Module for an aircraft turbine engine

A turbine engine module comprising:

• an annular casing having an internal wall forming a channel wall, and
• a bladed stator surrounded by the casing and comprising an annular external platform and an annular internal platform between which stator blades extend, the external platform having an outer face facing the internal wall of the casing comprising an annular slot facing outwards and housing a sealing device, the sealing device coming into cylindrical contact with a track on the inner wall of the casing,
• wherein the internal wall of the casing comprises a thermal barrier made of ceramic material directly above the track, the track being arranged between the thermal barrier and the sealing device, and
• wherein the ceramic material of the thermal barrier is of the yttria-stabilized zirconia type.

A turbine engine module comprising:

• an annular casing having an internal wall forming a channel wall, and
• a bladed stator surrounded by the casing and comprising an annular external platform and an annular internal platform between which stator blades extend, the external platform having an outer face facing the internal wall of the casing comprising an annular slot facing outwards and housing a sealing device, the sealing device coming into cylindrical contact with a track on the inner wall of the casing,
• wherein the internal wall of the casing comprises a thermal barrier made of ceramic material directly above the track, the track being arranged between the thermal barrier and the sealing device and the ceramic material of the thermal barrier has a thermal conduction coefficient substantially between 0.5 and 2.5 W/(m·° C.), and
• wherein the ceramic material of the thermal barrier is of the yttria-stabilized zirconia type.