Patent Description:
Conventional gas turbine engines are often tight on free space due to envelope constraints. Therefore innovative space-saving designs and architectures are often sought out when integrating new components into the gas turbine engine. <CIT> relates to thermal management of a tail cone mounted generator. <CIT> relates to a low pressure generator for gas turbine engine, which is installed at the nose cone of the gas turbine engine.

According to an aspect of the present invention, a tail cone assembly for a gas turbine engine, according to claim <NUM>, is provided.

In addition to one or more of the features described above, or as an alternative, further embodiments of the tail cone assemblies may include an electric generator installed within the generator housing.

In addition to one or more of the features described above, or as an alternative, further embodiments of the tail cone assemblies may include that the electrical conductor is a three-phase electrical conductor having three wires.

In addition to one or more of the features described above, or as an alternative, further embodiments of the tail cone assemblies may include that the electrical connector comprises three electrical pins and the adapter comprises three bus bars arranged to each connect one of the three wires to one of the three electrical pins.

In addition to one or more of the features described above, or as an alternative, further embodiments of the tail cone assemblies may include at least one additional hollow strut extending radially between the first casing and the second casing and defining an interior cavity, the at least one additional hollow strut located circumferentially relative to the longitudinal axis at a location radially aligned with at least one additional electrical connector of the generator housing. At least one additional electrical conductor is arranged within the interior cavity of the at least one additional hollow strut and at least one additional adapter is configured to electrically connect the at least one additional electrical conductor with the at least one additional electrical conductor.

In addition to one or more of the features described above, or as an alternative, further embodiments of the tail cone assemblies may include a bracket configured to fixedly attach the adapter to the generator housing.

In addition to one or more of the features described above, or as an alternative, further embodiments of the tail cone assemblies may include that the adapter comprises an adapter body and an adapter cover.

In addition to one or more of the features described above, or as an alternative, further embodiments of the tail cone assemblies may include that the adapter body is configured to directly connect to the generator housing.

In addition to one or more of the features described above, or as an alternative, further embodiments of the tail cone assemblies may include that the adapter body and the adapter cover are electrically insulating.

According to a further aspect, a gas turbine engine, according to claim <NUM> is provided.

In addition to one or more of the features described above, or as an alternative, further embodiments of the gas turbine engines may include an electric generator installed within the generator housing, wherein the electric generator is operably connected to the low spool shaft.

In addition to one or more of the features described above, or as an alternative, further embodiments of the gas turbine engines may include that the adapter is arranged within the interior cavity of the hollow strut.

In addition to one or more of the features described above, or as an alternative, further embodiments of the gas turbine engines may include that the electrical conductor is a three-phase electrical conductor having three wires.

In addition to one or more of the features described above, or as an alternative, further embodiments of the gas turbine engines may include a third casing arranged radially outward from the second casing relative to the longitudinal axis, wherein a space between the first casing and the second casing is a core flow exhaust area and a space between the second casing and the third casing is a bypass flow exhaust are.

In addition to one or more of the features described above, or as an alternative, further embodiments of the gas turbine engines may include at least one additional hollow strut extending radially between the first casing and the second casing and defining an interior cavity, the at least one additional hollow strut located circumferentially relative to the longitudinal axis at a location radially aligned with at least one additional electrical connector of the generator housing, at least one additional electrical conductor arranged within the interior cavity of the at least one additional hollow strut, and at least one additional adapter configured to electrically connect the at least one additional electrical conductor with the at least one additional electrical conductor.

In addition to one or more of the features described above, or as an alternative, further embodiments of the gas turbine engines may include at least one additional hollow strut extending radially between the first casing and the second casing and defining an interior cavity, the at least one additional hollow strut located circumferentially relative to the longitudinal axis at a location radially aligned with a fluid connector of the generator housing and at least one fluid line connected to the fluid connector and passing through the at least one additional hollow strut.

