Fuel supply circuit for a combustion chamber of a turbomachine

A fuel supply circuit for a combustion chamber of a turbomachine, in particular an aircraft, comprising:

• a supply channel configured for the circulation of a first fuel flow from a fuel tank;
• a metering unit configured to provide a predetermined flow rate of fuel into the combustion chamber;
• at least one supply pump for circulating the fuel from the tank towards the metering unit;
• a recirculation channel for a second fuel flow, corresponding to a quantity of excess fuel from the metering unit, upstream of the supply pump;
• the supply and recirculation channels opening in different directions upstream of the supply pump;
• wherein the circuit comprises a distribution device of at least one of the fuel flows which comprises an internal conduit for the flow of the first fuel flow, an external annular gorge for the flow of the second fuel flow and at least one orifice for the passage of the second flow which is in fluidic communication with the annular gorge, and in that said at least one orifice and said internal conduit are coaxial and open respectively upstream of the supply pump.