HEAT EXCHANGE SYSTEM FOR AIRCRAFT ENGINE

A heat exchange system (40) for an aircraft engine (10) includes a heat exchanger (41), a main conduit (42) directing fuel to a combustion chamber of the aircraft engine (10), and a pump (44) connected to the main conduit (42). A return conduit (46) receives excess fuel outputted by the pump (44) and exceeding a fuel requirement of the combustion chamber. The return conduit (46), which is connected to a fuel conduit (46) of the heat exchanger (41), has an inlet connected to the main conduit (42) downstream of the pump (44) and an outlet connected to the main conduit (42) upstream of the pump (44). An actuator (45) has an inlet (45A) connected to the main conduit (42) downstream of the pump (44) and an outlet (45B) connected to the main conduit (42) upstream of the pump (44) while bypassing the heat exchanger (41), wherein a pressure differential between the actuator inlet (45A) and the actuator outlet (45B) remains substantially unchanged with variations of a fuel flow through the heat exchanger (41).