Propulsion system for an aircraft comprising an at least partially ventilated pipe circuit

A propulsion system for an aircraft, comprising:

• a tank which is designed to contain a fuel and to be arranged in a wing of said aircraft, said tank comprising a first connection interface;
• a turbojet, comprising:
• an engine having a second connection interface;
• and
• a fan designed to blow an airflow from the front to the rear of the aircraft, a third connection interface being arranged inside the airflow upstream of the fan;
• a pipe circuit comprising a first connector and a single-skin conduit extending between said first connection interface of said tank and said first connector, and a second pipe portion comprising:
• a second connector arranged between said first connector and said second interface of said engine;
• a first double-skin conduit extending between said first connector and said second connector;
• and
• a second double-skin conduit extending between said second connector and said second interface of said engine,
• wherein said first and second double-skin conduits each comprise a central conduit delimiting a central channel in which said fuel flows and a peripheral conduit extending about said central conduit and delimiting with said central conduit a peripheral channel;
• wherein said second connector ensures a fluidic continuity between the central channels of the first and second double-skin conduits and a fluidic continuity between the peripheral channels of the first and second double-skin conduits;
• wherein said second connector comprises an inlet orifice which opens into said peripheral channel of the first double-skin conduit or of the second double-skin conduit;
• and
• said pipe circuit also comprising an air supply conduit fluidically connecting said third connection interface of the fan and said inlet orifice so as to cause a part of said airflow from the fan to flow into said peripheral channels of the first and second double-skin conduits.