A gas turbine shroud includes a ceramic abradable coating superior in abradable property and durability. The gas turbine ceramic abradable coating of the present invention is configured by an abradable metal layer and a porous ceramic abradable layer (3) (hardness RC15Y: 80±3), the porous ceramic abradable layer (3) is provided with slit grooves (4) by machining work, and a slit groove width (5) is 0.5 to 5 mm. Thereby, the abradable property, and durability against a thermal cycle and high-temperature oxidation are improved.
