Zwischenwellenklingendichtung

Details

Veröffentlichungs-Nr.

EP3428389

Aktenzeichen

EP18172139

Anmeldetag

14. Mai 2018

Veröffentlichung

31. März 2021

Erteilung

31. März 2021

Rechtsraum

EP

IPC

F01D5/02F01D11/02F16J15/00F16J15/02F16J15/3232F16J15/3292

Abstract

A gas turbine engine (20) includes a first rotor shaft (40) and a second rotor shaft (50) around the first rotor shaft (40). A knife edge seal (62) is radially between the first rotor shaft (40) and the second rotor shaft (50), and is connected to one of the first rotor shaft (40) or the second rotor shaft (50). The knife edge seal (62) is sized radially to form a gap (84) between the knife edge seal (62) and the other of the first rotor shaft (40) or the second rotor shaft (50). A plurality of blades (66) having a general airfoil shape is between the first rotor shaft (40) and the second rotor shaft (50) proximate the knife edge seal (62). The plurality of blades (66) is connected to the first rotor shaft (40) or the second rotor shaft (50), and a second gap (86) is formed radially between the plurality of blades (66) and the other of the first rotor shaft (40) or the second rotor shaft (50).

Anmelder

Firmen

Raytheon Technologies Corporation
United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete