公开(公告)号：US20190032574A1

公开(公告)日：2019-01-31

申请号：US16044869

申请日：2018-07-25

Applicant: ROLLS-ROYCE plc

Inventor： Alan R. MAGUIRE ,  Timothy J. SCANLON ,  Luis F. LLANO ,  Paul A. SELLERS

IPC: F02C9/18 ,  F02C3/04 ,  F02K3/06

Abstract: A gas turbine engine has a core engine including: a compressor, combustion equipment which receives compressed air from the compressor, a circumferential row of nozzle guide vanes, and a turbine. The nozzle guide vanes defines a throat receiving hot working gases from the combustion equipment into the turbine. The gas turbine engine further has an air system which is switchably operable between an on-position which opens a diversion pathway along which a portion of the compressed air exiting the compressor bypasses the combustion equipment to join the hot working gases at re-entry holes located between the nozzle guide vanes and a rotor at the front of the turbine, thereby increasing the semi-dimensional mass flow ω(T30)0.5/(P30) of the core engine at the exit of the compressor, and an off-position which closes the diversion pathway, thereby decreasing the semi-dimensional mass flow of the core engine at the exit of the compressor.

公开(公告)号：US20200141330A1

公开(公告)日：2020-05-07

申请号：US16666928

申请日：2019-10-29

Applicant: ROLLS-ROYCE PLC

Inventor： Luis F. LLANO ,  Arthur L. ROWE

IPC: F02C9/18 ,  F02C3/073

Abstract: A control system for a gas turbine engine includes an engine core, the engine core including combustion equipment, a turbine, a compressor, and a core shaft connecting the turbine to the compressor. The control system includes at least one variable stator vane for controlling the angle at which gas enters the engine core, and there is a bypass passage within the engine core for directing gas flow to bypass the combustion equipment.