In addition to one or more of the features described above, or as an alternative, further embodiments of the gas turbine engines may include that the at least one fluid line is one of an oil input line, an air input line, and an oil scavenge line.

In addition to one or more of the features described above, or as an alternative, further embodiments of the gas turbine engines may include a bracket configured to fixedly attach the adapter to the generator housing.

In addition to one or more of the features described above, or as an alternative, further embodiments of the gas turbine engines may include a tail cone arranged with the generator housing positioned within the tail cone.

High pressure spools of gas turbine engines may be used to drive accessories of the gas turbine engine. However, as engine bypass ratios increase, the capability of a high pressure spool to drive accessories, such as electric generators, has been diminished. Therefore it is desirable to drive accessories off of a low pressure spool of the gas turbine engine. Gas turbine engines typically drive accessories through a radial tower shaft and accessory gearbox operably connected to the high pressure spool, however connecting to the low pressure spool is more challenging.

Gas turbines may also include a tail cone at the rear of the engine to help accelerate the exhaust flow and create additional thrust. The enclosed area within this tail cone is typically empty space, and is also adjacent to the rotating low pressure spool. Embodiments disclosed herein seek to take advantage of this empty space by locating an electric generator within the tail cone and operably connecting the electric generator to the low speed spool such that the electric generator is driven by the low speed spool. Supplying electricity generated by such electric generator to various other engine and/or aircraft systems requires a terminal block to connect electrical wires or conductors and/or other conduits or connectors (e.g., for cooling air and/or fluids). However, given the relatively small amount of space, and high temperature gas exiting the engine, the availability of using convention terminal blocks is very limited (i.e., such terminal blocks may not fit within and around the tail cone at the aft end of the engine).

<FIG> schematically illustrates an example gas turbine engine <NUM> that may incorporate embodiments of the present disclosure. The gas turbine engine <NUM> is disclosed herein as a two-spool turbofan that includes, as illustrated, a fan section <NUM>, a compressor section <NUM>, a combustor section <NUM>, and a turbine section <NUM>. The fan section <NUM> is configured to drive air along a bypass flow path B in a bypass duct, while the compressor section <NUM> is configured to drive air along a core flow path C for compression and communication into the combustor section <NUM>, expansion through the turbine section <NUM>, and exhausted out an aft end of the gas turbine engine <NUM>. Although depicted as a two-spool turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with two-spool turbofans as the teachings may be applied to other types of turbine engines, without departing from the scope of the present disclosure.

The gas turbine engine <NUM>, shown in <FIG>, includes a low speed spool <NUM> and a high speed spool <NUM> mounted for rotation about an engine central longitudinal axis A relative to an engine static structure <NUM> via several bearing systems <NUM>. It should be understood that additional and/or alternative bearing systems, such as at various different locations, may be provided and the location of the bearing systems <NUM> may be varied as appropriate to the application.

The low speed spool <NUM>, as shown, includes an inner shaft <NUM> that interconnects a fan <NUM>, a low pressure compressor <NUM>, and a low pressure turbine <NUM>. The fan <NUM> may be driven at a lower speed than the low speed spool <NUM>. The high speed spool <NUM> includes an outer shaft <NUM> that interconnects a high pressure compressor <NUM> and a high pressure turbine <NUM>. A combustor <NUM> is arranged in the gas turbine <NUM> between the high pressure compressor <NUM> and the high pressure turbine <NUM>. The engine static structure <NUM> is arranged generally between the high pressure turbine <NUM> and the low pressure turbine <NUM>. The engine static structure <NUM> is configured to support the bearing systems <NUM> in the turbine section <NUM>. The inner shaft <NUM> and the outer shaft <NUM> are concentric and rotate via the bearing systems <NUM> about the engine central longitudinal axis A, which is collinear with their longitudinal axes.

