GAS TURBINE ENGINE

A gas turbine engine comprises a fan, a compressor, a combustor, and a turbine coupled to the compressor through a shaft, wherein the compressor comprises a first stage with respective rotor blades and stator vanes with a leading edge, a trailing edge and a tip, the blades and vanes being separated by axial gaps. A tip axial distance between the blade trailing edge of the first rotor and the vane leading edge of the first stator is equal to d × inlet flow function 10 , wherein d is equal or greater than 23 mm and less than 40 mm, and the inlet flow function is defined as dimensionless value of m T P , wherein m is a mass airflow at an inlet to the compressor in kg/s, T is the total temperature at the inlet to the compressor in K, and P is the total pressure at the inlet to the compressor in kPa at the compressor aerodynamic design point.