GAS TURBINE

In a gas turbine with a rotor (11) and a blade (10) is attached to said rotor (11), wherein said blade (3) comprises an airfoil (14), a blade root (12) at the lower end of said airfoil (14) provided for being removably received by a groove (31) in said rotor (11), and a hollow blade core (18) arranged within said airfoil (14) and extending along the longitudinal axis (X) between said blade root (12) and said blade tip (15), for the flow of a cooling fluid, which enters said blade core (18) through a blade inlet (20) at said blade root (12), and is supplied by means of a rotor bore (23), which runs through the rotor (11) and is in fluid communication with said blade inlet (20) of said blade, whereby said blade inlet (20) has a cross section area which exceeds the cross section area of said rotor bore (23) in at least one direction, said rotor bore (23) having a diffuser-shaped rotor bore exit (24), such that the cross section area of the rotor bore exit (24) at the interface between rotor bore (23) and blade inlet (20) covers the cross section area of the blade inlet (20).