Exhaust section for an aircraft gas turbine engine

An exhaust section for an aircraft gas turbine engine, comprising:

• an exhaust nozzle in a downstream serial flow relationship with the gas turbine engine, and defining an exhaust cavity through which combustion exhaust gases of the engine are emitted in a direction defining an exhaust vector;
• and
• a magnetohydrodynamic (MHD) generator having a magnetic field generator forming a magnetic field having at least some magnetic field lines perpendicular to the exhaust vector, and at least one electrically coupled electrode pair, comprising at least one positive electrode and at least one negative electrode, arranged relative to the exhaust cavity wherein movement of charged particles entrained in the exhaust gas along the exhaust vector generates current between the at least one electrode pair;
• wherein the conversion of exhaust gas enthalpy into electric current by the MHD generator increases the propulsion efficiency of the gas turbine engine by reducing the exhaust gas temperature.