Turbine blade for a gas turbine which is flowed through in particular axially, in particular for one of the highpressure turbine stages thereof, having a blade root and a blade airfoil comprising a pressure-side side wall and a suction-side side wall, which side walls (14, 16) extend along a spanwise direction from a root-side end to a blade tip and along a chordwise direction, which is oriented transversely to the spanwise direction, from a leading edge to a trailing edge, wherein, in the interior of the blade airfoil, a first cooling path for a first coolant stream (M 1) and a second cooling path, substantially separated from the first cooling path, for a second coolant stream (M 2) are formed, wherein the first cooling path comprises - a first coolant passage, which is configured for cyclone cooling of the leading edge, and - a second coolant passage, which adjoins the first coolant passage and extends below the blade tip from the leading edge in the direction of the trailing edge, wherein the second cooling path comprises - a serpentine coolant passage for cooling of a middle region of the blade airfoil, which middle region is arranged behind the leading-edge region in the chordwise direction, and - a first trailing-edge coolant passage for at least partial cooling of a trailing-edge region of the blade airfoil, which trailing-edge region is arranged behind the middle region in the chordwise direction and extends as far as the trailing edge, wherein the first trailing-edge coolant passage is connected in terms of flow to a multiplicity of first exit holes arranged in the trailing edge, wherein the first coolant passage and/or the serpentine coolant passage are/is free of exit holes and the first cooling path comprises - a third coolant passage, which adjoins the second coolant passage and extends mainly radially inwardly, and - a second trailing-edge coolant passage, which adjoins the third coolant passage and is configured for cooling of a blade-tip-side region of the trailing-edge region and is connected in terms of flow to a multiplicity of second exit holes arranged in the trailing edge. having a blade root and a blade airfoil comprising a pressure-side side wall and a suction-side side wall, which side walls (14, 16) extend along a spanwise direction from a root-side end to a blade tip and along a chordwise direction, which is oriented transversely to the spanwise direction, from a leading edge to a trailing edge, wherein, in the interior of the blade airfoil, a first cooling path for a first coolant stream (M 1) and a second cooling path, substantially separated from the first cooling path, for a second coolant stream (M 2) are formed, wherein the first cooling path comprises - a first coolant passage, which is configured for cyclone cooling of the leading edge, and - a second coolant passage, which adjoins the first coolant passage and extends below the blade tip from the leading edge in the direction of the trailing edge, - a first coolant passage, which is configured for cyclone cooling of the leading edge, and - a second coolant passage, which adjoins the first coolant passage and extends below the blade tip from the leading edge in the direction of the trailing edge, wherein the second cooling path comprises - a serpentine coolant passage for cooling of a middle region of the blade airfoil, which middle region is arranged behind the leading-edge region in the chordwise direction, and - a first trailing-edge coolant passage for at least partial cooling of a trailing-edge region of the blade airfoil, which trailing-edge region is arranged behind the middle region in the chordwise direction and extends as far as the trailing edge, - a serpentine coolant passage for cooling of a middle region of the blade airfoil, which middle region is arranged behind the leading-edge region in the chordwise direction, and - a first trailing-edge coolant passage for at least partial cooling of a trailing-edge region of the blade airfoil, which trailing-edge region is arranged behind the middle region in the chordwise direction and extends as far as the trailing edge, wherein the first trailing-edge coolant passage is connected in terms of flow to a multiplicity of first exit holes arranged in the trailing edge, wherein the first coolant passage and/or the serpentine coolant passage are/is free of exit holes and the first cooling path comprises - a third coolant passage, which adjoins the second coolant passage and extends mainly radially inwardly, and - a second trailing-edge coolant passage, which adjoins the third coolant passage and is configured for cooling of a blade-tip-side region of the trailing-edge region and is connected in terms of flow to a multiplicity of second exit holes arranged in the trailing edge. - a third coolant passage, which adjoins the second coolant passage and extends mainly radially inwardly, and - a second trailing-edge coolant passage, which adjoins the third coolant passage and is configured for cooling of a blade-tip-side region of the trailing-edge region and is connected in terms of flow to a multiplicity of second exit holes arranged in the trailing edge.