A gas turbine engine comprising: - a fan rotating about an engine main axis and generating a core airflow and a bypass airflow; - a core duct, across which the core airflow flows; - an engine core comprising: - a compressor for compressing the core airflow and comprising a plurality of stages, each stage comprising a row of rotor blades and a row of stator vanes, a fist stage of said plurality of stages being arranged at an inlet of the compressor; - combustion equipment; and - a turbine connected to the compressor through a shaft; - an Engine Section Stator comprising a plurality of ESS vanes and arranged in the core duct downstream of the fan, each ESS vane comprising an ESS leading edge and an ESS trailing edge; and - a plurality of variable inlet guide vanes (VIGV) adapted to rotate about a pivot axis and arranged in the core duct downstream of the ESS and upstream of the compressor, each variable inlet guide vanes (VIGV) comprising a VIGV leading edge and an VIGV trailing edge, wherein a mid-span ESS leading edge point is arranged at a first radius R1 from the engine main axis and a mid-span VIGV leading edge point is arranged at a second radius R2 from the engine main axis, the mid-span ESS leading edge point being at an axial distance L from the mid-span VIGV leading edge point, characterised in that the ratio ΔR/L of a difference ΔR between the first radius R1 and the second radius R2 to the axial distance L is comprised between 0.23 and 0.70, preferably between 0.40 and 0.70, and in that the VIGV vanes are arranged angularly rotated with respect to the ESS vanes such that first longitudinal planes passing through the engine main axis, extending radially therefrom, and through respective 70% span ESS leading edge points are rotated with respect to corresponding second longitudinal planes passing through the engine main axis, extending radially therefrom, and through respective 70% span VIGV pivot axis points by a rotation angle α comprised between 0.1° and 6°. - a fan rotating about an engine main axis and generating a core airflow and a bypass airflow; - a core duct, across which the core airflow flows; - an engine core comprising: - a compressor for compressing the core airflow and comprising a plurality of stages, each stage comprising a row of rotor blades and a row of stator vanes, a fist stage of said plurality of stages being arranged at an inlet of the compressor; - combustion equipment; and - a turbine connected to the compressor through a shaft; - a compressor for compressing the core airflow and comprising a plurality of stages, each stage comprising a row of rotor blades and a row of stator vanes, a fist stage of said plurality of stages being arranged at an inlet of the compressor; - combustion equipment; and - a turbine connected to the compressor through a shaft; - an Engine Section Stator comprising a plurality of ESS vanes and arranged in the core duct downstream of the fan, each ESS vane comprising an ESS leading edge and an ESS trailing edge; and - a plurality of variable inlet guide vanes (VIGV) adapted to rotate about a pivot axis and arranged in the core duct downstream of the ESS and upstream of the compressor, each variable inlet guide vanes (VIGV) comprising a VIGV leading edge and an VIGV trailing edge, wherein a mid-span ESS leading edge point is arranged at a first radius R1 from the engine main axis and a mid-span VIGV leading edge point is arranged at a second radius R2 from the engine main axis, the mid-span ESS leading edge point being at an axial distance L from the mid-span VIGV leading edge point, characterised in that the ratio ΔR/L of a difference ΔR between the first radius R1 and the second radius R2 to the axial distance L is comprised between 0.23 and 0.70, preferably between 0.40 and 0.70, and in that the VIGV vanes are arranged angularly rotated with respect to the ESS vanes such that first longitudinal planes passing through the engine main axis, extending radially therefrom, and through respective 70% span ESS leading edge points are rotated with respect to corresponding second longitudinal planes passing through the engine main axis, extending radially therefrom, and through respective 70% span VIGV pivot axis points by a rotation angle α comprised between 0.1° and 6°.