambient air (e.g., an external air source from the nacelle, such as external air source <NUM>). The electric fan <NUM> and the vent <NUM> may be electrically coupled to a processor <NUM>. In various embodiments, processor <NUM> may be in electrical communication with electric fan <NUM>. The processor <NUM> may be configured to activate, increase, or decrease a speed of the electric fan in response to various operation conditions of the gas turbine engine. Similarly, the vent <NUM> may be modulated in response to changes in various operation conditions of gas turbine engine. The processor <NUM> may be configured to detect an engine shutdown. In response to the engine shutdown, processor <NUM> may command vent <NUM> to open and command the electric fan to activate and begin rotating. In various embodiments, vent <NUM> may already be open at engine shutdown, and the processor may command the electric fan to increase a rotation speed or begin to rotate. In various embodiments, vent <NUM> may be commanded to operate between open and closed during operation in response to a desired air flow desired in conduit <NUM>. Although the electric fan <NUM> and the vent <NUM> are illustrated as being forward of the electric motor <NUM>, the disclosure is not limited int his regard. For example, in various embodiments, the electric fan <NUM> and the vent <NUM> are disposed aft of the electric motor <NUM>.

The vent <NUM> may assume a closed configuration, an open configuration (<NUM>% open), and/or a partially open configuration (ranging between the open configuration and the closed configuration) as commanded by a controller. In various embodiments, the closed configuration may comprise the vent <NUM> being approximately <NUM>% percent open (e.g., between <NUM>% and <NUM>% open), which may be set at any desired percent open. For the sake of simplicity, in this disclosure, the minimum percent open for the closed configuration is <NUM>% open but in some embodiments may also be different values (e.g., <NUM>% or other small openings that may allow passage of small amounts of air). In various embodiments, the vent actuator may cause the vent <NUM> to become more open or less open, at any time before, during, or after operation of the gas turbine engine <NUM> from <FIG> to assume the open configuration, a partially open configuration, and/or the closed configuration.

In various embodiments, processor <NUM> may be integrated into computer systems onboard an aircraft, such as, for example, a full authority digital engine control (FADEC), an engine-indicating and crew-alerting system (EICAS), and/or the like. Processor <NUM> may include one or more processors and/or one or more tangible, non-transitory memories and be capable of implementing logic. Each processor can be a general purpose processor, a digital signal processor (DSP), an application specific integrated circuit (ASIC), a field programmable gate array (FPGA) or other programmable logic device, discrete gate or transistor logic, discrete hardware components, or any combination thereof.

In various embodiments, processor <NUM> may comprise a processor configured to implement various logical operations in response to execution of instructions, for example, instructions stored on a non-transitory, tangible, computer-readable medium. As used herein, the term "non-transitory" is to be understood to remove only propagating transitory signals per se from the claim scope and does not relinquish rights to all standard computer-readable media that are not only propagating transitory signals per se.

In various embodiments, processor <NUM> may be configured to control conductive cable cooling system <NUM>. For example, processor <NUM> may be configured to transfer a control signal to electric fan to actively control cooling of the plurality of conductive cables <NUM>. Processor <NUM> may generate and transmit the control signal based on an input received from FADEC or an electronic engine control in response to gas turbine engine shutting down. In this regard, conductive cable cooling system <NUM> may allow for active cooling of the plurality of conductive cables <NUM> after engine shutdown. The excitation control signal may further comprise electronic instructions configured to cause the electric fan <NUM> to rotate and provide cooling air in response to a temperature in conduit <NUM> exceeding a predetermined threshold. For example, a temperature sensor may be disposed in conduit <NUM> in electrical communication with the processor <NUM>. In response to the temperature sensor detecting a conduit temperature above a threshold level, electric fan <NUM> may be active. In various embodiments, processor <NUM> may be configured to transmit a control signal to rotate electric fan <NUM> during operation of gas turbine engine <NUM> from <FIG>. In this regard, electric fan <NUM> may drive air from external air source <NUM> (e.g., ambient air). The external air source <NUM> may provide colder air relative to bypass air flow, core air flow or the like and/or provide better cooling to the plurality of conductive cables than typic cable cooling systems.

In various embodiments, the cooling air provided by electric fan <NUM> may travel along cooling path D through the pylon <NUM> and strut <NUM> into the tail cone <NUM> and exit out a tail cone ejector disposed at an aft end of tail cone <NUM> as described further herein.

