Rolls-royce Deutschland Ltd & Co. Kg

Rolls-royce Corporation

Airbus Defence and Space Gmbh

Itp Next Generation Turbines S.l.

Christoph Richter

Marco Rose

Reinhard Pongratz

Carlos Omar Marquez Gutierrez

Daniel Redmann

Fredi Holste

Gregory Mack

Jürgen Dierke

Adolfo Serrano González

Max Kern

Tom Hilton

Adolfo Serrano Gonzalez

The invention regards an acoustic liner which comprises: a facing sheet that comprises holes, the facing sheet having a porosity and a facing sheet thickness, a backing sheet, and a plurality of cells arranged between the facing sheet and the backing sheet, the cells having a cell depth and each cell defining a cavity. A plurality of internal necks are provided that extend from the inner side of the facing sheet towards the backing sheet, each internal neck being located around a hole of the facing sheet, thereby extending the longitudinal length of the hole. The invention further regards a gas turbine engine with such acoustic liner.

Acoustic liner and gas turbine engine with such acoustic liner

An engine pod for a gas turbine engine which includes a pod wall having an inside and an outside. The pod wall includes a fixed downstream portion and a displaceable upstream portion which is displaceable in the axial direction between a first upstream position and a second downstream position. At its downstream end facing the fixed portion, the upstream portion forms a radially outer rear edge and axially spaced therefrom a radially inner rear edge, with a recess in between. It is provided that adjacent to the recess, an air-permeable structure is formed in the upstream portion which is intended and configured, in the first upstream position of the displaceable portion, to conduct air flowing in the region of the recess to the inside of the displaceable portion. According to a further aspect of the invention, the axial position of the radially inner rear edge varies in the circumferential direction.

Engine nacelle for a gas turbine engine

A gas turbine engine for an aircraft includes: a flow path boundary, which delimits the flow path through the engine radially on the outside, and a lining, which lines the flow path boundary on the inside, at least along an axial section. Here, the lining includes a plurality of panels, which, in the circumferential direction of the flow path boundary, adjoin each other and which together line a circumferential area of 360&#xb0;, wherein each panel has two end faces, which each adjoin an end face of an adjacent panel. The panels are of beveled design at their end faces, such that two mutually adjoining panels form a V-shaped gap between them, the minimum clearance of which is realized at the inside of the panels. The panels can be sound-absorbing panels. Also disclosed is a panel for a gas turbine engine.

Gas turbine engine and panel for a gas turbine engine

A sound-absorbing arrangement for an engine nacelle includes a first damping structure that includes a sound-damping honeycomb structure between a perforated inner layer and an outer layer, wherein the first damping structure has a first section and a second section that are arranged behind one another in the axial direction. The arrangement further includes a second damping structure that is formed in a ring-shaped manner and adjoins the first damping structure in the second section of the same in the radially external direction. The second damping structure is formed by multiple hollow chambers that adjoin each other in the circumferential direction, wherein the hollow chambers are formed without a honeycomb structure.

Sound-damping arrangement for an engine nacelle and engine nacelle comprising such an arrangement

A sound absorber comprising a base body and a tongue (). The base body has a bottom plate, a wall enclosing the bottom plate and an opening enabling the entry of air into the base body. The tongue has a fixed end, a free end and a central portion disposed between the fixed and the free end. The free end of the tongue is spaced from the wall and the bottom plate, and the central portion of the tongue is disposed to extend at least partially straight along a width direction. Furthermore, a sound absorber assembly can include at least two sound absorbers, and an engine, in particular, for an aircraft, comprising such a sound absorber and/or such a sound absorber assembly.

Sound absorber, sound absorber assembly and an engine with a sound absorber assembly

An acoustic absorber includes a wall provided with a plurality of apertures as well as a substantially non-perforated second wall, with the first wall and the second wall being spacedly arranged to one another, and at least one honeycomb structure being provided between the walls, with the honeycomb structure having a substantially cylindrical recess in at least one area, with a funnel element opening to the first and second walls being provided in the recess, and having a height greater than the distance of the walls, with the second wall being designed pot-like in the area of the funnel element.

Growing community of inventors

Berlin, Germany

Christoph Richter