Gasturbinenmotor

Details

Veröffentlichungs-Nr.

EP3181824

Aktenzeichen

EP16205138

Anmeldetag

19. Dezember 2016

Veröffentlichung

27. November 2019

Erteilung

27. November 2019

Rechtsraum

EP

IPC

F02C7/36F04D29/66F01D5/02F01D5/10F01D5/14F01D5/16F01D5/26F01D5/30F02C7/04F02K3/06F04D29/32

Abstract

A gas turbine engine (20; 100) comprises a fan rotor (42; 103; 150; 170; 196; 230; 242; 274) having fan blades (98; 152, 154; 172, 176; 182, 190; 220; 232, 234; 240; 276, 282) received within an outer nacelle (94). The fan blades (98...282) are provided with at least a first type (152; 172; 182; 232; 276) having a first natural frequency, and a second type (154; 176; 190; 234; 282) having a second natural frequency. The fan rotor (42...274) has a first mount structure intended for the first type (152...276) and a distinct second mount structure intended for the second type (154...282). The first type (152...276) of fan blade fits into the first mount structure intended for the first type, but there is a first obstruction preventing the first type (152...276) of fan blade from being placed into the second mount structure intended for the second type. The second type (154...282) of fan blade fits into the second mount structure intended for the second type, but there is a second obstruction preventing the second type (154...282) of fan blade from being placed into the first mount structure intended for the first type.

Anmelder

Firma

United Technologies Corporation

Land

🇺🇸 USA

Fachgebiete