The air of the core flow path C is compressed by the low pressure compressor <NUM> then the high pressure compressor <NUM>, mixed and burned with fuel in the combustor <NUM>, then expanded over the high pressure turbine <NUM> and the low pressure turbine <NUM>. The turbine section <NUM> rotationally drives the respective low speed spool <NUM> and high speed spool <NUM> in response to the expansion. It will be appreciated that each of the positions of the fan section <NUM>, the compressor section <NUM>, the combustor section <NUM>, and the turbine section <NUM> may be varied, depending on the specific engine configuration and/or application.

As shown, the gas turbine engine <NUM> includes a tail cone <NUM> located on a rear or aft portion of the gas turbine engine <NUM>. The tail cone <NUM> is operably shaped to help accelerate the exhaust air flow exiting the core flow path C and configured to create additional thrust for the gas turbine engine <NUM>. Commonly, the tail cone <NUM> may be securely fastened to the gas turbine engine <NUM> via a plurality of fasteners <NUM> and/or struts to one or more structural parts of the gas turbine engine <NUM>. The structural parts of the gas turbine engine <NUM> to which the tail cone <NUM> may attach may be the engine static structure <NUM>. The plurality of fasteners <NUM> may be arranged circumferentially around the engine central longitudinal axis A. The tail cone <NUM> may be securely fastened to the gas turbine engine <NUM> in a cantilevered arrangement, as shown in <FIG>. The tail cone <NUM> may include or define a hollow interior space <NUM> within the tail cone <NUM>. Conventional gas turbine engines typically leave this interior space empty and unused. However, in accordance with embodiments disclosed herein, this interior space <NUM> may be utilized by locating an electric generator within the interior space <NUM>.

When mounting the electric generator within the interior space of a tail cone, the connectors for the electric generator must enable connection from the generator to other engine and/or aircraft systems. Such electric generator may require fluid inputs (e.g., air and/or liquid) for the purpose of cooling and lubrication (can include input and output conduits). Further, the electricity must be directed along electrical conductors to deliver the electricity to one or more desired locations (e.g., on the gas turbine or elsewhere on the aircraft). Conventional terminal blocks are not suitable for use in this tail cone configuration. This is because conventional terminal blocks are too large and cannot fit within the space at the tail cone.

For example, turning to <FIG>, a tail cone assembly <NUM> is shown. The tail cone assembly <NUM> is configured to house an electric generator within a generator housing <NUM>. The generator housing <NUM> is supported within a gas turbine engine by a first casing <NUM>. As shown, struts <NUM> extend between the first casing <NUM> and a second casing <NUM>. The space between the first casing <NUM> and the second casing may define the hot gas exhaust from the gas turbine engine (e.g., core flow path C shown in <FIG>). Although not shown, a third casing may be arranged radially outward from the second casing, with the space between the second casing <NUM> and the third casing defining an exhaust of bypass air (e.g., bypass flow path B shown in <FIG>).

Also shown in <FIG> is a terminal block <NUM>. The terminal block <NUM>, as shown, cannot fit within a reasonable space around the generator housing <NUM>, and thus is shown extending through the first casing <NUM> and into the exhaust area of the core flow path. Furthermore, as shown, cabling for electrical connections is not viable either, as such cables would need to extend through and be exposed to the hot exhaust gases. This is due in part to the relatively narrow or small area in which the generator housing <NUM> is installed, and also due in part to the relatively small circumference of the generator housing <NUM>. That is, the generator housing <NUM> does not provide sufficient surface area for the proper installation and use of the terminal block <NUM>, as shown.

In view of this, embodiments of the present disclosure are directed to improved systems and configurations that allow for the use of a tail cone-mounted electric generator and electrical connections thereto.

