A gas turbine engine comprising: - a fan mounted to rotate about a main longitudinal axis to produce a bypass flow and a core engine flow; - an engine core, comprising in axial flow series a compressor, a combustor, and a turbine coupled to the compressor through a shaft, wherein the compressor is an intermediate pressure compressor, the gas turbine engine further comprising a high pressure compressor downstream of the intermediate pressure compressor; the turbine is an intermediate pressure turbine, the gas turbine engine further comprising a high pressure turbine upstream of the intermediate pressure compressor; and the shaft is a first shaft, the gas turbine engine further comprising a second shaft coupling the high pressure turbine to the high pressure compressor; - an inlet duct to guide the core engine flow to the compressor; - a reduction gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; - an engine section stator arranged in the inlet duct upstream of the compressor, the engine section stator comprising a plurality of vanes with respective leading edges defining a first annulus area in the inlet duct, a mid-span leading edge point of the engine section stator vanes being arranged at a first radius from the main longitudinal axis; wherein the compressor comprises a first rotor with a row of first blades with respective leading edges defining a second annulus area in the inlet duct; a mid-span leading edge point of the compressor first blades being arranged at a second radius from the main longitudinal axis and at an axial distance from the engine section stator vane mid-span leading edge point, and wherein a ratio (A2/A1) of the second annulus area to the first annulus area is equal or greater than 0.80, and a ratio (ΔR/L) of a difference (ΔR) between the first radius and the second radius to the axial distance is equal or greater than 0.23; and the gas turbine engine further comprises a variable inlet guide vane arranged in the inlet duct between the engine section stator and the first rotor of the compressor. - a fan mounted to rotate about a main longitudinal axis to produce a bypass flow and a core engine flow; - an engine core, comprising in axial flow series a compressor, a combustor, and a turbine coupled to the compressor through a shaft, wherein the compressor is an intermediate pressure compressor, the gas turbine engine further comprising a high pressure compressor downstream of the intermediate pressure compressor; the turbine is an intermediate pressure turbine, the gas turbine engine further comprising a high pressure turbine upstream of the intermediate pressure compressor; and the shaft is a first shaft, the gas turbine engine further comprising a second shaft coupling the high pressure turbine to the high pressure compressor; - an inlet duct to guide the core engine flow to the compressor; - a reduction gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; - an engine section stator arranged in the inlet duct upstream of the compressor, the engine section stator comprising a plurality of vanes with respective leading edges defining a first annulus area in the inlet duct, a mid-span leading edge point of the engine section stator vanes being arranged at a first radius from the main longitudinal axis; wherein the compressor comprises a first rotor with a row of first blades with respective leading edges defining a second annulus area in the inlet duct; a mid-span leading edge point of the compressor first blades being arranged at a second radius from the main longitudinal axis and at an axial distance from the engine section stator vane mid-span leading edge point, and wherein a ratio (A2/A1) of the second annulus area to the first annulus area is equal or greater than 0.80, and a ratio (ΔR/L) of a difference (ΔR) between the first radius and the second radius to the axial distance is equal or greater than 0.23; and the gas turbine engine further comprises a variable inlet guide vane arranged in the inlet duct between the engine section stator and the first rotor of the compressor.