Referring now to <FIG>, a schematic view of a tail cone ejector assembly <NUM> for use in a conductive cable cooling system <NUM>, in accordance with various embodiments, is illustrated. Tail cone ejector assembly <NUM> may include a nozzle section <NUM>, a mixing section <NUM>, a constant area section <NUM>, and a diffuser section <NUM>. In various embodiments, the ejector assembly <NUM> comprises a tail cone <NUM> and an ejector body <NUM>. The tail cone <NUM> may be a part of tail cone <NUM> from <FIG> and <FIG>. In operation, an entrained flow may travel through a flow path defined by a wall <NUM> of a tail cone <NUM> and a primary flow may travel between the wall <NUM> and a nozzle portion <NUM> of an ejector body <NUM>. The nozzle portion <NUM> may be a portion of the ejector body within the nozzle section <NUM> of the tail cone ejector assembly <NUM>. The wall <NUM> may further define cooling path D, and the wall <NUM> and the nozzle portion <NUM> of the ejector body <NUM> may further define core-flow path C. Fluid (e.g., air) is driven through core-flow path C as described previously herein, which is configured to entrain cooling flow along cooling flow path D. For example, a drop in pressure of the fluid traveling along core-flow path C caused by an increase in velocity after the flow along core-flow path C is choked at the choke area (e.g., the throat A*) pulls in (e.g., entrains) the cooling air flow through the cooling flow path D. The choke area is a constriction area along core-flow path C and may be a minimum constriction area. By choking the flow at the choke area, the velocity of the air flow traveling along core-flow path C increases aft of the choke area. Although described herein as an ejector assembly with choked flow resulting in a sonic exit velocity, the present disclosure is not limited in this regard. For example, a tail cone ejector assembly <NUM> may include a non-choked ejector without a choke area (e.g., throat A*) resulting in a subsonic exit velocity of the ejector assembly.

In various embodiments, the electric fan <NUM> from <FIG> may be sized and configured to actively cool the conductive cables <NUM> after an engine shutdown when an airplane having the gas turbine engine is on the ground. During operation of the gas turbine engine, the electric fan <NUM> may not provide enough pressure to eject air out the tail cone <NUM> on its own. For example, without the ejector assembly <NUM>, air traveling along cooling flow path D may be subject to reverse. In various embodiments, by having an ejector assembly <NUM> a size of the electric fan <NUM> from <FIG> may be reduced as the air traveling along the core flow path C of the ejector assembly <NUM> may entrain the cooling air traveling along cooling flow path D in the mixing section <NUM> of the ejector assembly <NUM>.

In various embodiments, the ejector body <NUM> further comprises a scoop <NUM> disposed at a forward end of the ejector body <NUM>. The scoop <NUM> is configured to scoop exhaust flow from the gas-turbine engine into the outer annulus defined by the wall <NUM> of the tail cone <NUM> and the ejector body <NUM> where the exhaust flow acts as the primary air flow of the ejector assembly <NUM>. In various embodiments, the tail cone <NUM> further comprises a tail cone outlet <NUM> disposed aft of the scoop <NUM> of the ejector body <NUM>. The tail cone outlet <NUM> is also aft of the throat A* of the ejector assembly <NUM> and adjacent to the mixing section <NUM> of the ejector assembly.

In various embodiments, the ejector assembly <NUM> may be referred to as a critical or a non-critical ejector assembly. In various embodiments, a critical ejector assembly means that the ejector assembly is designed to accommodate fluid velocity along the core flow path C prior to the throat A* that is sonic, whereas a non-critical ejector assembly means ejector assembly that is designed to accommodate a fluid velocity along the core flow path C prior to the throat A* as being subsonic. In various embodiments, when the ejector assembly <NUM> is a critical design, the ejector assembly <NUM> may be sensitive to operating conditions other than those for which the ejector assembly <NUM> is designed. With a critical ejector assembly, it is possible to decrease the motivating pressure (e.g., the air flow through core flow path C) without a resulting change in the suction pressure if the discharge pressure is also decreased. The relation of change between the motivating pressure and the discharge pressure depends on the characteristics of the design of the ejector assembly <NUM>. Since an ejector may have an optimal design point for a certain throat profile, once the ejector assembly <NUM> is designed and built to definite specifications of motivating pressure, discharge pressure and suction pressure, suction capacity of the ejector assembly <NUM> does not increase without changing the internal physical dimensions of the ejector assembly <NUM>. The suction capacity may actually be lowered by increasing the motivating pressure. Since the nozzle portion <NUM> of the ejector body <NUM> is a fixed orifice metering device any change in the motivating pressure is accompanied by a proportionate change in the quantity of motive fluid.

