Gas turbine performance

Abstract

A method of operating a gas turbine engine is disclosed, the gas turbine engine including a combustor arranged to combust a fuel and a fuel management system arranged to provide the fuel to the combustor. The fuel management system includes two fuel-oil heat exchangers through which oil and the fuel flow, the heat exchangers arranged to transfer heat to the fuel and comprising a primary fuel-oil heat exchanger and a secondary fuel-oil heat exchanger; and a fuel pump arranged to deliver the fuel to the combustor, wherein the fuel pump is located between the two heat exchangers. The method includes controlling the fuel management system so as to raise the fuel temperature to at least 135° C. on entry to the combustor at cruise conditions.

Dependencies are inferred from the claim text.