A gas turbine engine for an aircraft includes an engine core including a first, lower pressure, turbine, a first compressor, and a first core shaft connecting the first turbine to the first compressor; and a second, higher pressure, turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor, and a fan located upstream of the engine core and including a plurality of fan blades extending from a hub. A low pressure turbine temperature change is defined as: the ⁢ ⁢ first ⁢ ⁢ turbine ⁢ ⁢ entrance ⁢ ⁢ temperature the ⁢ ⁢ first ⁢ ⁢ turbine ⁢ ⁢ exit ⁢ ⁢ temperature . A fan tip temperature rise is defined as: the ⁢ ⁢ fan ⁢ ⁢ tip ⁢ ⁢ rotor ⁢ ⁢ exit ⁢ ⁢ temperature the ⁢ ⁢ fan ⁢ ⁢ rotor ⁢ ⁢ entry ⁢ ⁢ temperature . A turbine to fan tip temperature change ratio of: the ⁢ ⁢ low ⁢ ⁢ pressure ⁢ ⁢ turbine ⁢ ⁢ temperature ⁢ ⁢ change the ⁢ ⁢ fan ⁢ ⁢ tip ⁢ ⁢ temperature ⁢ ⁢ rise is in the range from 1.46 to 2.0.