Abstract: A fan assembly includes a fan and a fan drive. The fan includes a fan hub located at a fan central axis, and a plurality of fan blades extending outwardly from the fan hub. The fan hub has a fan hub opening at the fan central axis. The fan hub opening is at least partially defined by a plurality of nodes extending radially inwardly toward the fan central axis from the fan hub. The fan drive is installed in the fan hub opening via an interference fit between the plurality of nodes and an outer surface of the fan drive, thus centering the fan drive in the fan hub opening.

Abstract: An airfoil assembly includes an airfoil body extending from a root to a tip defining a longitudinal axis therebetween. The airfoil body includes a leading edge between the root and the tip. A sheath is direct deposited on the airfoil body. The sheath includes at least one metallic material layer conforming to a surface of the airfoil body. In accordance with another aspect, a method for assembling an airfoil assembly includes directly depositing a plurality of material layers on an airfoil body to form a sheath. In accordance with some embodiments, the method includes partially curing the airfoil body.

Abstract: A turbine blade has a first end, and an opposing second end. A base includes a dovetail for complementing a corresponding dovetail slot in a rotor. The dovetail has a body and a plurality of projections extend from the body in opposing directions. A tapered groove extends through the body from the first end to the second end, and has a tapered profile such that a first depth of the tapered groove near the first end is greater than a second depth of the tapered groove near the second end. The tapered profile gradually transitions from the first depth to the second depth. The tapered groove is open at a bottom surface of the body and is sized to engage a shim. The tapered groove includes a flat section near the first end or the second end, and the flat section has a constant depth.

Abstract: The invention relates to a fan wheel having blades (11) which are distributed over the circumference and are connected to one another in the circumferential direction via at least one ring. The fan wheel consists of at least three integrally formed segments (I to VII). Said segments comprise at least one respective ring portion (1) of at least one ring as well as either a blade (II) or at least a portion of the blades. The segments (I to VII) are joined together to form the fan wheel. The ring portions (1) lie against each other with edges (4, 5) which form the joining areas (15, 16) that are disposed transversely with respect to the circumferential direction of the fan wheel. At least one edge (4) of the ring portion (1) of each segment (I to VII) is provided with at least one projecting form-fitting part (18), and at least one edge (4, 5) of the ring portion (1) of each segment (I to VII) is provided with at least one recess (17) which is at least approximately complementary to the form-fitting part (18).

Abstract: A tap is connected to a location upstream of a downstream most location in a compressor to a heat exchanger. Downstream of the heat exchanger is a shut off valve and a cooling compressor. The cooling compressor is connected to a chamber provided with a check valve configured to selectively allow flow directly from a downstream location in the compressor. There is a system for stopping operation of the cooling compressor, and a control for closing the shut off valve. The cooling compressor is configured to compress air to a greater pressure than the higher pressure, such that the check valve is configured to maintain a closed position, but when said cooling compressor is not providing compressed air, the at least one check valve is configured to allow said higher pressure flow into the chamber. A method is also disclosed.

Abstract: A heat shield vane support may have a structure including at least one of a cylindrical and a frustoconical portion with an outboard diameter and an inboard diameter extending about an axis and extending axially between a forward face and an aft face and may comprise a flange extending circumferentially about the aft face radially inward from the inboard diameter, a plurality of anti-rotation features distributed circumferentially about the inboard diameter extending radially inward from the inboard diameter and extending axially with respect to the cylindrical structure between a forward edge and an aft edge defining a length L, and a plurality of teeth distributed circumferentially about the forward face and extending axially from the forward face.

Abstract: A stiffness controlled abradable seal system for a gas turbine engine includes a cantilevered arm that supports one of a rotating seal surface and a static seal surface, a stiffness of the cantilevered arm controlled to achieve a desired operational temperature at a seal interface, and an optimally matched abradeable seal material with required thermo-physical and friction properties to enable desired wear mechanisms and maximized sealing and durability.

Abstract: A gas turbine engine includes a rotatable component and a non-rotatable component. A seal is carried on one of the rotatable component or the non-rotatable component to provide sealing there between. The seal includes a geopolymer seal element.

Abstract: A propeller component, for example a propeller blade airfoil, includes an external surface exposed in use to an oncoming airstream (A), and a protective polymeric film applied over substantially the entire exposed external surface of the component.

Abstract: An impeller includes: a main body portion which is increased in diameter from one side to another side in a rotation axis direction; a thinned portion, which is formed in a back surface of the main body portion so as to be oriented toward the another side in the rotation axis direction, and is recessed toward the one side in the rotation axis direction; a plurality of full blades which are formed on an outer circumferential surface of the main body portion so as to be oriented toward the one side in the rotation axis direction; and a plurality of splitter blades, which are formed on the outer circumferential surface, and have end portions being located on the one side in the rotation axis direction and being positioned on the another side in the rotation axis direction with respect to the full blades.

