Gasturbinentriebwerk

Details

Veröffentlichungs-Nr.

EP3434906

Aktenzeichen

EP18184461

Anmeldetag

19. Juli 2018

Veröffentlichung

27. Januar 2021

Erteilung

27. Januar 2021

Rechtsraum

EP

IPC

F02K3/075F02C7/18F01D11/24F02C9/18

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 for entry of 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 É(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. É is the real mass flow of the compressed air exiting the compressor, T30 is the temperature of the compressed air exiting the compressor, and P30 is the pressure of the compressed air exiting the compressor. The air system is configured such that said portion of the compressed air is at least 2% of the total compressed air exiting the compressor.

Anmelder

Firma

Rolls-Royce plc

Land

🇬🇧 Großbritannien

Fachgebiete