in the conventional manner with air being drawn in and compressed by the fan 14 and the compressors 18 the compressed air is mixed with fuel and air in the combustor the resultant exhaust gases expand through the turbines 22 24 and 26 and are exhausted through the exhaust nozzle 28 propulsive thrust is provided by the exhaust flow through the nozzle 28 and through air from the fan 14 which bypasses the compressors 18 referring now to fig2 turbine blade 30 forms part of an annular array of rotary aerofoil blades the turbine blade is hollow to permit the flow of cooling air from the compressor region 18 into the blade a shroud 32 is mounted on the tip of each blade 30 although it is envisaged that the present invention is equally applicable to shrouded and unshrouded blades a shroud liner 34 surrounds the blades and comprises a ring type structure the radially inner surface 36 of the shroud liner segments is provided with a ceramic coating to reduce the cooling heat flux required to maintain the shroud liner segments 34 at a suitable temperature a plurality seal segments 38 are attached to each shroud liner 34 the seal segment comprises a number of channels 40 high pressure flow from the high pressure compressor 18 is directed through channels 40 to provide cooling to the seal segment 38 each seal segment 38 is connected to a mounting element 42 through a u shaped slot 44 this mounting element is itself connected to the inner turbine casing 46 seal segment 38 is also mounted on a seal carrier 48 which is.