Patent ID: 8534999

Claim:
Gas turbine comprising at least a combustion chamber ( 2 ), a guide vane row ( 3 ) and a rotor airfoil row, said guide vane row ( 3 ) comprising a plurality of guide vane airfoils comprising a blade ( 7 ) and an inner platform ( 8 ), wherein a ratio between a pitch (P) and a leading edge diameter (D) of the guide vane airfoils is between 6.3-7.6 and a ratio between a platform length (L) and the leading edge diameter (D) of the guide vane airfoils is between 4.0-5.5, the platform length (L) is defined by the axial distance between a leading edge ( 15 ) of a guide vane blade ( 7 ) and an inner guide vane platform inlet ( 16 ) measured at half height of the guide vane blade ( 7 ).