Turning now to <FIG>, schematic illustrations of a tail cone assembly <NUM> in accordance with an embodiment of the present disclosure are shown. <FIG> is an aft-facing view of the tail cone assembly <NUM>, <FIG> is a forward-facing isometric illustration of the tail cone assembly <NUM>, and <FIG> is an aft-facing isometric illustration of the tail cone assembly <NUM>. The tail cone assembly <NUM> includes an electric generator installed within a generator housing <NUM> that is arranged within a tail cone <NUM> and along an axis of a gas turbine engine, with the electric generator having an input shaft <NUM> that is configured to operably connect to a low spool of the gas turbine engine. The low spool of the gas turbine engine may be configured to drive operation of the electric generator to generate power which may be distributed to other systems of the gas turbine engine and/or of an aircraft.

The generator housing <NUM> is mounted within a first casing <NUM> of the gas turbine engine. Radially outward from the first casing <NUM> is a second casing <NUM>, and radially outward from the second casing <NUM> is a third casing <NUM> (shown in <FIG>). The space between the first casing <NUM> and the second casing <NUM> defines an core exhaust area <NUM> of a core flow path through the gas turbine engine and space between the second casing <NUM> and the third casing <NUM> defines a bypass exhaust area <NUM> of a bypass flow path, as shown in <FIG>. As shown, a plurality of hollow struts <NUM> extend between the first casing <NUM> and the second casing <NUM>. Although not show, similar hollow struts may be provided between the second casing <NUM> and the third casing <NUM>. In this configuration, the first casing <NUM> is an inner casing, the second casing <NUM> is a middle casing, and the third casing <NUM> is an outer casing, with each casing description made relative to a radial line extending from an engine axis.

The electric generator housed within the generator housing <NUM> can be operably connected to other systems using one or more types of conduits, cables, and/or connectors. For example, in this non-limiting example embodiment, the electric generator has four sets of electrical conductors <NUM> operably (and electrically) connected thereto along with an oil input line <NUM>, an air input line <NUM>, and an oil scavenge line <NUM>. As shown, the tail cone assembly <NUM> includes seven hollow struts <NUM>. The hollow struts <NUM> are arranged circumferentially about or relative to the generator housing <NUM> at specific locations and aligned therewith, as described herein. For example, as shown, four of the hollow struts <NUM> are configured to contain and protect the electrical conductors <NUM>, one hollow strut <NUM> each is used to contain and protect the oil input line <NUM>, the air input line <NUM>, and the oil scavenge line <NUM>. As such, each of the electrical conductors <NUM>, the oil input line <NUM>, the air input line <NUM>, and the oil scavenge line <NUM> may pass through the core exhaust area <NUM> without being directly, and adversely, impacted thereby. Moreover, such elements are housed such that they are contained within substantially aerodynamic structures (i.e., the hollow struts <NUM>), and thus do not adversely impact the exhaust stream efficiencies. The circumferential position or location of the hollow struts allows for an easy installation of the internal components and ease of connection and/or interfacing with the generator housing <NUM> and/or elements/structures housed within the generator housing <NUM>. This is achieved, in part, for example, due to the circumferential alignment of the hollow struts with a connector on the generator housing.

It will be noted that in <FIG>, the electrical conductors <NUM>, the oil input line <NUM>, the air input line <NUM>, and the oil scavenge line <NUM> pass through the bypass exhaust area <NUM>. This configuration is not to be limiting. For example, due to the lower temperatures within the bypass exhaust area <NUM>, it may be possible to run one or more of the electrical conductors <NUM>, the oil input line <NUM>, the air input line <NUM>, and the oil scavenge line <NUM> along an exterior surface of the second casing <NUM> (e.g., a surface facing the third casing <NUM>). Such configuration may have one or more of the electrical conductors <NUM>, the oil input line <NUM>, the air input line <NUM>, and the oil scavenge line <NUM> extending axially along the second casing <NUM> (i.e., in-and-out of the page of <FIG>). As such, the illustrative configuration is not to be limiting, but rather is merely for illustrative and explanatory purposes.

In this illustrative configuration, as noted, there are four electrical conductors <NUM> that electrically connect to the electric generator within the generator housing <NUM>. The four electrical conductors <NUM> are configured to securely engage with, and electrically engage with, respective terminal posts arranged on the exterior of the generator housing <NUM>. As described further below, the terminal posts are arranged at locations on the exterior of the generator housing <NUM> such that when installed into a gas turbine engine, the terminal posts will align with the hollow struts <NUM>. As such, the electrical conductors <NUM> may pass directly through the hollow struts <NUM> and electrically connect with the terminal posts. As illustratively shown in <FIG>, the electrical conductors <NUM> are formed of a group of three wires or cables. Each wire or cable of the electrical conductors <NUM> may be arranged as one of A, B, or C Phase, such that at each terminal post a set of A, B, C Phases are connected to the electric generator housed within the generator housing <NUM>.

Turning now to <FIG>, a schematic cross-sectional illustration of a tail cone assembly <NUM> in accordance with an embodiment of the present disclosure is shown. <FIG> illustrates a generator housing <NUM> with an electric generator <NUM> installed therein. The electric generator <NUM> includes an input shaft <NUM> that operably connects to a low spool shaft <NUM> of a gas turbine engine and is arranged along a longitudinal axis Ax of the generator housing <NUM>. When installed within a gas turbine engine, the longitudinal axis Ax of the generator housing <NUM> will align with the engine longitudinal axis. Other examples of such electric generators are disclosed in: <CIT>, entitled "Integrated Tail Cone and Mounted Generator;" <CIT>, entitled "Temperature Control Device for Tail Cone Mounted Generator;" <CIT>, entitled "Plug In Fluid Cooled Electrical Connections for Tail Cone Mounted Generator. " The contents of these prior filed and commonly owned Applications are incorporated into the present disclosure in their entireties.

Turning now to <FIG>, schematic illustrations of a tail cone assembly <NUM> in accordance with an embodiment of the present disclosure are shown. <FIG> is an aft-facing isometric view of the tail cone assembly <NUM> without electrical connections, <FIG> is an aft-facing isometric illustration of the tail cone assembly <NUM> with electrical connections shown, and <FIG> is a forward-facing illustration of the tail cone assembly <NUM> as installed within a portion of a gas turbine engine. The tail cone assembly <NUM> includes an electric generator installed within a generator housing <NUM> that is arranged along an axis of a gas turbine engine, with the electric generator having an input shaft <NUM> that is configured to operably connect to a low spool of the gas turbine engine. The low spool of the gas turbine engine may be configured to drive operation of the electric generator to generate power which may be distributed to other systems of the gas turbine engine and/or of an aircraft.

As shown in <FIG>, the generator housing <NUM> includes a plurality of different connectors. For example, the generator housing <NUM> includes a number of electrical connectors <NUM> (e.g., terminal posts), and as shown are arranged as sets of three wires or cables (e.g., A, B, C, phases). Further, the generator housing <NUM> includes one or more fluid connectors <NUM> which can provide for fluid connection to one or more sources of fluid (e.g., oil inlet, air inlet, scavenge outlet, etc.). <FIG> illustrates electrical conductors <NUM> that connect to the electrical connectors <NUM> by a respective adapter <NUM>. The adapters <NUM> are configured to receive the electrical conductors <NUM> and provide for an electrical interface between the electrical conductors <NUM> and the electric generator housed within the generator housing <NUM>. As such, the adapters <NUM> may be considered terminal blocks of the system.

The adapters <NUM> can provide fixed connection between the electrical conductors <NUM> and a respective electrical connector <NUM> of the generator housing <NUM>. The adapters <NUM> are configured to enable both physical and electrical connection between the electrical conductors <NUM> and a respective electrical connector <NUM>.

