Rotoranordnung eines Gasturbinentriebwerks

Details

Veröffentlichungs-Nr.

EP2574724

Aktenzeichen

EP12186435

Anmeldetag

27. September 2012

Veröffentlichung

25. April 2018

Erteilung

25. April 2018

Rechtsraum

EP

IPC

F01D5/06F01D5/30F01D11/00

Abstract

A rotor stack assembly (125) for a gas turbine engine includes a first rotor assembly (126A) and a second rotor assembly (126B) axially downstream from the first rotor assembly (126A). The first rotor assembly (126A) includes a first rim (138A), a first bore (140A) and a first web (142A) that extends between the first rim (138A) and the first bore (140A). The second rotor assembly (126B) includes a second rim (138B), a second bore (140B) and a second web (142B) that extends between the second rim (138B) and the second bore (140B). A tie shaft (147) is positioned radially inward of the first bore (140A) and the second bore (140B). The tie shaft (147) maintains a compressive load on the first rotor assembly (126A) and the second rotor assembly (126B). The compressive load is communicated through a first load path (LP1) of the first rotor assembly (126A) and a second load path (LP2) of the second rotor assembly (126B). At least one of the first load path (LP1) and the second load path (LP2) is radially inboard of the first rim (138A) and the second rim (138B). A corresponding gas turbine engine and a method of providing a rotor stack assembly are also provided.

Anmelder

Firma

United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete