An apparatus is provided for a turbine engine. This turbine engine apparatus includes a turbine engine component that includes a sidewall and a cooling aperture. The cooling aperture includes an inlet, an outlet, a meter section, a diffuser section and a transition section between and fluidly coupled with the meter section and the diffuser section. The cooling aperture extends through the sidewall from the inlet to the outlet. The meter section is at the inlet. The diffuser section is at the outlet. The transition section is configured to accommodate lateral misalignment between the meter section and the diffuser section.

The film cooling structure includes a wall part and a cooling hole inclined such that an outlet is positioned rearward of an inlet. The cooling hole includes a straight-tube part and a diffuser part. The diffuser part includes a flat surface, a curved surface curved rearward and forming, together with the flat surface, a semicircular or semi-elliptical channel cross section larger than that of the straight-tube part, a first section and a second section extending from the first section toward the outlet. In the first section, an area of the channel cross section increases as it approaches the outlet. In the second section, the area of the channel cross section increases as it approaches the outlet at an increase rate smaller than that of the first section or is constant. The diffuser part has a width equal to or twice greater than the depth of the diffuser part.

A gas turbine engine comprises a bypass duct and a heat exchanger assembly, the heat exchanger assembly comprising a heat exchanger and a heat exchanger duct having an inlet region, an inflection region and an outlet region. A direction of a centreline of the heat exchanger duct has a tangential component with respect to a principal rotational axis of the gas turbine engine at one or more of the inlet region, the inflection region and the outlet region. The heat exchanger is disposed within the inflection region and configured to transfer heat generated by the gas turbine engine into the flow of air as it passes through the inflection region.

A locking structure of a compressor impeller, which includes: a rotary shaft; a lock nut arranged on an end of the rotary shaft by means of a threaded connection and provided with waist-shaped holes extending along a circumferential direction thereof; an impeller sleeved on the end of the rotary shaft and located on an inner side of the lock nut, the impeller is provided with threaded holes in communication with the waist-shaped holes of the lock nut; a nose piece located on an outer side of the lock nut and provided with through holes in communication with the waist-shaped holes of the lock nut; and bolts passing through the through holes and the waist-shaped holes in turn into the threaded holes, thereby fixing the nose piece, the lock nut and the impeller together.

A high-temperature component including a plurality of cooling passages through which the cooling medium can flow, a header connected to respective downstream ends of the plurality of cooling passages, and one or more outlet passages for discharging the cooling medium flowing into the header to outside of the header. The one or more outlet passages are less in number than the plurality of cooling passages. Respective minimum flow passage cross-sectional areas of the one or more outlet passages are not less than respective flow passage cross-sectional areas of the plurality of cooling passages in a connection between the header and the cooling passages. A sum of the respective minimum flow passage cross-sectional areas of the one or more outlet passages is less than a sum of the respective flow passage cross-sectional areas of the plurality of cooling passages in the connection between the header and the cooling passages.

A turbofan with a sliding element, rotary blades that can rotate between stowed and deployed positions, and a maneuvering system which moves each blade when the sliding element moves and which includes, for each blade, a rotary main shaft, for each main shaft, a transmission lever rigidly secured to the main shaft, at least two connecting strips articulated to one another, wherein each connecting strip is associated with at least three main shafts, the transmission levers of which are articulated to the connecting strip, and a drive system which rotates the first connecting strip when the sliding element moves. The use of rotary blades on the sliding element and the simplified maneuvering system makes the assembly more lightweight compared to the use of conventional reverser doors.

A turbofan with a nacelle having a slider that is movable between an advanced position and a retracted position to open a window between a duct and the outside, blades, each one being able to move in rotation between a stowed position and a deployed position, and a maneuvering system that moves each blade, a transmission arrangement that rotates the blades one after the other, a drive system that converts the translational movement of the slider into a rotational movement of a first blade and that has a ball screw system, an epicyclic gear train, and an assembly of arms and levers.

Embodiments of the invention are shown in the figures, where a gas turbine engine for an aircraft includes: an engine core including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan including a plurality of fan blades; and a gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan about a rotational axis at a lower rotational speed than the core shaft, wherein the gearbox is an epicyclic gearbox with a plurality of planet gears arranged in first and second sets of planet gears, the planet gears of the first set being positioned displaced relative to the planet gears of the second set in a direction parallel to the rotational axis.

A turbocharger includes a first housing configured to house a turbine impeller, a second housing configured to rotatably support a rotating shaft to which the turbine impeller is fixed, and a variable capacity mechanism configured to surround the turbine impeller and to guide a fluid to the turbine impeller. The variable capacity mechanism has a nozzle ring that faces the second housing. A first pin and a second pin extend between the second housing and the nozzle ring and are attached to one of the second housing and the nozzle ring. The other of the second housing and the nozzle ring is provided with a first guide in which an end portion of the first pin is disposed and a second guide in which an end portion of the second pin is disposed.

A propulsion system is provided including an unducted rotating fan defining a fan axis; and a turbomachine disposed downstream from the unducted rotating fan, wherein the turbomachine defines a working gas flowpath flowing therethrough; wherein the propulsion system defines a third stream flowpath and an inlet passage having an inlet that is offset from the fan axis, wherein the inlet passage is configured to provide an inlet airflow to the working gas flowpath, and wherein the third stream flowpath bypasses at least a portion of the turbomachine.