The invention relates to a turbine blade which comprises at least one cavity that is defined by a wall with one or more surface discontinuities which preferably are selected from elevations, depressions and undercuts and preferably change at least one eigenmode of the blade. The blade may suitably be produced by a generative production method such as selective laser melting (SLM).

Described is a blade for a high-speed turbine stage of an aircraft gas turbine, in particular of an aircraft engine, the blade including a radially inner blade root, and an airfoil extending radially outwardly from the blade root. It is provided that the blade be shroudless and that the airfoil have a radially outer end portion that is positionable opposite a rub surface when the blade is in an installed state, and that the airfoil have a radially inner chord length that is at least 1.1 times, preferably at least 1.2 times, in particular at least 1.3 times a radially outer chord length, the inner chord length being measured at the airfoil directly above the blade root, and the outer chord length being measured at the airfoil in the region of or below the end portion.

An airfoil for a gas turbine engine includes a first portion joined to a second portion along an interface such that at least the first portion establishes an airfoil section and the second portion establishes a root section. The airfoil section includes an airfoil body that extends between leading and trailing edges in a chordwise direction, between pressure and suction sides separated in a thickness direction, and from the root section to a tip portion in a spanwise direction. A recessed region extends inwardly from at least one of the pressure and suction sides. The airfoil body includes at least one rib that bounds a respective pocket within a perimeter of the recessed region. The recessed region and the at least one rib are dimensioned to extend across the interface. A cover skin is coupled to the airfoil body along the at least one rib to enclose the recessed region.

A centrifugal air-sending device has blades that each have a vane length in a first region that is greater than a vane length in a second region, and are each formed such that a proportion for which a turbo vane portion accounts is higher in a radial direction than a proportion for which a sirocco vane portion accounts in the first region and the second region. The blades that are located closer to an outer circumference than is a blade inner diameter of inner circumferential ends of the blades at end portions of the blades that are close to a side plate in an axial direction are defined as a blade outer circumferential portion that is formed such that a vane thickness of each of the blades in decreased in the radial direction from an inner circumference toward the outer circumference.

An ceiling fan comprising a motor system. The motor system is mounted around a motor shaft. The motor shaft couples to a downrod for suspending the ceiling fan from a structure. The motor shaft and motor are encased by a motor housing. The motor housing comprises hub arms for mounting a plurality of blade holders. The blade holders coupled to a plurality of blades rotatable about the motor during operation. The downrod comprises a wire disk mounting guy wiring to the downrod. A retention rod is utilized internal of the motor and downrod as a secondary retention method. An electrical connector is internal of the motor shaft and electrically couples to the stator to power the motor.

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 with an upper surface, a lower surface, and a side edge. A performance feature can be included in the body between the upper surface and the side edge, or the lower surface and the side edge to improve efficiency. The performance feature can be tailored to the particular blade edge, shape, or intended rotational direction to increase efficiency.

A blade for room fans comprising an elongated body extending longitudinally along a longitudinal direction of development and provided with a first end mounted, in use, on a central body movable in rotation around an axis of rotation orthogonal to the direction of development for the movement of at least one air flow intended for the airing/ventilation of rooms, and a second end opposite said first end, the elongated body rotating arranged on a plane of rotation orthogonal to the axis of rotation; wherein the elongated body is provided with a cross section the inclination of which with respect to the plane of rotation and/or the conformation of which varies along the direction of development.

A turbomachine rotor blade includes plural blade sections stacked along an axis between a blade root and a blade head defining between the blade root and the blade head the height of the blade, each blade section including a chord and a maximum sweep defined by the maximum length of a segment perpendicular to the chord line and connecting a point of the chord line and a point of a camber line formed of all points located equidistant from the extrados and the intrados in the section, and verifying that the ratio between the maximum sweep and the chord at mid-height of the blade and the same blade head ratio is between 25% and 40% of the ratio between a maximum sweep and a blade root chord.

A rotor assembly for a gas turbine engine includes a rotatable hub that has a main body and an array of annular flanges that extend about an outer periphery of the main body to define an array of annular channels. An array of airfoils are circumferentially distributed about the outer periphery. Each one of the airfoils includes an airfoil section extending from a root section received in the annular channels. Retention pins extend through the root section of a respective one of the airfoils and through the array of annular flanges to mechanically attach each root section to the hub.

An airfoil for a turbine engine, comprising an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction, outlets on the exterior surface, and a cooling air supply conduit within the interior and having a supply passage.