A hybrid power tri-propeller helicopter apparatus for efficient and quiet flying includes a helicopter body, a cockpit portion, an engine portion, a tail boom portion, a gas motor, a generator, a battery pack, and an electric nose motor. A nose propeller and a lift propeller support are coupled to the helicopter body. A pair of electric lift motors is coupled to the lift propeller support and is in operational communication with the battery pack. A pair of lift propellers is coupled to the pair of lift motors. A tail fin and a pair of horizontal rear stabilizer fins are coupled to the tail boom portion. A pair of front stabilizer fins is coupled to the cockpit portion. A plurality of controls is coupled to the cockpit portion and is in operational communication with the nose motor, the pair of lift motors, and the pair of rear stabilizer fins.

An assembly is provided for an aircraft propulsion system. This assembly includes an exhaust center body and a duct system. The exhaust center body includes an exterior skin. The duct system is fluidly coupled with a plurality of exterior skin perforations in the exterior skin. The duct system is configured to direct bypass air received from a bypass flow path within the aircraft propulsion system to the exterior skin perforations.

A exhaust nozzle assembly comprises a nozzle that extends about an axial centerline and includes an exhaust nozzle flange; an radially inner surface that comprises an axially forward inner surface; a noise attenuating structure; a through hole inlet formed in the axially forward inner surface; a through hole outlet formed in the axially rear inner surface. The nozzle assembly also includes a radially outer surface that is radially separated from the radially inner surface by a nozzle cavity, where engine core air enters the nozzle cavity from the through hole inlet and exits the nozzle cavity axially downstream of the hole inlet via the through hole outlet.

Acoustic cores and methods for forming and for assembling acoustic cores are provided. For example, an acoustic core of a gas turbine engine comprises a first attenuation section having a first plurality of attenuation members and a first mating wall having a planar first mating surface. The first mating wall is integrally formed with at least a portion of the first plurality of attenuation members and defines a portion of a perimeter of the first attenuation section. A method for forming an acoustic core comprises additively manufacturing a first attenuation section of the acoustic core, which comprises a first plurality of attenuation members and a first mating wall that are integrally formed as a single unit. A method for assembling an acoustic core comprises applying an adhesive to mating surfaces of first and second attenuation sections and pressing together the mating surfaces to join the first and second attenuation sections.

An internal structure of a primary exhaust duct of a turbomachine, which has a primary wall allowing air to pass through orifices and forming an internal surface of the primary exhaust duct, an interior skin arranged inside the primary wall, and at least one separator of which a first edge region is attached to the interior skin and which has two geometries. A change from the first geometry to the second takes place when the temperature of the separator exceeds a first temperature, and the change from the second to the first takes place when the temperature of the separator drops below a second temperature. The coefficient of expansion of the separator is greater than that of the interior skin. The variation in the geometry of the separators depending on the temperature of the engine eases assembly at ambient temperature due to the compression of the separators.

An aft engine pylon fairing including a framework including lateral panels, transverse reinforcing ribs, and a heat shield linked to the framework. The heat shield has a multilayer structure comprising an insulating core configured both to constitute a thermal barrier and to damp acoustic waves, an outer skin configured to guide an aerodynamic flow and contribute to the acoustic damping, and an inner skin configured to ensure the mechanical strength of the shield. The shield multilayer structure allows the aft engine pylon fairing to contribute to the attenuation of the noise nuisances of the engine, and, also, to improve the thermal insulation conferred by the shield by allowing the use, for the insulating core of the shield, of materials having a better thermal resistance but a low mechanical rigidity, the mechanical strength being essentially ensured by the inner skin of the multilayer structure.

The present disclosure concerns an acoustic attenuation panel for an aircraft turbojet engine nacelle and a method for manufacturing this panel. The acoustic attenuation panel includes an alveolar central core interposed between an acoustic front skin comprising perforations and a rear skin, the acoustic attenuation panel including a front structure and a rear structure. The front structure includes the acoustic front skin and a first network of alveolar walls, the rear structure including the rear skin and a second network of alveolar walls, the first and second networks of alveolar walls being complementary so as to form, in an assembled position, the alveolar central core, the front structure and the rear structure being positioned opposite to each other and so that the network of alveolar walls of a structure is spaced from the skin of the other structure facing it by a clearance d.

A structural panel is provided that includes a first core structure and a second core structure. The first core structure is configured with a first endwall and a plurality of first cavities that extend vertically through the first core structure. The second core structure is configured with a second endwall and a plurality of second cavities that extend vertically through the second core structure. The second core structure is laterally bonded to the first core structure at a complex splice joint between the first endwall and the second endwall.

An assembly for a turbomachine includes an exhaust cone and an exhaust casing having an annular inner shell. The exhaust cone and the exhaust casing can extend about a first axis, the exhaust cone can have an outer surface extending in the projection of the inner shell, the exhaust cone can be connected to the exhaust casing by means of a flange, the flange having an upstream portion fastened to the exhaust casing and lugs extending downstream from said upstream portion, and the exhaust cone can be fastened to the lugs. The flange can be sectorized and include of a plurality of angular sectors arranged so as to be circumferentially adjacent, with each flange sector having at least one lug extending rectilinearly along a second axis parallel to the first axis.

An aerodynamic device defining a thickness direction is provided. The aerodynamic device configured to produce lift or thrust or configured to be a part of an aerodynamic system that produces lift or thrust. The aerodynamic device includes a cowl assembly that defines at least in part an airflow stream. The cowl assembly includes a first cowl and a second cowl moveable relative to the first cowl. The first cowl includes a plurality of first cowl indentations at an end of the first cowl. The second cowl defines an outer surface along the thickness direction and an inner surface along the radial direction. The second cowl includes a plurality of second cowl indentations complementary in shape to the plurality of first cowl indentations. The plurality of second cowl indentations are positioned locally on the outer surface of the second cowl or locally on the inner surface of the second cowl.