In a convergent-divergent flap pair for a turbojet engine nozzle of the variable-geometry convergent-divergent type, the convergent flap and the divergent flap include respective cooling-air ducts connected to one another through air passage openings formed in respective contact surfaces of the convergent flap and of the divergent flap arranged facing one another.

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.

An aero-propulsion system includes a drive shaft, a low-pressure compressor, a fan shaft driving a fan, a reduction device that couples the drive shaft and the fan shaft, and an inlet channel which extends between the fan and the low-pressure compressor, the inlet having a predetermined mean radius, a ratio between a mean radius of the inlet channel and the mean radius of the low-pressure compressor, on the one hand, and the reduction ratio of the reduction mechanism, on the other hand, being less than 0.35.

A heat exchanger system for a propulsion system inlet duct includes a heat exchanger assembly that is disposed within an inlet duct assembly. The heat exchanger includes a heat exchanger with a front facing area that is greater than an area of the inlet duct that is transverse to a longitudinal length of the inlet duct.

A last chance screen for a fuel system includes a mesh that includes a first plurality of members extending in a first direction and a second plurality of members extending in a second direction and intersecting the first members. Openings are formed in the mesh between the first plurality of members and the second plurality of members. The first plurality of members and the second plurality of members have an airfoil shaped cross-section.

A circumferential seal assembly suitable for forming a thin film between a rotatable runner and a sealing ring is presented. The assembly includes an annular seal housing, a rotatable runner, an annular seal ring, and a plurality of groove structures. Each groove structure includes a groove and an optional feed groove. The groove includes at least two adjoining steps defined by base walls arranged to decrease depthwise. Two adjoining base walls are disposed about a base shoulder. Each base shoulder locally redirects a longitudinal flow to form an outward radial flow in the direction of the annular seal ring. The base walls are bounded by and intersect a pair of side walls. A side wall includes side shoulders which narrows the groove widthwise and locally redirects the longitudinal flow to form a lateral flow in the direction of the other side wall. Outward and lateral flows separately or in combination enhance stiffness of a thin-film layer between the annular seal ring and the rotatable runner.

A secondary air system (SAS) of an aircraft engine that produces secondary airflow from a source of secondary air includes a hollow strut and one or more SAS feed pipes upstream thereof. The hollow strut extends radially through the main gas path of the engine and defines therein a strut conduit extending between a strut inlet and a strut outlet at opposite ends of the hollow strut. The strut outlet is in fluid flow communication with a buffer cavity for feeding the secondary airflow to the engine core. The SAS feed pipe includes an inlet receiving the secondary airflow from the source of secondary air, and an outlet in fluid flow communication with the strut inlet to feed the secondary airflow into the strut conduit. The SAS feed pipe has a sonic orifice therein, between the inlet and the outlet thereof.

A segmented augmented turbine assembly for generating electricity from a fluid in motion, the assembly comprising a segmented annular ducted channel extending between an inlet receiving the fluid and an outlet, the channel comprising a convergent accelerating the fluid, a segmented turbine-rotor section comprising blades and guide vanes rotating about a central shaft coupled to a generator, and a diffuser section configured to decelerate the fluid, wherein the channel comprises solid inserts attached to an outside face of the turbine-rotor section, the flow stream passing through open flow-through segments positioned between the solid inserts.

A gas turbine engine is provided having a static structure including a flowpath wall. A fluid circuit is extended through the flowpath wall and includes a first inlet opening in fluid communication with a first cavity to receive a first flow of fluid through the fluid circuit. The static structure includes an ejector positioned at the fluid circuit, in which the ejector includes a second inlet opening in fluid communication with a second cavity to receive a second flow of fluid through the ejector and into the fluid circuit.

A nacelle assembly of a gas turbine engine includes an annular structure defining a central axis, and having a radially inward surface and a radially outward surface, the radially inward surface at least partially defining a bypass duct. An aft portion of the radially inward surface at least partially defines an axially extending convergent-divergent exit nozzle. A secondary nozzle flap is radially spaced from the aft portion of the radially inward surface. The secondary nozzle flap and the aft portion of the radially inward surface define a secondary bypass duct therebetween. The secondary nozzle flap is operably connected to the annular structure such that the secondary nozzle flap is selectably movable relative to the aft portion of the radially inward surface, thereby changing a cross-sectional area of a secondary bypass duct exit.