Patent ID: 7938618
Filing Date: 2011-05-10
Classification: B64C,B64D,F02C,F04D,F05D,Y02T

Abstract:
1. Device for silencing a helicopter gas turbine engine, having a compressor ( 10 ) and a compressor air supply passage ( 12 ) opening at an upstream end through an outer opening ( 12 a ) delimited by a metallic casing ( 14 ) of the engine, the silencing device comprising air intake lips ( 30 , 32 ) which define an air intake ( 34 ) for the compressor air supply passage, which have inner ends ( 30 b , 32 b ) for connection to the metallic casing along the passage outer opening ( 12 a ) and which are at least partially formed by a sound attenuator ( 40 , 42 ) calculated to attenuate sound frequencies produced by the compressor rotation.