Coating system for gas turbines

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The invention relates to a coating system for a gas turbine blade and/or a gas turbine sheet , in particular a material of a ceramic matrix component "CMC" (Ceramic matrix Component) and/or a monolithic ceramic. The coating system comprises a tread layer for protection from environmental conditions such as humidity and thereon at least a combined layer, oxygen and against the penetration of CMAS, which layer at least one ceramic component, a spinel (mg, Zn, Fe, Mn) of the general formula 2 O4-Al, (RE1, RE2) AlO a perovskite of the general formula 3, wherein for a trivalent cation of a rare earth element RE1 and RE2 may be equal or unequal, and/or a grenades having a general formula a oxyapatite ( [...] ) Al 12 wherein 5 O RE1, RE2 and RE3 are each a trivalent cation of a rare earth-member and may be the same or different, comprises, as well as any mixtures of the aforementioned compounds.