In various embodiments, when the ejector assembly <NUM> is a non-critical design, changes in the motivating pressure and discharge pressure cause gradual changes in the suction pressure and capacity. Suction capacity does not increase in proportion to motivating pressure increases.

Referring now to <FIG>, a schematic view of a tail cone ejector assembly <NUM> for use in a conductive cable cooling system <NUM>, in accordance with various embodiments, is illustrated. In various embodiments, the conductive cable cooling system <NUM> is in accordance with the conductive cable cooling system <NUM> except as further described herein. In various embodiments, the tail cone <NUM> comprises a scoop <NUM> proximate primary nozzle <NUM>. In this regard, the scoop <NUM> may be configured to direct a portion of exhaust flow from core flow path C from <FIG> internal to the tail cone <NUM> along a channel <NUM>.

In various embodiments, the channel <NUM> is in fluid communication with an ejector body <NUM> of the ejector assembly <NUM>. For example, the channel <NUM> may direct exhaust air from core flow path C through the choke area (e.g., throat A*), and entrain cooling flow traveling along cooling flow path E. In various embodiments, the cooling flow path E may be radially outward from the channel <NUM>. Similar to ejector assembly <NUM> from <FIG>, ejector assembly <NUM> comprises a nozzle section <NUM>, a mixing section <NUM>, a constant area section <NUM>, and a diffuser section <NUM>. The nozzle section <NUM> includes a nozzle portion <NUM> of the ejector assembly <NUM>. In various embodiments, the cooling flow path E is disposed between the nozzle portion <NUM> and the ejector body <NUM>. In various embodiments, the cooling flow path E is the secondary flow path, and the channel <NUM> defines the primary flow path. In various embodiments, an ejector assembly in accordance with ejector assembly <NUM> may be more complicated from a manufacturing standpoint for a tail cone ejector relative to an ejector assembly in accordance with the ejector assembly <NUM>. However, an ejector assembly in accordance with ejector assembly <NUM> may be slightly more efficient relative to an ejector assembly in accordance with ejector assembly <NUM> from <FIG>.

In various embodiments, the ejector body <NUM> may be coupled to the tail cone <NUM> proximate a tail cone outlet <NUM>. In various embodiments, the channel <NUM> may be a fluid conduit disposed within the tail cone <NUM>. In various embodiments, the ejector body <NUM> and the tail cone <NUM> may be a monolithic component. In various embodiments, the ejector body <NUM> and the tail cone may be distinct components.

Referring now to <FIG>, the tail cone ejector assembly <NUM> in accordance with various embodiments, is illustrated. In various embodiments, the ejector assembly <NUM> further comprises a motive fluid inlet scoop <NUM>. Although illustrated as comprising three motive fluid inlet scoops, the ejector assembly <NUM> is not limited in this regard. For example, the ejector assembly <NUM> may include any number of motive fluid inlet scoops (e.g., one single inlet scoop that sweeps a circumference of less than <NUM> degrees that is non-axisymmetric, a plurality of motive inlet scoops disposed symmetrically proximate the tail cone outlet <NUM> of the tail cone <NUM>, or a plurality of asymmetric motive inlet scoops disposed proximate the tail cone outlet <NUM>). In various embodiments, the motive fluid inlet scoop <NUM> may provide a lip height that is larger to avoid clogging of the ejector assembly <NUM>.

Referring now to <FIG>, a method <NUM> of using a tail cone ejector assembly (e.g., tail cone ejector assembly <NUM>, <NUM>), in accordance with various embodiments, is illustrated. In various embodiments, the method <NUM> comprises diverting an exhaust air flow from a gas turbine engine proximate a tail cone (step <NUM>). The exhaust air flow may be diverted by a scoop, such as scoop <NUM> from <FIG> or scoop <NUM> from <FIG>. The exhaust air flow may be diverted internal to the tail cone, as illustrated in <FIG>, or between the tail cone and an ejector body as illustrated in <FIG>.

Claim 1:
A cooling system (<NUM>; <NUM>) of a turbine engine (<NUM>), the cooling system comprising:
a tail cone (<NUM>; <NUM>) having a tail cone outlet (<NUM>; <NUM>);
an electric motor (<NUM>) disposed in the tail cone;
a conduit (<NUM>);
a plurality of cables (<NUM>) extending from the electric motor, the plurality of cables disposed at least partially in the conduit;
a cooling source (<NUM>) in fluid communication with the conduit, the cooling source configured to flow a cooling air flow through the conduit to cool the plurality of cables; and
an ejector body (<NUM>; <NUM>) coupled to the tail cone, the ejector body configured to entrain the cooling air flow through the tail cone outlet.