Abstract: An interlocking shroud assembly for a turbine engine includes at least two shroud elements, each having confronting radial ends that define a split interface with axial fore, aft, and circumferential portions.

Abstract: A yaw assembly for a wind turbine may include a bushing configured for securement within a yaw cylinder containing a yaw piston and a yaw pad having a first side configured for engagement with a slew ring of the wind turbine and a second side configured for engagement with the yaw piston, a thrust stem engaged with the bushing and configured to apply force to the yaw pad against the slew ring, the thrust stem biased away from the yaw pad by one or more springs residing within the yaw piston, and an anti-rotation collar disposed at an interface between the thrust stem and the yaw piston, the anti-rotation collar including a flange extending from a bottom-center portion thereof, the flange disposed between the one or more springs and a bottom end of the yaw piston.

Abstract: A flow mixing lobe for an exhaust diffuser includes a first flange member having a first leading end, a first trailing end, and an intermediate portion extending therebetween. A second flange member includes a second leading end, a second trailing end, and an intermediate section extending therebetween. A first leg portion includes a first end extending from the first flange member, and a second end. A second leg portion has a first end portion extending from the second flange member, and a second end portion. A wing member is arranged between the first and second leg portions at respective ones of the second end and second end portions. The wing member includes a flow conditioning surface having a non-linear profile extending between the second end and the second end portion.

Abstract: A method for inspecting a rotor blade unit of a gas turbine, the rotor blade unit including a radially outwardly disposed outer shroud connected by a material-to-material bond to a radially inwardly adjoining rotor blade. The method includes: providing a rotor blade unit; processing the outer shroud at its axially forward or axially aft side, the side selected to be processed being the one that has a greater distance from the adjacent axial leading edge or axial trailing edge of the rotor blade, a contact surface being formed by processing the selected side; providing the rotor blade unit having the contact surface in a measuring device, in particular a measuring device for determining the torsion or twist of the rotor blade unit about an axis.

Abstract: An exemplary rotorcraft includes a power train with an engine coupled to a gearbox, a main rotor blade having a mast coupled to the power train, a control input linkage in communication between a pilot input device and the main rotor blade configured to communicate a control input force from the pilot input device to the main rotor blade, and a counterweight system in connection with the control input linkage and the power train to apply a centrifugal force to the control input linkage.

Abstract: An axial fan includes a motor, an impeller, and a housing including a tubular air channel wall portion. The impeller includes a tubular impeller hub, and arranged in a circumferential direction on the impeller hub. Each blade includes a first portion where all of an inner circumferential developed blade, an outer circumferential developed blade, and an intermediate circumferential developed blade superimposed on each other overlap. The inner circumferential developed blade is a junction of the blade with the outer surface of the impeller hub. The outer circumferential developed blade is a radially outermost portion. The intermediate circumferential developed blade is a radially intermediate portion of the blade between the junction and the radially outermost portion. The radially outermost portion is at the shortest radial distance from the air channel wall portion in at least a portion of the first portion.

Abstract: A weight system for a rotor blade includes a weight box open in an outboard direction, a weight guide rod connected to the weight box, the weight guide rod extending in a spanwise direction through an interior of the weight box, and a span balance weight disposed within the weight box, the span balance weight being captured between the weight guide rod and the weight box.

Abstract: The present disclosure discloses an omnidirectional oscillating fan with a clamp, including: a base, a mounting part being disposed on a mounting surface of the base, a main fan unit, disposed on a side of a support surface of the base, and an oscillating main control assembly, disposed between the main fan unit and the base. A cross section, perpendicular to an extending direction, of the mounting part has a circular shape. The main fan unit has a columnar shape. The oscillating main control assembly includes: a first rotational assembly, partially disposed in the mounting part, and a second rotational assembly, having one end rotatably assembled to the main fan unit and the other end fixedly assembled to a rotating end of the first rotational assembly, and being capable of rotating synchronously with the first rotational assembly.

Abstract: An afterbody for a rotor blade of a rotorcraft is unitarily formed of a single material of construction. The afterbody includes an upper surface disposed from a lower surface, a concave leading edge connected to the upper surface and the lower surface, and a trailing edge formed at an intersection of the upper surface with the lower surface.

Abstract: A propulsor hub is provided and includes a casing including an inner annular part and blade-connection parts extending outwardly from the inner annular part, a liner having inner and outer opposed radial ends, the liner being disposed about a corresponding one of the blade-connection parts with the inner radial end thereof at a distance from the inner annular part and a weighted element securely disposed about the corresponding one of the blade-connection parts to abut the outer radial end of the liner.