公开(公告)号：US10995678B2

公开(公告)日：2021-05-04

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 ,  F01D11/24 ,  F02K3/075 ,  F02C7/18 ,  F01D25/24 ,  F02C3/04 ,  F01D25/12 ,  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.