GAS TURBINE ENGINE

A propulsive aircraft gas turbine engine (103) comprises a turbine (208, 209) disposed in a gas turbine engine core (201) flow and a recuperator heat exchanger (218) disposed downstream of the turbine (208, 209) in gas turbine engine core flow, the recuperator heat exchanger (218) being configured to transfer heat from the gas turbine engine core flow to gas turbine engine fuel. The recuperator heat exchanger (218) is configured to accommodate a portion of the gas turbine engine core flow therethrough, the remainder being bypassed around the recuperator heat exchanger.