Getriebeturbolüfter mit Überdrehzahlschutz

Details

Veröffentlichungs-Nr.

EP3940214

Aktenzeichen

EP21186237

Anmeldetag

16. Juli 2021

Veröffentlichung

17. April 2024

Erteilung

17. April 2024

Rechtsraum

EP

IPC

F02C7/36F02C3/107

Abstract

A gas turbine engine (100) includes a fan shaft (110) rotatable about an axis (A), a fan (112) connected to the fan shaft (110), and an outer housing (114) surrounding the fan (112) to define a bypass passage (B). A compressor section (24) has both a low pressure compressor (106) that is fixed to rotate with the fan shaft (116) and a high pressure compressor (124). A turbine section (28) has a low pressure turbine (104) driving a low speed spool (116) and a high pressure turbine (122) driving the high pressure compressor (124). The low pressure turbine (104) includes rotating blades and a static structure (130) aft of the rotating blades. A fan drivetrain (120) includes a geared architecture (102) connecting the low speed spool (116) to the fan shaft (110) such that the fan (112) and low pressure compressor (106) rotate at a lower speed than the low pressure turbine (104). A thrust bearing (132) is axially aft of the geared architecture (102) and axially forward of the high pressure compressor (122). A tower shaft (140) is rotatably driven by the low speed spool (116).

Anmelder

Firmen

RTX Corporation
Raytheon Technologies Corporation

Land

🇺🇸 USA

Fachgebiete