Gas turbine temperature sensor

A gas turbine engine for an aircraft comprising:

• an engine core comprising a turbine, a compressor, a combustor arranged to combust a fuel, and a core shaft connecting the turbine to the compressor;
• a fan located upstream of the engine core;
• an oil loop system arranged to supply oil to cool at least one engine component;
• a fuel-oil heat exchanger through which the oil in the oil loop system and the fuel flow such that heat is transferred from the oil to the fuel;
• and
• a refrigeration cycle apparatus through which the oil in the oil loop system and the fuel flow, the refrigeration cycle apparatus being arranged to transfer further heat from the oil to the fuel,
• wherein the fuel-oil heat exchanger and the refrigeration cycle apparatus are arranged to transfer heat to the fuel such that fuel temperature on entry to the combustor is higher than a maximum oil temperature within the oil loop system.