Air system for aircraft propulsion system electric machine

An assembly for an aircraft propulsion system, comprising:

• a low pressure compressor section comprising a low pressure compressor rotor;
• a high pressure compressor section comprising a high pressure compressor rotor;
• a combustor section;
• a turbine section;
• a flowpath comprising a flowpath inlet and a flowpath exhaust, the flowpath extending through the low pressure compressor section, the high pressure compressor compression section, the combustor section and the turbine section from the flowpath inlet to the flowpath exhaust;
• a tail cone structure forming an inner peripheral boundary of the flowpath at the flowpath exhaust, the tail cone structure comprising an internal volume;
• an electric machine disposed within the internal volume;
• and
• an air system configured to direct air into the tail cone structure to cool the electric machine, the air system configured to bleed the air from the flowpath along the low pressure compressor section during a first mode of operation, and the air system configured to receive the air from an air source outboard of the flowpath during a second mode of operation;
• wherein the low pressure compressor section is fluidly coupled inline along the flowpath between the flowpath inlet and the high pressure compressor section;
• and
• wherein the air system comprises a circuit inlet disposed along a downstream half of the low pressure compressor rotor in the low pressure compressor section, the air system being configured to bleed the air from the flowpath along through the circuit inlet.

An assembly for an aircraft propulsion system, comprising:

• an open propulsor rotor;
• an engine core configured to power rotation of the open propulsor rotor, the engine core comprising a first compressor section, a second compressor section, a combustor section and a turbine section, and the first compressor section including a compressor rotor;
• a flowpath extending through the first compressor section, the second compressor section, the combustor section and the turbine section from a flowpath inlet to a flowpath exhaust;
• a tail cone structure forming an inner peripheral boundary of the flowpath at the flowpath exhaust, the tail cone structure comprising an internal volume;
• an electric machine disposed within the internal volume;
• and
• an air system configured to direct air, bled from the flowpath upstream of a combustor in the combustor section, into the tail cone structure to cool the electric machine;
• wherein the first compressor section is fluidly coupled inline along the flowpath between the flowpath inlet and the second compressor section;
• and
• wherein the air system comprises a circuit inlet disposed along the flowpath in the first compressor section upstream of an end of the compressor rotor, the air system being configured to bleed the air from the flowpath through the circuit inlet.