GAS TURBINE ENGINE

A gas turbine engine includes an annular combustion chamber (7) and a plurality of combustors (6) communicating with the annular combustion chamber (7). Each combustor (6) defines a respective gas flow path (20) along a respective combustor axis (C) and has a first combustor stage (6a) and a second combustor stage (6b), sequentially arranged along the respective gas flow path (20). The second combustor stages (6b) of the combustors (6) are configured to discharge into the annular combustion chamber (7).