An acoustic attenuation structure for a gas turbine engine includes a periodic structure having a first unit cell, the first unit cell having a first central body and a first axial tube disposed on the first central body and a second axial tube disposed on the first central body, opposite the first axial tube, each of the first axial tube and the second axial tube being in fluid communication with one another through the first central body.

An airflow profile structure having a leading and/or trailing edge profiled with a serrated profile. The serrated profile has a succession of teeth and depressions, characterized in that, along the leading and/or trailing edge, from a first location to a second location, the teeth of the serrated profile are individually inclined towards the second location.

An airflow profile structure having a leading and/or trailing edge profiled with a serrated profile. The serrated profile has a succession of teeth and depressions, characterized in that, along the leading and/or trailing edge, from a first location to a second location, the teeth of the serrated profile are individually inclined towards the second location.

A component for a gas turbine engine includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge, the airfoil extending radially from a platform to a tip, a tip pocket formed in the tip and terminating prior to the trailing edge, and one or more heat transfer augmentation devices formed in the tip pocket.

A variable geometry inlet system of an aircraft engine includes an inlet duct. The inlet duct includes at least first and second sections moveable between extended and retracted positions such that the inlet duct defines a variable axial length of an inlet passage for selective flight conditions. The inclusion of acoustic treatment may assist in controlling noise.

A variable geometry inlet system of an aircraft engine includes an inlet duct. The inlet duct includes at least first and second sections moveable between extended and retracted positions such that the inlet duct defines a variable axial length of an inlet passage for selective flight conditions. The inclusion of acoustic treatment may assist in controlling noise.

A noise attenuation panel for a structure within a propulsion system includes a first plurality of unit cells; and a second plurality of unit cells, the second plurality of unit cells merged within the first plurality of unit cells, the first plurality of unit cells including a first periodic structure having a first unit cell, a second unit cell, a third unit cell and a fourth unit cell, each of the first unit cell, the second unit cell, the third unit cell and the fourth unit cell including a central body interconnected via a plurality of lateral tubes extending from the central body, the first periodic structure forming a first lateral layer of unit cells.

The present invention provides compartment(s) for a turbine engine, comprising a main compartment for receiving the turbine engine and an intake compartment disposed on a side of the main compartment. The intake compartment comprises: an intake compartment body, a gas filter device and a muffler device. The gas filter device and the muffler device are disposed outside the intake port of the intake compartment. The compartment unit is configured to have a first gas path which permits air for combustion in the turbine engine to pass from the external through the gas filter device and the first muffler device in turn into the intake compartment body, and then be delivered through the exhaust port of the intake compartment to the turbine engine in the main compartment.

The present invention provides compartment(s) for a turbine engine, comprising a main compartment for receiving the turbine engine and an intake compartment disposed on a side of the main compartment. The intake compartment comprises: an intake compartment body, a gas filter device and a muffler device. The gas filter device and the muffler device are disposed outside the intake port of the intake compartment. The compartment unit is configured to have a first gas path which permits air for combustion in the turbine engine to pass from the external through the gas filter device and the first muffler device in turn into the intake compartment body, and then be delivered through the exhaust port of the intake compartment to the turbine engine in the main compartment.

An assembly for a gas turbine engine has: a fan case with a forward end, an aft end, and an inner surface extending from the forward end of the fan case to the aft end of the fan case; an acoustic liner having a forward end, an aft end, and an acoustic liner body that extends continuously from the forward end of the acoustic liner to the aft end of the acoustic liner; an inlet case located forward of the forward end of the fan case, the forward end of the acoustic liner being secured to the inlet case, and wherein the acoustic liner body is positioned against an inner surface of the inlet case and an inner surface of the fan case, and the aft end of the acoustic liner is secured to the fan case between the forward end and the aft end of the fan case.