Kompressoranordnung für einen Gasturbinenmotor

Details

Veröffentlichungs-Nr.

EP4123143

Aktenzeichen

EP22185830

Anmeldetag

19. Juli 2022

Veröffentlichung

3. Mai 2023

Rechtsraum

EP

IPC

F02C3/107F02K3/06

Abstract

A gas turbine engine (20) includes a fan section (22) that drives air along a bypass flow path in a bypass duct (13). A gear reduction is in driving engagement with the fan (42) and has a gear reduction ratio of greater than 3.0 and less than 4.0. A low spool (30) includes a low pressure turbine (46) that drives a low pressure compressor (44) and drives the gear reduction to drive the fan (42) at a speed slower than the low pressure turbine (46). The low pressure compressor (44) includes a greater number of stages than the low pressure turbine (46). A high spool (32) includes a high pressure turbine (54) that drives a a nine stage high pressure compressor (52) that includes a pressure ratio per stage of greater than or equal to 1.20 and less than or equal to 1.33.

Anmelder

Firmen

RTX Corporation
Raytheon Technologies Corporation

Land

🇺🇸 USA

Fachgebiete