<FIG> illustrates the tail cone assembly <NUM> with the generator housing <NUM> and interior electric generator installed relative to casings of a gas turbine engine. For example, as shown, the generator housing <NUM> is installed radially inward from a first casing <NUM>, which in turn is arranged radially inward from a second casing <NUM>, similar to that shown and described above. A number of hollow struts <NUM> are arranged to connect the first casing <NUM> to the second casing <NUM>. As shown, the electrical conductors <NUM> are arranged to pass through the hollow struts <NUM> from the second casing <NUM> to the first casing <NUM> and to engage with a respective electrical connector <NUM>. An adapter <NUM> is arranged between each electrical conductor <NUM> and a respective electrical connector <NUM> to enable electrical connection between the electrical conductors <NUM> and the electric generator installed and housed within the generator housing <NUM>. Also shown in <FIG>, various fluid lines <NUM> are installed through respective hollow struts <NUM> to provide for fluid connections with the electric generator installed and housed within the generator housing <NUM>. Such fluid lines <NUM> may provide for inlets and/or outlets for fluids such as, without limitation, oil and air.

Turning now to <FIG>, schematic illustrations of a part of a tail cone assembly <NUM> in accordance with an embodiment of the present disclosure are shown. <FIG> illustrates a partially transparent isometric illustration of a portion of the tail cone assembly <NUM> and <FIG> is a radially inward view of the portion of the tail cone assembly <NUM>. The tail cone assembly <NUM> may be similar to that shown and described above. In the view of <FIG>, a generator housing <NUM> is shown radially inward from an first casing <NUM> and a second casing <NUM>, similar to that shown and described above. A hollow strut <NUM> extends between the first casing <NUM> and the second casing <NUM>.

As shown, an electrical conductor <NUM> passes through the hollow strut <NUM>. The electrical conductor <NUM> in these illustrations comprises three separate wires or cables, and may be configured as a three-phase electrical conductor. The hollow strut <NUM> defines an interior cavity <NUM> that openly connects to a first casing opening <NUM> of the first casing <NUM> and to a second casing opening <NUM> of the second casing <NUM>. As such, an open path or conduit is defined between the first casing <NUM> and the second casing <NUM> through which the electrical conductor <NUM> can pass. As shown, an adapter <NUM> is arranged to fit within the interior cavity <NUM> of the hollow strut <NUM> and within the first casing opening <NUM> of the first casing <NUM>. The adapter <NUM> provides for an electrical interface or connection between the electrical conductor <NUM> and an electrical connector of the generator housing <NUM>.

Turning now to <FIG>, schematic illustrations of a portion of a tail cone assembly <NUM> in accordance with an embodiment of the present disclosure are shown. <FIG> is an isometric illustration of an adapter <NUM> shown relative to a generator housing <NUM> to enable connection of an electrical conductor <NUM> to an electric generator housed within the generator housing <NUM>. <FIG> illustrates a partial transparent illustration of the adapter <NUM> as connected to an electrical conductor <NUM> of the generator housing <NUM>. <FIG> illustrates a top down cross-sectional illustration of the adapter <NUM> as viewed along the line C-C of <FIG>. <FIG> is a cross-sectional illustration of the adapter <NUM> as viewed along the line D-D of <FIG>. The tail cone assembly <NUM> may be similar to that shown and described above. The adapter <NUM> and the electrical conductor <NUM> may be configured to fit within an interior cavity of a hollow strut, such as shown above.

The adapter <NUM> includes an adapter body <NUM> and an adapter cover <NUM>. The adapter cover <NUM> may be removably attached to the adapter body <NUM> by one or more fasteners <NUM>. In this illustrative configuration, the electrical conductor <NUM> may pass through the adapter cover <NUM> to enable an electrical connection within the adapter <NUM>, as described below. The adapter body <NUM> is configured to be installed to an electrical connector <NUM> of the generator housing <NUM>. One or more electrical pins 716a, 716b, 716c are configured to extend from the electric generator and pass through the electrical connector <NUM> of the generator housing <NUM>. The electrical conductor <NUM> includes respective wires 718a, 718b, 718c, which are configured to each electrically connect to one of the electrical pins 716a, 716b, 716c through an electrical connection within the adapter <NUM>.

