An aircraft nacelle air inlet comprising: a lip skin defining a curved surface of the inlet, the curved surface extending about a longitudinal axis of the inlet; a forward bulkhead; an inner barrel having a radially inner surface defining a surface of the inlet, a radially outer surface, and a sound attenuating layer arranged between the radially inner and radially outer surfaces; and a joining frame fixed to the lip skin and/or to the forward bulkhead. A first portion of the joining frame extends over at least a portion of the sound attenuating layer of the inner barrel and is fixed to the radially outer surface of the inner barrel.

A system and method for preventing icing in the combustion inlet air path of a gas turbine system. An air intake system of the gas turbine system supplies intake air to a gas turbine engine. The air intake system includes an air filter inlet house to filter the intake air. The air filter inlet house includes at least one filter stage having an array of pulse filters, with each of the pulse filters being hydrophobic. A combustion inlet air path is in fluid communication with the air intake system and the gas turbine engine. The combustion inlet air path receives the filtered air from the air filter inlet house and supplies the filtered air as combustion inlet air to an inlet of the gas turbine engine. A surface of at least one component in the combustion inlet air path includes an anti-icing coating to prevent ice from forming thereon.

An acoustic panel with a cellular core includes cells that are provided with one or more obstacles, each of the obstacles extending transversely in relation to the main axis of the associated cell so as to increase the length of the path (F) that sound waves travel through the cell. Methods enabling the production of such a panel implements steps of cutting, folding and bonding that are suitable for creating cells provided with such obstacles.

An acoustic panel with a cellular core includes cells that are provided with one or more obstacles, each of the obstacles extending transversely in relation to the main axis of the associated cell so as to increase the length of the path (F) that sound waves travel through the cell. Methods enabling the production of such a panel implements steps of cutting, folding and bonding that are suitable for creating cells provided with such obstacles.

A thrust reverser track beam may comprise a noise suppressing structure. The noise suppressing structure may form the airflow surface of the track beam. The noise suppressing structure may be riveted, bolted, or bonded to the track beam.

An aeroderivative gas turbine including an air intake plenum; a compressor with a compressor air intake in fluid communication with the air intake plenum; a combustor; a high pressure turbine; a power turbine. A forced air-stream generator is arranged in fluid communication with the air intake plenum. A shutter arrangement is provided in a combustion-air flow path, arranged and controlled to close the combustion-air flow path for pressurizing said air intake plenum by means of the forced air-stream generator to a pressure sufficient to cause pressurized air to flow through the aeroderivative air turbine.

A fan case assembly adapted for use with a gas turbine engine includes a fan track liner and an annular case. The fan track liner extends circumferentially at least partway about a central axis of the gas turbine engine. The annular case is configured to support the fan track liner at a radial position relative to the central axis. The fan case assembly further includes an air recirculation duct configured to redirect air around the fan track liner.

An acoustic panel for a gas turbine engine, includes a panel body, a panel-body cover, and a support bracket. The panel body is configured to dampen vibrations caused by the gas turbine engine. The forward support bracket is configured to mount the acoustic panel to portions of the gas turbine engine.

An acoustic panel for a gas turbine engine, includes a panel body, a panel-body cover, and a support bracket. The panel body is configured to dampen vibrations caused by the gas turbine engine. The forward support bracket is configured to mount the acoustic panel to portions of the gas turbine engine.

Aspects of the disclosure regard a fan case assembly for a gas turbine engine, the fan case assembly comprising a fan case having an inner surface, a fan track liner comprising abradable material layer, and a rear acoustic panel arranged aft of the fan track liner. The fan track liner and the rear acoustic panel are integrated into a single panel structure attached to the fan case inner surface.