Patent ID: 11920499
Assignee: ROLLS-ROYCE PLC
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. 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 first 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 (ESS) 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 (VIGVs) adapted to rotate about a pivot axis and arranged in the core duct downstream of the ESS and upstream of the compressor, each of the plurality of variable inlet guide vanes (VIGVs) comprising a VIGV leading edge and a VIGV trailing edge, and
wherein the plurality of VIGVs are arranged angularly rotated with respect to the plurality of ESS vanes such that first longitudinal planes passing through respective 70% span ESS leading edge points are angularly rotated with respect to corresponding second longitudinal planes passing through respective 70% span VIGV pivot axis points by a rotation angle α comprised between 0.1° and 6°.