As shown in <FIG>, one or more bus bars 720a, 720b, 720c are arranged within the adapter <NUM> to provide an electrical connection between each wire 718a, 718b, 718c of the electrical conductor <NUM> and the electrical pins 716a, 716b, 716c. As such, an electrical connection can be achieved between the electrical conductor <NUM> and an electric generator within the generator housing <NUM>. The adapter housing <NUM> and the adapter cover <NUM> may be made of an electrically insulating material such that the electrical paths through the adapter <NUM> is defined by respective sets of wires 718a, 718b, 718c, bus bars 720a, 720b, 720c, and electrical pins 716a, 716b, 716c. The electrical pins 716a, 716b, 716c may be supported within the electrical connector <NUM> by respective pin supports 722a, 722b, 722c, as shown in <FIG>.

The adapter <NUM> may be attached to or otherwise connected to the generator housing <NUM> by an attachment mechanism. In the illustrative embodiment of <FIG>, the attachment mechanism is provided by a bracket <NUM> that can be fastened to a bracket support <NUM> using one or more fasteners <NUM>. As shown, the bracket <NUM> is a separate element from the adapter <NUM>. In other embodiments, the bracket functionality may be integrated into one or both of the adapter body <NUM> and the adapter cover <NUM>. Further, in some embodiments, the adapter body <NUM> may be formed to provide for a snap-connection or other direct connection between the adapter body and the generator housing and/or the electrical connector thereof.

Advantageously, embodiments of the present disclosure can enable improved electrical connection and power supply and distribution on an engine and/or aircraft. For example, embodiments described herein may enable installation of power sources within limited-access locations, such as tail cones of gas turbine engines. At the tail of gas turbine engines, the environment and installation limits the size and nature of components installed. As discussed above, a tail cone can be hollow and enable the installation of an electric generator therein. Embodiments described herein enable efficient electrical routing by using adapters and electrical connectors that allow for electrical conductors to be installed and pass through hollow struts that are arranged about the tail cone of the gas turbine engine.

In some embodiments, advantageously, a generator housing can be configured to multiple electrical connectors (e.g., terminal posts) that allow for electrical connection to an electric generator within the tail cone. The electrical connectors can be configured to electrical pins to provide three-phase electrical transmission, and thus three-phase can be distributed from the electric generator at multiple locations. Such multiple electrical connectors can improve power quality and reduce electromagnetic interference within the power system.

As used herein, the terms "about" and "substantially" are intended to include the degree of error associated with measurement of the particular quantity based upon the equipment available at the time of filing the application. For example, the terms may include a range of ± <NUM>%, or <NUM>%, or <NUM>% of a given value or other percentage change as will be appreciated by those of skill in the art for the particular measurement and/or dimensions referred to herein.

It should be appreciated that relative positional terms such as "forward," "aft," "upper," "lower," "above," "below," "radial," "axial," "circumferential," and the like are with reference to normal operational attitude and should not be considered otherwise limiting.

Claim 1:
A tail cone assembly (<NUM>) for a gas turbine engine comprising:
a tail cone;
a generator housing (<NUM>) having an electrical connector (<NUM>), the generator housing defining a longitudinal axis, the generator housing arranged within the tail cone;
a first casing (<NUM>) arranged radially outward from the generator housing relative to the longitudinal axis, the tail cone extending axially from the first casing;
a second casing (<NUM>) arranged radially outward from the first casing relative to the longitudinal axis;
a hollow strut (<NUM>) extending radially between the first casing and the second casing and defining an interior cavity, the hollow strut located circumferentially relative to the longitudinal axis at a location circumferentially aligned with the electrical connector of the generator housing;
an electrical conductor (<NUM>) arranged within the interior cavity of the hollow strut; and
an adapter (<NUM>) configured to electrically connect the electrical conductor with the electrical connector of the generator housing, wherein the adapter is an elongate structure that fits within the interior cavity of the hollow strut.