FUEL MANAGEMENT SYSTEM

There is provided a fuel management system (500A) for a gas turbine engine (10), the fuel management system (500A) comprising a fuel supply line (510) configured to supply fuel from a system inlet (520) to a combustor (16) of the gas turbine engine via a combustor pump (530) and combustor valve (550). A heat exchanger (540) is configured to reject heat from a thermal load (44) of the gas turbine engine (10) to fuel in the fuel supply line (510) between the system inlet (520) and the combustor valve (550). There is a downstream recirculation line (511) configured to recirculate a downstream excess portion of fuel from the fuel supply line (510), the downstream recirculation line (511) extending from a downstream recirculation point (512) on the fuel supply line (510) between the heat exchanger (540) and the combustor valve (550).