Rotorzusammenbauten für ein Gasturbinentriebwerk

Details

Veröffentlichungs-Nr.

EP3851635

Aktenzeichen

EP21152129

Anmeldetag

18. Januar 2021

Veröffentlichung

14. Juni 2023

Erteilung

14. Juni 2023

Rechtsraum

EP

IPC

F01D5/30// F01D5/28C04B35/80

Abstract

A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk (180A), a second rotor disk (180B) and a plurality of rotor blades (104). The first rotor disk is configured to rotate about a rotational axis (102). The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is mounted to the first rotor disk and to the second rotor disk. The rotor blades include a first rotor blade (104). The first rotor blade includes an attachment (116) projecting axially along the rotational axis into a first pocket (196A) in the first rotor disk and a second pocket (196B) in the second rotor disk. The attachment has a dovetail cross-sectional geometry when viewed in a plane perpendicular to the rotational axis. A portion (186A) of the first rotor disk extends circumferentially across and covers the attachment.

Anmelder

Firmen

RTX Corporation
Raytheon Technologies Corporation

Land

🇺🇸 USA

Fachgebiete