Air system for aircraft propulsion system electric machine

An assembly for an aircraft propulsion system, comprising:

• a fan rotor;
• an engine core configured to power operation of the fan rotor, the engine core including a compressor section, a combustor section and a turbine section;
• a core flowpath extending through the compressor section, the combustor section and the turbine section, and an airflow inlet into the core flowpath disposed next to and downstream of the fan rotor;
• a bypass flowpath extending outside of and bypassing the engine core, an airflow inlet into the bypass flowpath disposed next to and downstream of the fan rotor;
• a vane structure including an inner platform, an outer platform and a plurality of vanes, the inner platform forming an inner peripheral boundary of the core flowpath through the vane structure, the outer platform forming an outer peripheral boundary of the core flowpath through the vane structure, the plurality of vanes arranged circumferentially about an axis in an array, each of the plurality of vanes extending radially across the core flowpath from the inner platform to the outer platform, the plurality of vanes including a first vane and a second vane, and the first vane disposed at a top-dead-center location circumferentially around the axis;
• a tail cone structure forming an inner peripheral boundary of the core flowpath downstream of the vane structure, the tail cone structure comprising an internal cavity;
• an electric machine disposed within the internal cavity;
• and
• an air system configured to direct air from the bypass flowpath, radially inward across the core flowpath through the second vane while bypassing the first vane, into the tail cone structure to cool the electric machine, the air system including an inlet axially aligned with and radially outboard of the vane structure.

An assembly for an aircraft propulsion system, comprising:

• a vane structure including an inner platform, an outer platform, a plurality of vanes and a first mount, the inner platform forming an inner peripheral boundary of a flowpath through the vane structure, the outer platform forming an outer peripheral boundary of the flowpath through the vane structure, the plurality of vanes arranged circumferentially about an axis in an array, each of the plurality of vanes extending radially across the flowpath from the inner platform to the outer platform, the plurality of vanes including a first vane and a second vane, the first mount connected to the outer platform and circumferentially aligned with the first vane, and the first mount configured for securing the vane structure to a pylon structure;
• a tail cone structure forming an inner peripheral boundary of the flowpath downstream of the vane structure, the tail cone structure comprising an internal cavity;
• an electric machine disposed within the internal cavity;
• and
• an air system configured to direct air from an air source radially outboard of the flowpath, radially inward across the flowpath through the second vane while bypassing the first vane, into the tail cone structure to cool the electric machine;
• wherein the air system comprises a first air circuit projecting radially across the flowpath through the second vane, and a first circuit inlet into the first air circuit is fluidly coupled to the air source and axially and circumferentially aligned with the second vane, and the first circuit inlet configured as an air scoop inlet of the air system.