US 11,920,499 B2
Gas turbine engine with improved VIGV shielding
Geoffrey B Jones, Burton-on-Trent (GB); Edward J Spalton, Derby (GB); and Duncan A Macdougall, Derby (GB)
Assigned to ROLLS-ROYCE plc, London (GB)
Filed by ROLLS-ROYCE plc, London (GB)
Filed on Mar. 17, 2023, as Appl. No. 18/122,807.
Application 18/122,807 is a continuation of application No. 17/514,977, filed on Oct. 29, 2021, granted, now 11,634,993.
Claims priority of application No. 2018264 (GB), filed on Nov. 20, 2020.
Prior Publication US 2023/0220780 A1, Jul. 13, 2023
This patent is subject to a terminal disclaimer.
Int. Cl. F01D 9/04 (2006.01); F01D 5/14 (2006.01); F01D 9/02 (2006.01); F01D 17/16 (2006.01); F01D 25/02 (2006.01); F02C 7/042 (2006.01); F02K 3/06 (2006.01); F04D 29/56 (2006.01)
CPC F01D 9/041 (2013.01) [F01D 9/04 (2013.01); F01D 17/162 (2013.01); F02C 7/042 (2013.01); F05D 2220/32 (2013.01); F05D 2220/323 (2013.01); F05D 2240/12 (2013.01)] 20 Claims
OG exemplary drawing
 
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°.