Fueldraulic heat management system

A gas turbine engine for an aircraft comprising:

• an engine core comprising a turbine, a combustor, a compressor, and a core shaft connecting the turbine to the compressor;
• a fan located upstream of the engine core and arranged to be driven by the core shaft, the fan comprising a plurality of fan blades;
• a nacelle surrounding the fan and the engine core and defining a bypass duct located radially outside of the engine core, where the bypass ratio, defined as the ratio of the mass flow rate of the flow through the bypass duct to the mass flow rate of the flow through the core at cruise conditions, is at least 4;
• a plurality of actuators, wherein at least one of the plurality of actuators is configured to actuate a bleed air valve;
• a controller;
• and
• a fuel supply system, wherein
• the fuel supply system is arranged to supply fuel for combustion in the combustor, and to supply fuel to fueldraulically drive the at least one actuator configured to actuate the bleed air valve, and
• the actuator is configured to actuate the bleed air valve to enable non-binary position adjustment between an open valve position and a closed valve position, and
• the controller is configured to control the actuator so that the non-binary position adjustment is based upon calorific value of the fuel.