GAS TURBINE ENGINE

A gas turbine engine, which may be a turbofan gas turbine engine that may optionally be geared, and in particular arrangements of turbine blades around an exhaust nozzle of an engine core of such a turbine. Example embodiments include a gas turbine engine for an aircraft comprising: an engine core (11) comprising a turbine (19), a compressor (14), and a core shaft (26) connecting the turbine to the compressor, the engine core (11) comprising an inlet upstream of the compressor (14) and an exhaust nozzle at a downstream outlet of the turbine (19); a fan (23) located upstream of the engine core inlet; and a set of exhaust nozzle vanes spanning the exhaust nozzle, the turbine (19) comprising a first row of turbine blades upstream of the exhaust nozzle vanes and a second row of turbine blades downstream of the exhaust nozzle guide vanes, one or more of the exhaust nozzle guide vanes comprising a passage configured to direct airflow downstream from the first row of turbine blades towards the second row of turbine blades.