SOUND ATTENUATION APPARATUS AND METHOD

摘要

An aircraft engine sound attenuation apparatus includes a perforated face member, a backing member, a plurality of connecting members coupling the perforated face member to the backing member to form a plurality of channels spanning from the perforated face member to the backing member, and a bulk absorber disposed in each of the plurality of channels, wherein the plurality of channels are connected to an interior portion of an aircraft engine nacelle component so that the plurality of channels are oriented in a direction substantially normal to a direction of fluid flow pressure drop passing through the aircraft engine.

主权项

1. An aircraft engine sound attenuation apparatus comprising:
a perforated face member; a backing member; a plurality of connecting members coupling the perforated face member to the backing member to form a plurality of channels spanning from the perforated face member to the backing member; and a bulk absorber disposed in each of the plurality of channels; wherein the plurality of channels are connected to an interior portion of an aircraft engine nacelle component so that the plurality of channels are oriented in a direction substantially normal to a direction of fluid flow pressure drop passing through the aircraft engine, and each channel has a width, in the direction substantially normal to the direction of fluid flow pressure drop passing through the aircraft engine, that at least one of prevents or mitigates sound propagation inside the channel substantially parallel to a surface of the channel in the direction substantially normal to the direction of fluid flow pressure drop passing through the aircraft engine.