Main gas duct internal seal of a high-pressure turbine

摘要

A high-pressure turbine of a gas-turbine engine provided with a turbine disk ( 1 ) carrying rotor blades ( 2 ) and with stator blades ( 3 ), and with a lateral wheel cavity ( 5 ) being formed between the turbine disk ( 1 ) and the stator ring ( 4 ), wherein a seal ( 8 ) is provided in axial direction between stator blade platforms ( 6 ) and rotor blade platforms ( 7 ) and which is arranged radially outwardly adjacent a main gas duct ( 9 ).