A center plug (206) for attenuating noise in a gas turbine engine (122) includes an inner skin (430), the inner skin (430) having a substantially cylindrical shape and extending along an axial centerline (A); an outer skin (416) positioned radially outside...

A gas turbine engine exhaust cone (40) comprising one or more acoustic absorption chambers (48), each chamber (48) comprising two side walls (50) and an acoustic attenuation wall (62). The side walls (50) define the circumferential extent of the chamber (4...

The present application provides a clocked combustor can array (370) for coherence reduction in a gas turbine engine having a number of combustor cans (380) positioned in a circumferential array (300). A first set (375) of the plurality of combustor cans (...

A flexible component 100 comprises a core element 110 provided with a heat protection assembly 140. The heat protection assembly comprises an intumescent coil wrap 120 that extends around the core element 110. The coil wrap 120 is arranged such that it is ...

A gas turbine combustor comprises: a combustor liner through which a combustion gas flows that is produced by combusting a fuel jetted from nozzles; and a first resonator and a second resonator mounted on the outer surface of the combustor liner. The secon...

A disclosed embodiment provides an acoustic panel having a composite laminate panel having a back sheet layer (106), a face sheet layer (104), and a core layer (102) disposed therebetween. The core layer has one or more depressions at an interface between ...

It is described a combustion arrangement (100), comprising: a casing (101); a combustion chamber (103) arranged within the casing (101), wherein an inner casing volume (107, 109) is defined to be a volume inside the casing but outside the combustion chambe...

A laser ignition system for an internal combustion engine, and more specifically a gas turbine engine, is provided. The system including a laser light source configured to generate a laser beam, an ignition port configured to provide optimized optical acce...

It is described a resonator device (101, 301) for damping a pressure oscillation within a combustion chamber (330), the resonator device comprising: a container (102, 302) filled with a gas; an opening (106, 306) in the container; and a heating element (10...

Noise reduction conduit for non rotary components of aircraft engines, subjected to a characteristic range of temperatures of a gas turbine engine, constituted by an annular structure composed of an aerodynamic wet wall (10a, 10b), perforated and resistant...