Aircraft power plant

A cooling system for a liquid cooled internal combustion power plant housed in an engine compartment in a tail cone of an aircraft, the cooling system comprising:

• a tail cone inlet defined through a wall of the tail cone and fluidly communicating with an environment outside the aircraft, the tail cone inlet located at an end of the tail cone;
• a wall inlet defined through a firewall of the engine compartment;
• a blower within the engine compartment and having a blower inlet and a blower outlet, the blower inlet fluidly communicating with the environment via the tail cone inlet, via the wall inlet, and via an interior of the engine compartment;
• an outlet defined through a wall of the aircraft and fluidly communicating with the environment, the blower outlet fluidly connected to a shroud duct extending within the tail cone from the firewall to the outlet;
• a cooling flow path extending from the tail cone inlet to the air outlet and across the wall inlet, the cooling flow path in heat exchange relationship with the liquid cooled internal combustion power plant;
• and an exhaust duct fluidly connected to an exhaust of the liquid cooled internal combustion aircraft power plant and to the environment, the exhaust duct extending within the shroud duct.