An erosion strip to protect a leading edge surface is provided including an outer layer comprising a wear-resistant material. An elastomer is affixed to an interior surface of the outer layer. An adhesive layer is shaped to adhere the leading edge surface to the elastomer such that the elastomer and adhesive layers are between the outer layer and the leading edge surface. The elastomer is configured to at least partially isolate strain at the outer layer from strain at the adhesive layer and the leading edge surface.

Aspects of the disclosure are directed to milling a nose of a first shield of a blade to leave at least one strip of the first shield coupled to a blade body, subsequent to the milling, applying a cryogenic technique to the blade to weaken a bond between the first shield and the blade body, and subsequent to the applying of the cryogenic technique, removing the at least one strip of the first shield from the blade body.

A core duct assembly for a gas turbine engine includes a core duct including an outer and an inner wall, the outer wall having an interior surface; a gas flow path member extending across the gas flow path at least partly between the inner and outer walls, the rotor blade having a radial span extending from a blade platform to a blade tip, wherein an upstream wall axis is defined as an axis tangential to a point on a first portion of the interior surface of the outer wall of the core duct extending downstream from the gas flow path member, the upstream wall axis lying in a longitudinal plane of the gas turbine engine containing the rotational axis of the engine, and wherein the upstream wall axis intersects the rotor blade at a point spaced radially inward from the blade tip of the rotor blade.

A ceiling mounted fan or ceiling fan includes a body defining an interior passage having an inlet and an outlet provided on the body. The inlet, outlet, and interior passage can be annular. An impeller mounted is mounted within the interior passage and driven by a motor mounted within the body to draw a volume of air through the interior passage from the inlet to the outlet. The impeller blades include a set of extensions extending from the tip.

A blade for an aircraft gas turbine engine includes, in a longitudinal direction, a blade root, a shank and an aerofoil body, the aerofoil body extending in the longitudinal direction between the shank and a blade tip and in a transverse direction between a leading edge made of metal material and a trailing edge. The blade includes a blade core made of composite material having a three-dimensional woven fibrous reinforcement forming the blade root, the shank and a part of the aerofoil body. The blade also includes a skin made of composite material having a two-dimensional woven fibrous reinforcement surrounding the aerofoil body part of the blade core, the skin being interposed between the leading edge made of metal material and a front edge of the aerofoil body part of the blade core to define a thinned leading edge portion, the skin including one or more two-dimensional woven plies.

An airfoil having an overlapping herringbone filmhole pattern is disclosed. For instance, the airfoil may have filmholes arranged in filmrows, each filmrow divided into groups of filmholes. A first group may be oriented to direct cooling air generally radially outward over a surface of the airfoil and a second group may be oriented to direct cooling air generally radially inward over a surface of the airfoil. Between the first group and the second group of filmholes in each filmrow, a transition region exists. A transition region filmrow group may be disposed within the transition region and may be co-linear with or staggered relative to the first group and/or the second group. In this manner, the transition region filmrow group enhances the effectiveness of the cooling proximate to the transition region.

A balancing weight for a rotor blade of a turbine stage of a gas turbine, in particular of an aircraft gas turbine; including a first bent fastening portion that is couplable to an axial leading edge of a shroud of the rotor blade, a second fastening portion that is couplable to an axial trailing edge of the shroud, and a middle portion that joins the first fastening portion and the second fastening portion; the second fastening portion assumes a first position relative to the first fastening portion prior to a mounting of the balancing weight on the rotor blade, and a second position relative to the first fastening portion subsequently to the mounting of the balancing weight on the rotor blade; in the second relative position, the middle portion or/and the second fastening portion being deformed, in particular plastically deformed.

An HVAC delivery system to supply air from an HVAC system in proximity to a fan blade. A fan blade for use in a high volume, low-speed fan, wherein the fan blade includes a body portion, a leading edge portion and a trailing portion. The leading edge portion of the fan blade includes a series of steps extending along the length of the leading edge. The fan distributes airflow from the HVAC delivery system.

A construction machine includes a centrifugal fan, and a bell mouth arranged on the suction side of the centrifugal fan. The centrifugal fan has a rotatable hub, an annular shroud arranged so as to face the hub and having a suction port, and multiple blades provided between the hub and the shroud. An outlet of the bell mouth is arranged on the radially inner side of the suction port of the shroud. Each blade is formed such that: a leading edge has a convex shape protruding toward a suction surface relative to a line segment linking a connection of the leading edge with the hub and a connection of the leading edge with the shroud; and a vertex of the convex shape of the leading edge is positioned on a radially inner side of a wall surface of the outlet of the bell mouth when the suction side of the centrifugal fan is seen in an axis direction.

A gas turbine engine blade includes a blade portion having a leading edge and a trailing edge. A first surface connects the leading edge to the trailing edge and a second surface connects the leading edge to the trailing edge. A tip section is located at a first end of the blade portion and includes a pocket protruding into the tip section from an outermost end of the tip section. The pocket has a first side wall adjacent the first surface and a second side wall adjacent the second surface. At least one of the first side wall and the second side wall have a curve distinct from a curve of the corresponding adjacent surface.