An acoustic device includes: a perforated plate that has a plurality of holes penetrating in a plate thickness direction of the perforated plate and in which a main flow is to flow on a first side of the perforated plate in the plate thickness direction; and a housing that is on a second side of the perforated plate in the plate thickness direction and partitions a space between the housing and the perforated plate, wherein a part of each of the plurality of holes on the first side in the thickness direction is inclined to at least one of the first side and a second side of a flow direction of the main flow.

A propulsion system is provided. The propulsion system defines a radial direction and includes a rotating element; a stationary element; an inlet assembly defining an inlet positioned between the rotating element and the stationary element and positioned inward of the stationary element along the radial direction, the inlet assembly comprising an inlet duct located downstream of the inlet; and a ducted fan comprising a plurality of fan blades positioned at least partially in the inlet duct; wherein the inlet duct divides into a first duct and a second duct separate from the first duct, wherein the first duct is a core duct downstream of the ducted fan, wherein the second duct is a fan duct downstream of the ducted fan, and wherein the second duct includes an exhaust nozzle having a plurality of chevrons disposed at an aft end of the exhaust nozzle to define an exhaust outlet.

A guide vane ring for a turbomachine minimizes a leakage flow that passes through a recess (11) into which a guide vane disk is inserted. It has a guide vane row having a plurality of guide vanes (20), each having a vane airfoil (24) and a vane disk (21), as well as an inner ring (10) having an inner ring surface (12) facing the plurality of guide vanes. Viewed in the direction (R) of a designated primary flow streaming through the turbomachine, the vane disks (21) have a front and a rear surface region (22a, 22b). In a nominal and/or a maximum open position of the guide vanes, the front and/or the rear surface region (22a, 22b) of at least one of the vane disks has an offset (31a, 31b) from the inner ring surface (12) that is radially disposed (relative to a central axis (X) of the inner ring (10)).

A modeling method for a fan assembly includes constructing non-axially symmetric end wall curved surfaces in a cascade channel. Constructing the non-axially symmetric end wall curved surfaces in the cascade channel includes: determining, using a flow path design method for a dual flow path of a blade end area, an initial axially symmetric curve radius and a recessed curve lowest point radius of non-axially symmetric curved surfaces; and constructing the non-axially symmetric end wall curved surfaces in the cascade channel according to the initial axially symmetric curve radius and the recessed curve lowest point radius. The modeling method constructs the non-axially symmetric end wall curved surfaces in the cascade channel using the flow path design method for a dual flow path of a blade end area, to implement the control of flow directions by the non-axially symmetric curved surfaces, thereby reducing end wall loss.

A double rotor for vertical axis turbine includes two single three-vane rotors separated by a horizontal or separation plate, wherein such plate provides two different access areas to the propelling fluid, wherein between each of the three vanes of each of the single rotors it is determined surface continuity attenuated by curves in the fluid flow direction preventing parasitic flows during rotation thereof.

A spindle assembly configured to be assembled in a machining device. A front cover of the spindle assembly includes passages to allow high pressure fluid to flow towards the blades of the turbine and rotate the turbine; openings located at the front end of the front cover may allow low pressure fluid to flow out of the spindle assembly; passages extending from behind the turbine to the front end of the front cover may allow collection of low pressure fluids that flow towards the rear end of the spindle after hitting the blades of the turbine and to direct these fluids towards the front end of the front cover and out of the spindle assembly. The housing of the spindle assembly may include a rear section configured to be assembled onto the machining device.

An engine component includes a body having an internal surface and an external surface, the internal surface at least partially defining an internal cooling circuit. The component further includes a plurality of cooling holes formed in the body and extending between the internal cooling circuit and the external surface of the body. The plurality of cooling holes includes a first cooling hole with a metering portion with a constant cross-sectional area and a cross-sectional shape having a maximum height that is offset relative to a longitudinal centerline of the metering portion; and a diffuser portion extending from the metering portion to the external surface of the body.

The present invention relates to a turbine engine guide (23) vane (25), with a height (H) extending between a vane root (26) and a vane tip (27) along a radial direction (Z), said vane (25) comprising a succession of five bulge portions along a tangential direction (Y) perpendicular to the radial direction (Z), this succession of bulge portions extending over the whole height (H) of the vane (25), and the convexity of the successive bulge portions being alternately in one direction and in the other. The vane (25) has the advantage of having an eigenfrequency for the first striped vibration mode which is different from the urging frequencies of said vane (25), during the operation of the turbine engine.

A fan assembly for a gas turbine engine includes a fan including a plurality of fan blades. Each fan blade extends radially outwardly from a fan hub to a blade tip. The plurality of blade tips define a fan diameter. A nacelle surrounds the fan and defines a fan inlet upstream of the fan, relative to an airflow direction into the fan. The nacelle has a forwardmost edge defining an inlet length from the forwardmost edge to a leading edge of a fan blade of the plurality of fan blades. A ratio of inlet length to fan diameter is between 0.20 and 0.45. A nacelle inner surface defines a nacelle flowpath. The nacelle flowpath has a convex throat portion and a concave diffusion portion between the throat portion and the leading edge of the fan blade at a bottommost portion of the nacelle.

In a gas turbine for aeronautic engines, a stator body delimited by an outer lateral surface is cooled by an air cooling device having a plurality of circumferential tubes for distributing air on the outer lateral surface; each circumferential tube having a plurality of outlets for guiding respective cooling airflows towards the outer lateral surface and into a respective circumferential channel obtained between two groups of circumferential channels adjacent to each other and lapped by the flow of air leaving the circumferential channel.