Verkleidungsanordnung für einen Gasturbinenmotor

Details

Veröffentlichungs-Nr.

EP4793478

Anmeldetag

11. Februar 2026

Veröffentlichung

19. August 2026

Rechtsraum

EP

IPC

F02C6/20, F02C7/04, F02K3/02

Abstract

A gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section in serial flow order. A fan section defines an axial centerline and a rotor and includes a fan and a spinner assembly drivingly coupled to the turbomachine. The rotor supports a plurality of fan blades being rotatable about the axial centerline in a circumferential direction. A cowl assembly is positioned aft of at least a portion of the spinner assembly. The cowl assembly and the spinner assembly define at least part of an airflow surface rotatable with the fan and exposed to a fan airflow provided to and through the fan during operation of the gas turbine engine. The cowl assembly is at least partly cantileverly supported by the rotor.

Anmelder

Firmen

General Electric Company
GE Aerospace Poland Sp. z o.o.

Land

🇺🇸 USA

Fachgebiete