The invention relates to a fan blade (1) comprising: —an aerofoil (8) made of a composite material comprising a fibrous reinforcement densified by a polymer matrix, a leading edge (4) and a trailing edge (5), and —a structural shield (10) fitted and attached to the leading edge (4) or the training edge (5), and —at least one stiffener (20) formed integrally and in one piece with the structural shield (10), said stiffener (20) extending in a cavity (15) formed between the shield (10) and the leading edge (4) or the trailing edge (5) so as to increase a stiffness of the blade (1).

A hot gas path component assembly includes a first component portion that includes a first set of interlocking features and a second component portion that includes a second set of interlocking features mechanically coupled to the first set of interlocking features. A fill material is disposed at an interface between at least one surface of the first set of interlocking features and at least one surface of the second set of interlocking features. The fill material is disposed during a joining process. The second component portion is joined to the first component portion via both the fill material and the first and second sets of interlocking features.

A ceiling fan or similar air-moving device can include a motor for rotating one or more blades to drive a volume of air about a space. The blade can include a body having an outer surface with a flat top surface and a flat bottom surface, and a side edge. A chamfered transition can extend between one of the flat top surface or the flat bottom surface, and the side edge. The chamfered transition can include multiple chamfered edges.

A turbomachine includes a rotor and a stator, the stator having a plurality of profiled structures, each profiled structure being elongated in a direction of elongation in which the profiled structure has a length exposed to an airflow, and having a leading edge and/or a trailing edge, at least one of which is profiled and has, in said direction of elongation, serrations defined by a succession of peaks and troughs and having a geometric pattern transformed, over at least a part of said length exposed to the airflow, by successive scaling, via multiplicative factors, in the direction of elongation and/or transverse to the direction of elongation. The geometric pattern, as defined with reference to a radial distribution of the integral scale of the turbulence, evolves in a non-periodic manner.

A blade of a turbomachine turbine, including a platform and a vane, including a cooling area extending along the trailing edge, with three distinct types of orifices, wherein the blade includes, at the root of the blade, a first type of orifices formed in the thickness of the trailing edge fillet, at the top of the blade, a third type of orifice formed in the thickness of at least one of the lower surface and upper surface walls, and in the middle of the blade, a second type of orifice formed in the thickness of at least one of the lower surface and upper surface walls. The lower surface wall, the upper surface wall and the trailing edge fillet define a dihedral with a radially changing radius and spacing.

An impeller includes: a disk-shaped hub centered on an axis; and a plurality of blades arranged in a circumferential direction and protruding from a surface of the hub facing one side in a direction of the axis. In a cross-sectional view including a blade height direction which is a direction away from the hub toward a tip of each blade, the blade has a recessed surface curved convexly toward a rear side in a rotational direction. In the cross-sectional view, when a distance between an imaginary line connecting a tip-side edge and a hub-side edge of the blade and a midspan of the blade along a direction perpendicular to the imaginary line is defined as a recess amount, the blade has a portion where the recess amount increases from a leading edge side to a trailing edge side.

A centrifugal or diagonal impeller has impeller blades (4) that are curved in the circumferential direction about an axis of rotation and are formed from a single-layer sheet metal. Each blade (4) has a suction side (11) and a pressure side (12) as well as a blade leading edge (5) and a blade trailing edge (6). At least the blade leading edge (5) of the impeller blades (4) adjacent to their suction side (11) have a geometric edge modification in the form of a rounding (7) over a predetermined partial length of a blade thickness (SD) of the impeller blades (4).

A turbine blade has an attachment root and an airfoil. A cooling passageway system has a plurality of trunks extending from respective inlets along the root inner diameter end from a leading trunk near a first axial end to a trailing trunk near a second axial end; and a plurality of outlets along the airfoil including trailing edge outlets fed by the trailing trunk. Viewed normal to a root end-to-end centerplane: the trailing trunk has a turn passing forward and then rearward; an outside of the turn protrudes forward; and the outside of the turn has a tighter curvature than an inside of the turn.

A curved contour of the lateral surface of a blade arrangement includes in at least one meridian section on mutually opposite sides of a blade airfoil an intersection point that is closer to the blade airfoil front edge, and an intersection point that is closer to the blade airfoil rear edge, and a best-fit line of least square distances from the curved contour. The curved contour includes first and/or the second contour section which meet specified conditions.

The invention relates to a movable turbomachine blade comprising at least one cooling circuit comprising at least one cavity extending radially between the root and the tip, at least one air intake opening at a radial end of the cavity, a plurality of first discharge slots arranged to open out along the trailing edge between the root and the tip, and a plurality of second discharge slots separate from the first discharge slots and arranged along the trailing edge between the root and the tip, the second discharge slots being offset axially upstream relative to the first discharge slots and each of the first discharge slots being radially offset relative to each of the second discharge slots, with no overlap between the first and second discharge slots.