Gedämpfte Verkleidungsanordnung

Details

Veröffentlichungs-Nr.

EP4745389

Anmeldetag

13. November 2025

Veröffentlichung

20. Mai 2026

Rechtsraum

EP

Abstract

A bypass duct (22) of a turbofan gas turbine engine (10) includes a first shroud (26) extending at least partially around an axis (A) and a second shroud (24) extending at least partially around the axis (A), the second shroud (24) being radially spaced apart from the first shroud (26) to define a bypass passage between the first (26) and second (24) shrouds. The bypass duct (22) further includes a fairing (12,12',12") disposed in the bypass passage. The fairing (12,12',12") includes a first outer shell (32A,32A',32A") and a second outer shell (32B,32B',32B") defining therebetween an internal passage (30,30',30"). The first (32A,32A',32A") and second (32B,32B',32B") outer shells extend radially from the first shroud (26) to the second shroud (24). A plate (40,40',40") extends across the internal passage (30,30',30") between the first (32A,32A',32A") and second (32B,32B',32B") outer shells. A damper (42,42',42") is engaged with the plate (40,40',40") between the first (32A,32A',32A") and second (32B,32B',32B") outer shells.

Anmelder

Firma

Pratt & Whitney Canada Corp.

Land

🇨🇦 Kanada