Aircraft Propulsion System With Internal Compartment Ventilation

An assembly for an aircraft, comprising:

• an engine core including a compressor section, a combustor section and a turbine section;
• an engine case housing the engine core;
• a nacelle wall radially outboard of and covering the engine case, wherein a compartment is formed by and extends radially between the engine case and the nacelle wall;
• and
• an air circuit including a heat exchange leg, a bypass leg, a heat exchanger and an outlet, the air circuit configured to direct air from an air source through at least one of the heat exchange leg or the bypass leg to the outlet for injection into the compartment;
• the heat exchange leg and the bypass leg fluidly coupled in parallel and upstream of the outlet, the heat exchange leg extending through the heat exchanger, and the bypass leg extending around the heat exchanger.

An assembly for an aircraft, comprising:

• an engine core including a compressor section, a combustor section and a turbine section;
• an engine case housing the engine core;
• a nacelle wall radially outboard of and covering the engine case, wherein a compartment is formed by and extends radially between the engine case and the nacelle wall;
• and
• an air circuit including a heat exchanger and an outlet, the air circuit configured to direct air from an air source through the heat exchanger to the outlet for injection into the compartment;
• an electric machine system comprising an electric machine system component;
• and
• a fluid circuit configured to cool the electric machine system component using a liquid working fluid, the heat exchanger further fluidly coupled inline along the fluid circuit.