Patent ID: 9371778
Filing Date: 2016-06-21
CPC Classification: B64D,F02C,F02K,Y02T

Claim Text:
1. An engine casing assembly of an aircraft gas turbine comprising: a fan casing; a radially inner honeycomb-structured layer arranged on the fan casing in a flow direction upstream of a fan in an area of an inflow-side air inlet, the honeycomb-structured layer including a plurality of chambers; sound-absorbing elements arranged radially outside at least one axial section of the honeycomb-structured layer, the elements extending in an axial direction and being arranged annularly next to one another in a circumferential direction; an intermediate chamber having a first end and a second end, the intermediate chamber extending substantially in the axial direction between the first end and the second end and having a first length extending between the first end and the second end; each sound-absorbing element including: