Rotorstufe eines Gasturbinentriebwerks mit Rotorblattdämpferanordnung

Details

Veröffentlichungs-Nr.

EP4807141

Anmeldetag

4. März 2026

Veröffentlichung

16. September 2026

Rechtsraum

EP

IPC

F01D5/22, // F01D11/00

Abstract

A rotor stage for a gas turbine engine is provided that includes a disk, first and second rotor blades (152, 252), a platform seal (72), and a damper (70). The first and second rotor blades (152, 252) are attached to the disk and adjacent. The first rotor blade (152) has a first neck portion and a first platform (158), and the second rotor blade (252) has a second neck portion and a second platform (258). The first rotor blade (152) has a first lateral rail (166) that extends laterally outward from a first neck portion surface, and has a first damper post (168) that extends laterally outward from the first neck portion surface. The second rotor blade (252) has a second lateral rail (266) that extends laterally outward from a second neck portion surface, and has a second damper post (268) that extends laterally outward from the second neck portion surface. The damper (70) is circumferentially disposed between the first and second lateral rails (166, 266).

Anmelder

Firma

RTX Corporation

Land

🇺🇸 USA

Fachgebiete