A turbofan gas turbine engine (110) comprises a fan (24) and an intake duct (134) upstream of the fan (24). The fan (24) comprises a fan rotor (26) having a plurality of fan blades (28). The intake duct (134) has a liner, the liner comprising an acoustic liner (154) positioned upstream of the fan (24) and a buzz-saw tone noise liner (152) positioned upstream of the acoustic liner (154). The buzz-saw tone noise liner (152) is positioned substantially at, or near, an upstream end (134A) of the intake duct (134). The intake duct (134) has a lip (156) and the buzz-saw tone noise liner (152) is positioned at, or near, the lip (156).
An intake duct liner for a turbofan gas turbine engine
Einlasskanaleinlage für ein Mantelstromtriebwerk
Revêtement de conduit d'admission pour un turboréacteur à double flux
2018-09-26
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
Turbofan duct liner design-optimization: A statistical method
Online Contents | 2008
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