The invention relates to a rotor for a turbomachine, having at least one blade and having at least one rotor main part, which has at least one recess, in which a blade root of the least one blade is interlockingly received, wherein the blade root comprises at least one depression, in which at least one protrusion of the at least one rotor main part which protrusion delimits the at least one recess in regions is received, wherein the at least one depression is delimited by a first delimiting face on the blade root side and the at least one protrusion is delimited by a second delimiting face on the rotor main part side. At least the first delimiting face has at least one elevation which narrows a gap at least in regions, which extends between the first delimiting face and the second delimiting face.

An interspatial blocker for a thrust reverser system of a turbofan engine, and a thrust reverser system and a turbofan engine incorporating the same. The interspatial blocker includes a first and second flap that rotate from a stored position to a blocking position, and a leading-edge structure rotatably coupling the first flap to the second flap. The leading-edge structure is set up to be installed in a fan nacelle of a turbofan engine in a substantially radial orientation such that the first flap rotates in a first direction about a first axis extending in a substantially radial direction from the stored position to the blocking position, and such that the second flap rotates in a second direction about a second axis extending in the substantially radial direction from the stored position to the blocking position, with the first direction being opposite to the second direction.

A turbine engine that includes an engine core, an inner cowl, an outer cowl and an accessory gearbox. The engine core includes at least a compressor section, a combustion section, and a turbine section in axial flow arrangement. The accessory gearbox is operably coupled to the engine core and includes a first portion and a second portion.

A heat exchanger for a gas turbine engine includes a heat exchanger body having a first surface and a second surface oriented at least partially at an oblique angle relative to the first surface. The heat exchanger body defines a plenum extending between the first and second surfaces. Furthermore, the heat exchanger body defines a fluid passage extending through the second surface such that the fluid passage is in fluid communication with the plenum. The fluid passage, in turn, includes first and second portions. The first portion intersects the plenum at an intersection and defines a line of projection extending normal to the second surface. The second portion defines a line of projection extending normal to the first surface. The fluid passage further includes a curved portion extending from the first portion to the second portion.

A two-dimensional variable area plug (2D VAP) nozzle assembly for a high-speed flight vehicle. In one embodiment, a 2D VAP nozzle assembly comprises a nozzle including a plurality of sidewalls; a plug body within the nozzle, the plug body abutting at least two of the plurality of sidewalls; a first convergent flap hingedly connected to at least one of the plurality of sidewalls; and a second convergent flap hingedly connected to at least one of the plurality of sidewalls. In one embodiment, the nozzle assembly includes only a first convergent flap and a second convergent flap, without diverging flaps. The 2D VAP nozzle assembly has a simplified design with reduced sidewall length, which results in reduced manufacturing and maintenance costs.

The invention relates to design and production methods for a rotor which is both a turbine and a propeller having blades that are hollow along the entire length thereof and which lead into peripheral circular chambers that operate as an engine (THRA) that can be powered by working fluids.

A nested lattice structure for use in a damping system for a turbine blade includes a first lattice structure including: a first outer passage including a hollow interior; a second outer passage including a hollow interior; and an outer node including a hollow interior and forming an intersection of the first outer passage and the second outer passage. The nested lattice structure includes a second lattice structure nested within the hollow interior of the first lattice structure. The second lattice structure includes: a first inner passage; a second inner passage; and an inner node forming an intersection of the first inner passage and the second inner passage. Each of the first inner passage, the second inner passage, and the inner node are nested within the respective first outer passage, the second outer passage, and the outer node.

A turbine engine includes a frame assembly including an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A baffle within the outer cavity includes a plurality of openings for directing cooling airflow into the outer cavity for preventing impingement on a radially inner wall of the outer cavity for maintaining a desired temperature of the cooling air within the outer cavity.

An equipment support including at least one attachment including an output shaft, an input gear wheel, the input gear wheel being both rotated by the motor shaft at a main speed and also connected to the output shaft of the attachment in order to rotate it at a determined output speed, an input shaft, rotated by the input gear wheel at a determined input speed, and a reducer with magnetic gears, arranged between the input shaft and the output shaft, such that the input speed is different from the output speed.

Aspects are directed to a system that includes an outer structure of a thrust reverser, a blocker door, and a plurality of four-bar mechanisms arranged in series with one another that couple the outer structure and the blocker door. Aspects are directed to a system for a thrust reverser of an aircraft that includes a blocker door, a kinematic mechanism configured to actuate the blocker door, and a pressure shelf, where the blocker door is configured to reside below the pressure shelf in proximity to a duct of the thrust reverser, and where at least a portion of the kinematic mechanism is configured to reside above the pressure shelf.