Abstract: A wind generator system with a plurality of lightweight, surface area adjustable airfoil/sail blades. Each blade is triangular or wedge shape with a narrow inner edge and a wide outer edge. Each blade includes an inner frame connected to a rigid mast that extends radially from a hub assembly. Each blade includes a curved outer skin layer that extends over the inner frame and configured into air foil shape with a large curved leading edge and a thin trailing edge. The outer skin layer is secured along its leading edge and removeably attached along its trailing edge to the inner frame. Coupled to the outer skin layer is a first linear actuator that when activated, causes the outer skin layer to fold or unfold thereby changing the blade's surface area. The internal frame may include a second linear actuator and a telescopic mast over which the blade slides to increase or decrease the sweep area of the blades.

Abstract: Within examples, systems for enhanced performance blades for rotor craft are provided and methods for operation. An example system for a rotary device is provided comprising a rotor blade coupled to a rotor hub. The system also comprises an air channel disposed within the rotor blade, where the air channel is sealed proximate to a distal end of the rotor blade. The system also comprises an inlet positioned at a proximal end of the rotor blade, where the inlet is in fluid communication with the air channel. The system also comprises a plurality of outlets positioned along the rotor blade, where each of the plurality of outlets are in fluid communication with the air channel.

Abstract: A rotor blade spar for use in a rotor blade is provided comprising a housing defining an interior and having an open end. An end cap is affixed to and sealed on the open end to seal the interior from an exterior outside of the housing. The end cap includes a first port and a second port fluidly coupling the interior to the exterior. A port sealing system closes the first and second ports. The first port is connectable to an external device configured to generate a pressure differential between the interior and the exterior sufficient to create an airflow through the first and second ports which removes a liquid disposed in the housing through one of the first and second ports.

Abstract: The impeller is provided with a disk that rotates about an axis line, and a plurality of blades provided at intervals around the circumference of the disk. Defining the blade angle of the tip of each blade as a first blade angle, the tip has a constant-tip-angle area in which the first blade angle is constant from an inlet where fluid flows in toward an outlet side, and an increasing-tip-angle area that is continuous with the outlet side of the constant-tip-angle area and that has a gradually increasing first blade angle towards the outlet.

Abstract: An airfoil for a compressor blade of a gas turbine engine has a chord between a leading edge and a trailing edge and a span between a root and a tip. The airfoil can further include a reduction in local chord from about 75% span to the tip for about a 5% reduction in local solidity. The airfoil can have decreasing sweep angles for the leading edge and the trailing edge from 50% span to the tip and can have decreasing leading and trailing edge dihedral angles from 50% span to the tip.

Abstract: A retention housing for the outer race of a bearing of a gas turbine engine includes a spring finger housing connected to and overlying a bearing housing that is connected to the outer race of the bearing. The spring finger housing includes an arrangement of spring fingers that yields a lightweight housing capable of withstanding very high radial loads combined with very high torsional windup and axial thrust load. A plurality of edge recesses are defined in the bearing housing and a plurality of lug tabs extending radially from the engine's interface shell limit are disposed in the edge recess to limit the deflection and self-arrest the distortion of the retention housing. A gas turbine engine includes the retention housing described above.

Abstract: An airseal for sealing between a rotating component and a stationary component of a turbine engine includes a sealing surface defining a spacing between the airseal and a rotating component of the turbine engine and a mounting flange to secure the airseal to a stationary component of the turbine engine. An airseal body extends between the sealing surface and the mounting flange. The airseal body includes a cavity configured to absorb thermal energy transferred into the airseal from a flowpath of the turbine engine. A gas turbine engine includes a rotating component and a stationary component located radially outboard of the rotating component. An airseal is located therebetween and includes a sealing surface and a mounting flange to secure the airseal to the stationary component. An airseal body extends between the sealing surface and the mounting flange and includes a cavity to absorb thermal energy transferred into the airseal.

Abstract: A partially assembled casing for a turbine including: an assembly of connected casing sections, wherein the assembly does not form a complete casing for the turbine; a gap in the assembly of connected casing sections, wherein the gap corresponds to an absent casing section which is not included in the assembly of connected casing sections, and a frame inserted in the gap and providing structural support to the assembly of connected casing sections.

Abstract: A turbomachine blade comprising a metallic leading edge having a region having varying fracture resistance in a spanwise direction so as to increase energy absorption by the leading edge in the event of the blade being released from a turbomachine and impacting a casing of the turbomachine.

