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 curved transition can extend between one of the flat top surface or the flat bottom surface, and the side edge. The curved transition can include an elliptical curvature.

The disclosure provides a blade with an airfoil including: a root region at a first radial end; a tip region at a second radial end opposite the first radial end; and a midspan region between the root region and the tip region and at least one endwall connected with the root region or the tip region of the airfoil along the suction side, the pressure side, the trailing edge and the leading edge, wherein the midspan region includes a reduced axial width relative to an axial width of the root region and an axial width of the tip region, and a reduced opening-to-pitch ratio at the midspan region relative to the root and tip regions.

A thrust nozzle, in particular thrust nozzle for a rocket engine, with a convergent wall section, a throat section and a divergent wall section. The divergent wall section has a first region adjacent to the throat section, the wall contour of which region corresponds to a truncated ideal nozzle, and the divergent wall section has a second region facing away from the throat section, which region has a wall contour deviating from the first region.

A structure for disrupting the flow of a fluid comprises and a second lateral wall spaced apart from one another, yet joined, by a floor and a ceiling; and, (b) a vorticor pin extending in a direction parallel to an X-axis, the vorticor pin concurrently rising above and extending away from the floor to a height, in a direction parallel to a Y-axis, the vorticor pin comprising: (i) a front surface extending incompletely between the first lateral wall and the second lateral wall, the front surface extending above the floor and having an arcuate portion that is transverse with respect to a Z-axis, which is perpendicular to the X-axis and the Y-axis, and (ii) a rear surface extending between the first lateral wall and the second lateral wall, the rear surface extending between the front surface and the floor, the rear surface having an inclining section that tapers in height, taken parallel to the Y-axis, in a direction parallel to the Z-axis.

An intake for channeling air flowing past a propeller to an inlet of an aircraft engine that drives the propeller with a drive shaft, the intake including: a static cowling that extends along an axis and that flares outward at an upstream end of the static cowling, and an intake slot that is formed in the static cowling. The intake slot connecting to a passage of the inlet of the aircraft engine, the intake slot including an arched opening that extends less than 360 degrees of a circumference of the static cowling, and the intake slot having a downstream lip with a curved profile that blends into the static cowling.

A diffuser is proposed which is formed as the gap between rotationally-symmetric surfaces which face each other. Moving in the radial direction, the axial extent of the gap generally decreases to a minimum value in a throat portion of the diffuser, and then generally increases again. The distance from the rotational axis of the compressor to the throat may be approximately at least 125% of the radius of the compressor wheel. The inventors have found that a throat at this distance from the rotational axis may lead to higher efficiency at high flow rates, especially for relatively low turbo speeds. This is because the spacing between the compressor wheel and the throat permits diffusion of the gas streams leaving the compressor wheel.

A rotor blade in an embodiment includes: a suction surface side projecting portion projecting from a suction surface on a leading edge side at a blade tip of the blade effective portion; and a pressure surface side projecting portion projecting from a pressure surface on a trailing edge side at the blade tip of the blade effective portion. The suction surface side projecting portion includes: a leading edge side end surface including a contact surface that comes into contact with the pressure surface side projecting portion of the adjacent rotor blade and a non-contact surface that does not come into contact with the pressure surface side projecting portion of the adjacent rotor blade during rotation; a groove portion formed from the non-contact surface to the trailing edge side; and a joining member joined to the groove portion, the joining member being formed of an erosion-resistance material.

An ultrashort nacelle configuration employs a fan cowl having an exit plane and a serrated trailing edge. A variable pitch fan is housed within the fan cowl. The variable pitch fan has a reverse thrust position inducing a reverse flow through the exit plane and into the fan cowl. The serrated trailing edge forms a plurality of vortex generators configured to induce vortices in the reverse flow.

The invention relates to a method for introducing a balancing mark into the compressor wheel of a turbocharger. According to the method, a milling tool is firstly moved in a first direction in order to introduce a recess into the compressor wheel, and the milling tool located in the recess then runs out in a second direction in order to convert the recess into a pear segment-shaped balancing mark. The invention furthermore relates to a turbocharger which comprises a compressor wheel that has one or more pear segment-shaped balancing marks.

An airfoil (10) for a turbine engine includes an array of features (22) positioned in an interior portion (11) of the airfoil (10). Each feature (22) extends from a pressure (14) side to a suction side (16). The array includes multiple radial rows (A-N) of features (22) with the features (22) in each row (A-N) being interspaced radially to define coolant passages (24) therebetween. The radial rows (A-N) are spaced along a forward-to-aft direction toward an airfoil trailing edge (20). The coolant passages (24) of the array are fluidically interconnected to lead a pressurized coolant toward the trailing edge (20) via a serial impingement on to the rows of features (22). The coolant passages (24) are geometrically configured to bias a coolant flow therethrough toward a first side (14) in relation to a second side (16) of the outer wall (12) to effect a greater cooling of the first side (14) than the second side (16).