Gasturbinenmotor mit Verdichterzapfluftsystem zur Brennkammerstarthilfe

Details

Veröffentlichungs-Nr.

EP4166770

Aktenzeichen

EP22198976

Anmeldetag

30. September 2022

Veröffentlichung

17. September 2025

Erteilung

17. September 2025

Rechtsraum

EP

IPC

F02C3/08F02C6/08F02C7/262

Abstract

A gas turbine engine includes a combustor having a combustor air inlet, an axial-centrifugal compressor, a shroud, a secondary flow duct, and a valve. The shroud surrounds at least a portion of the axial-centrifugal compressor and has a surge bleed plenum defined therein that is in fluid communication with, and receives compressed air from, the axial compressor outlet. The secondary airflow duct has a duct inlet that is in fluid communication with the surge bleed plenum, and a duct outlet that is in fluid communication with the combustor air inlet. The valve is mounted on the secondary airflow duct and is movable between a closed position, in which the secondary airflow duct does not provide fluid communication between the surge bleed plenum and the combustor air inlet, and an open position, in which the secondary airflow duct provides fluid communication between the surge bleed plenum and the combustor air inlet.

Anmelder

Firma

Honeywell International Inc.

Land

🇺🇸 USA

Fachgebiete