A method is provided for coating a hollow, internally cooled blade (1) of a gas turbine, in which method an outer coating (5) comprising an MCrAlY-based bonding layer (6) and a ceramic thermal barrier layer (9) of zirconium oxide is applied to the base material (3) of the blade (1) on the outer side of the blade (1) and an inner coating (4) comprising a Cr diffusion layer (7) is applied to the base material (3) of the blade (1) on the inner side of the blade (1). The MCrAlY-based bonding layer (6) is thereby applied to the finished blade (1). At the same time, along with the inner coating (4), the Cr diffusion layer (7) is also applied to the MCrAlY-based bonding layer (6) of the outer coating (5) by chemical vapor deposition. Subsequently, an Al diffusion layer (8) and an outer brittle Al build-up layer are applied by chemical vapor deposition to the bonding layer (6) coated with the Cr diffusion layer (7). After that, the outer brittle Al build-up layer is removed by an abrasive treatment and the ceramic thermal barrier layer (9) is applied to the Al diffusion layer (8).