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 engine blade having an aerodynamic surface extending a first direction between a leading edge and a trailing edge and in a second direction, perpendicular to the first direction, between a root of the blade and a tip of the blade, the aerodynamic surface being made of a fiber-reinforced organic matrix composite material, and a metallic structural reinforcement bonded by an adhesive joint to the leading edge whose shape it follows and which has over its entire height a substantially V-shaped section with a base extended by two lateral flanks having a thinned profile at free ends directed toward the trailing edge, the adhesive joint being locally supplemented below the free ends of the lateral flanks by an elastomeric polymer introduced in the form of solid particles into the adhesive joint and adhered to the aerodynamic surface and/or the free ends of the lateral flanks during a polymerization phase.

An airfoil arrangement for a gas turbine engine may include a support device using a shape memory alloy to support and control the airfoil. The support device may be formed as part of a fan blade. The arrangement may be configured to reduce overall weight and dimensions of the gas turbine engine.

The impeller of a rotating machine according to at least one embodiment of the present discloser is provided with: a disc; a cover disposed on an opposite side of a radial passage from the disc in an axial direction; and a blade disposed between the disc and the cover. In a dimensionless position along a camber line of the blade when the position of a leading edge of the blade is defined as 0 and the position of a trailing edge of the blade is defined as 1, a position where an angle difference between a first blade angle at a disc-side end portion of the blade and a second blade angle at a cover-side end portion of the blade is maximum is in a range of 0.5 or more and 1 or less. The first blade angle is −10 degrees or more and 0 degrees or less at the position where the angle difference is maximum.

The present application discloses an impeller for a centrifugal fan and a centrifugal fan. The impeller comprises a support member and several vanes. The support member has an inner wall that defines a hollow portion. The several vanes are arranged inside the hollow portion, each of the several vanes is connected with the inner wall and extends along the axial direction of the support member, and the several vanes are arranged along the circumferential direction of the support member. Each of the several vanes is bent and comprises a front edge, a tail edge, a convex suction surface, and a concave pressure surface, the suction surface and the pressure surface are arranged to oppose each other, and the front edge and the tail edge are arranged to oppose each other, wherein the tail edge is connected with the inner wall of the support member, and wherein several protrusions are provided on the suction surface, and the several protrusions are arranged to be close to the front edge. The protrusions can regulate the flow of a fluid immediately when the fluid contacts the vanes. During the flow regulation process, a large vortex in the fluid can be divided into several small vortices. Such small vortices have smaller friction resistance, and the kinetic energy dissipated from the motion of the small vortices themselves can be partially cancelled out, thereby reducing the noise of the impeller and improving the performance of the centrifugal fan.

A turbine impeller includes: a hub portion coupled to an end of a rotational shaft; a plurality of main blades disposed at intervals on a peripheral surface of the hub portion; and a short blade disposed between two adjacent main blades among the plurality of main blades. An inter-blade flow channel is formed between the two adjacent main blades so that a fluid flows through the inter-blade flow channel from an outer side toward an inner side of the turbine impeller in a radial direction. In a meridional plane, a hub-side end of a leading edge of the short blade is disposed on an inner side, in the radial direction, of a hub-side end of a leading edge of the main blade.

A coupon for replacing a cutout in a hot gas path component of a turbomachine is provided. The coupon includes a body having an outer surface; a chamber within the body for receiving a flow of a coolant; and a passage extending from the chamber to the outer surface of the body. The passage includes an internal portion within a wall of the body having a first perpendicular, cross-sectional area and an exit portion at the outer surface of the body having a second perpendicular, cross-sectional area that is greater than the first perpendicular, cross-sectional area.

A method for manufacturing a blade in composite material having an added metal leading edge for gas turbine aeroengine, includes producing a blade body in composite material including in longitudinal direction, a blade root part, a shank part and an airfoil body part; manufacturing, via additive manufacturing, a leading edge extending in longitudinal direction between a lower end present at the shank part in composite material and an upper end present at the tip; bonding the manufactured leading edge onto the foremost edge portion of the airfoil body of the blade body in composite material.

An axial-flow fan includes a hub that is to be rotated and defines a rotation axis, and a vane provided on a circumference of the hub. The vane includes a leading edge, a trailing edge, an outer circumferential edge, and an inner circumferential edge. The vane is shaped such that a first line chart in a first diagram includes a downward convex portion that is convex further downward than a first virtual line chart, the first virtual line chart being a linear line connecting a point representing a size of an outlet angle formed at a point of the trailing edge that is at the inner circumferential edge and a point representing a size of the outlet angle formed at a point of the trailing edge that is at the outer circumferential edge.

A fan blade (1) has a front inflow edge (2) and a rear outflow edge (3). The fan blade (1) has an at least partially wavy inflow edge (4). The wavy inflow edge (4) forms a wave (W) with a specific three-dimensional waveform.