Bifurcation integrated electrical system for hybrid aircraft propulsion system

A system for an aircraft, comprising:

• a fan rotor;
• an engine core configured to drive rotation of the fan rotor about an axis;
• a fan case housing the fan rotor;
• a core case housing the engine core;
• a bifurcation extending radially across a bypass flowpath, the bypass flowpath downstream of the fan rotor and radially between the core case and the fan case;
• a first inner electrical component arranged with the engine core and having a first operating power greater than twenty kilowatts;
• a second inner electrical component arranged with the engine core and having a second operating power less than twenty kilowatts;
• a first outer electrical component mounted to the fan case;
• a second outer electrical component mounted to the fan case;
• a first line electrically coupling the first inner electrical component to the first outer electrical component;
• and
• a second line electrically coupling the second inner electrical component to the second outer electrical component;
• and
• a non-conductive barrier;
• the first line and the second line run in parallel through the bifurcation and, in an upstream direction, to a split location at the fan case, the first line runs in a first circumferential direction along the fan case away from the split location to the first outer electrical component, and the second line runs in a second circumferential direction along the fan case opposite the first circumferential direction and away from the split location to the second outer electrical component, and
• the non-conductive barrier separating the first line from the second line as the first line and the second line run in parallel through the bifurcation and from the bifurcation to the split location,
• wherein the first line is configured for an operating current greater than one hundred amps, and the second line is configured for an operating current less than fifty amps.

A system for an aircraft, comprising:

• a fan rotor;
• an engine core configured to drive rotation of the fan rotor about an axis;
• a fan case housing the fan rotor;
• a core case housing the engine core;
• a lower bifurcation radially crossing a bypass flowpath, the bypass flowpath downstream of the fan rotor and located radially between the fan case and the core case;
• a plurality of electric machines operatively coupled to the engine core and radially next to the core case;
• a plurality of control units mounted to the fan case at a first lateral side of the fan case;
• an electrical bus mounted to the fan case vertically above the plurality of control units and at the first lateral side of the fan case, the electrical bus electrically coupled to each of the plurality of control units;
• a plurality of electrical lines extending between and electrically coupling the plurality of electric machines to the plurality of control units, the plurality of electrical lines extending radially outward through the lower bifurcation and, in an axially forward and upstream direction, from the lower bifurcation to the fan case;
• and
• an engine controller mounted to the fan case at a second lateral side of the fan case opposite the first lateral side of the fan case,
• wherein each electrical line in a first set of the plurality of electrical lines is configured for an operating current greater than one hundred amps, and each electrical line in a second set of the plurality of electrical lines is configured for an operating current less than fifty amps.