Abstract: Aircraft gas turbine engine spinner includes conical forward spinner section extending aftwardly from spinner tip to a curved aft spinner section circumscribed about centerline axis, a spinner aspect ratio greater than about 1.8, and wherein spinner aspect ratio is an axial distance between spinner tip and spinner end divided by radial distance from axis to spinner end. Aspect ratio may be in a range of about 2.0-2.2 or about 2.2-2.8. Aft spinner section may be substantially tangential to platform leading edges of platforms of fan blades. Aft spinner section may have cambered or an elliptical axially curved cross-section. Spinner axial cross-section may have longer spinner axial distance compared to baseline axial distance of baseline cross-section and spinner aspect ratio greater than baseline aspect ratio of baseline cross-section.

Abstract: Gas turbine engines and related systems involving air-cooled vanes are provided. In this regard, a representative vane for a gas turbine engine includes: an airfoil having a leading edge, a pressure surface, a trailing edge and a suction surface; and a cooling air channel; the suction surface being formed by an exterior surface of a first wall portion and an exterior surface of a second wall portion, the first wall portion spanning a length of the suction surface between the second wall portion and the trailing edge; the cooling air channel being defined, at least in part, by an interior surface of the first wall portion, the first wall portion exhibiting a thickness that is thinner than a thickness exhibited by the second wall portion.

Abstract: The present disclosure generally relates to a rotor assembly, and in particular relates to an improved rotor heat shield which provides an innovative configuration for securing the same to the rotor assembly. The rotor heat shield element is secured to the rotor assembly in correspondence of the groove in which it is inserted. Embodiments of the present disclosure can allow the removal of current fixation features on heat shields and blades. Furthermore, since the heat shield is no longer connected to a blade but directly to the rotor assembly, there is more freedom in selecting the number of heat shield elements to be provided to form the circumferential heat shield.

Abstract: An oil bearing to support a rotor of a turbine, especially of a gas turbine, wherein the rotor extends along a rotor axis coinciding with a bearing axis, has at least one oil bearing pad being lubricated by oil, including an oil sump suitable and located to collect the oil from the bearing pads by forces of gravity, including a drain system of the oil sump to conduct the oil away from the oil sump. The drain system includes at least three drain openings of the oil sump, wherein a first drain opening joining a first drain line is located between 4 o'clock and 5 o'clock according to the bearing axis, wherein a second drain opening joining a second drain line is located between 5:30 and 6:30, wherein a third drain opening joining a third drain line is located between 7 o'clock and 8 o'clock.

Abstract: A variable area turbine arrangement according to an exemplary aspect of the present disclosure includes, among other things, a variable vane assembly and a secondary flow system associated with the variable vane assembly. Flow modulation of a cooling fluid through the secondary flow system is changed simultaneously with actuation of the variable vane assembly.

Abstract: A platform includes a platform body. The platform body has an airfoil support surface, an axially extending base surface opposite the airfoil support surface, and a leading edge. The leading edge includes an upstream extending flange with a raised portion and a trough portion downstream of and radially inward from the raised portion. The raised portion and the trough portion are for holding a vortex of fluid flow. The upstream extending flange includes a converging surface connecting the upstream extending flange to the base surface. The converging surface converges in a direction toward the axially extending base surface and is at an angle relative to the base surface.

Abstract: A splined muff is provided for use with a ram air turbine (RAT). The splined muff includes a body formed of plastic material that acts as an insulator during a lightning strike. The body is formed to define an aperture and includes an interior facing spline for engagement with a complementary exterior facing spline; and an exterior facing spline for engagement with a complementary interior facing spline.

Abstract: An attachment assembly for attaching a center structure to an outer structure at least partially circumscribing the center structure, the attachment assembly having a bushing provided within the center structure or the outer structure, the bushing defining a first through passage, a bushing adapter slidably mounted within the first through passage and defining a second through passage, a threaded passage provided on the other of the center structure or the outer structure and a bolt passing through the first through passage and the second through passage and threaded into the threaded passage.

Abstract: A static component for a gas turbine engine includes an axially extending body comprising a forward end and an aft end disposed axially downstream from the forward end. A rib is formed on at least one of the forward end and the aft end of the axially extending body and extending axially from the axially extending body. A recess is formed in the rib.

Abstract: A turbomachine blade comprising a metallic leading edge having a weakened region extending in a spanwise direction; and a crack initiator for selectively initiating cracking of the metallic leading edge along the weakened region.

Abstract: A turbine housing for a turbocharger is provided. The turbine housing includes an exterior housing and an interior housing as well as a bearing flange. The exterior housing is connected to the bearing flange. The interior housing includes a flange socket on which the bearing flange is positioned. A fastening ring is inserted inside in the bearing flange and connected to the flange socket, with the bearing flange being fixed in the axial direction (AR) by the fastening ring.