Thermoinsulating tile for a combustion chamber of a gas turbine

Gas turbine combustion chamber comprising

• a thermoinsulating coating having a plurality of thermoinsuiating tiles including first thermoinsulating, tiles and second thermoinsulating tiles wherein a portion of the first thermoinsulating tiles are engaged with a portion of the second thermoinsulating tiles to form the thermoinsulating coating in the gas turbine combustion chamber,
• the first thermoinsuiating tiles arranged in a region where a risk of damage of the thermoinsulating tiles is statistically enhanced relative to at least one other region of the combustion chamber due to an operating parameter of temperature or vibration, wherein each first thermoinsulating tile in the region comprises:
• a thermoinsulating material body having a first face and a second face:
• a sealed chamber encapsulated in the thermoinsulating material body between the first face and the second face and containing a marker substance, the marker substance having at least a component which is in a liquid state at least at a temperature of use of the first thermoinsulating tiles.