Abstract: A fan blade for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge, and extends radially between a root portion and a tip portion. A tip pocket is defined by collapsible external walls of the tip portion, and has a pocket opening at a radially outer face of the tip portion.

Abstract: A method of protecting a wind turbine having a set of blades, each blade having a set of loci suitable for placement of a corresponding set of lightning receptors, against lightning strikes, includes applying to each blade a coating that surrounds at least one lightning receptor locus of the set, wherein the coating comprises paint in which has been mixed a conductive powder having a concentration by weight in the coating sufficiently low as to prevent formation of a conductive path through the coating but sufficiently high as to foster ionization of air along the coated exposed surface.

Abstract: The present invention relates to a rotor assembly where associated electric motors are configured to rotate the rotor, control the collective pitch of the rotor/assembly, and/or control the cyclic pitch of the rotor/assembly, by varying the relative rotational angle between two or more of the associated electric motors.

Abstract: A fan blade support assembly for an aircraft is generally disclosed. The fan blade support assembly includes a fan assembly having a plurality of fan blades, a power shaft extending between the fan assembly and an engine of the aircraft, and a housing assembly positioned around the power shaft. The housing assembly includes a convergent housing and a sealing shroud. The convergent housing includes a cap, a base, and a middle portion extending therebetween. The base defines a first diameter, and the cap defines a second diameter less than the first diameter. The sealing shroud is positioned between the convergent housing and the power shaft. A gap is defined between the sealing shroud and the power shaft.

Abstract: A wind turbine (100) comprising a turbine generator (101), rotating mast (102) and a bedplate (103) which is the foundation of the turbine, and three vertical airfoils (104, 105) positioned parallel forming a diffuser, where two of them are side airfoils (104) and the third one, which is positioned in an equal distance between the side airfoils (104), is the central airfoil (105), wherein three vertical airfoils (104, 105) have cross-section diminishing upwardly and the central airfoil (105) comprises in its leeward area a mounted turbine generator (101) having at least one rotor connected to at least one electric generator, wherein said turbine generator (101) is located inside the central airfoil (105), the central airfoil (105) in its cross-section has a shape of biconvex airfoil section preferably drop-shaped.

Abstract: Gearboxes for aircraft gas turbine engines, in particular to arrangements for journal bearings such gearboxes, and to related methods of operating such gearboxes and gas turbine engines. Example embodiments include a gearbox for an aircraft gas turbine engine, the gearbox including: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.

Abstract: A turbo pump vent assembly and method are disclosed. The turbo pump vent assembly comprises: a primary manual actuator operable to deliver an initial volume of air to a turbo pump; and a secondary manual actuator operable to deliver a secondary volume of air to the turbo pump, wherein the secondary volume of air is greater than the initial volume of air. In this way, an uncomplex and reliable vent is provided which can deliver initial volumes of air to slow the turbo pump initially. Thereafter, the secondary volume of air may be delivered to slow the turbo pump more rapidly than is possible just using further initial volumes of air. Having an apparatus which can deliver differing volumes of air enables the turbo pump to be slowed safely and more quickly than is possible by delivering just the same sized volumes of air.

Abstract: A turbine assembly adapted for use in a gas turbine engine is disclosed in this paper. The turbine assembly includes a turbine vane comprising ceramic matrix composite materials configured for use in high temperature environments. The turbine assembly further includes a vane-stage support for holding the turbine vane and other components in place relative to a turbine case.

Abstract: Method of controlling a wind turbine. A data set is obtained that includes a direction of the wind relative to the wind turbine and a pitch angle parameter representing a pitch angle of at least one of the wind turbine blades. Based on the obtained data sets, a statistical representation of the pitch angle parameter as a function of the relative wind direction is determined, which is then used in estimating a wind direction offset corresponding to the relative wind direction where the pitch angle parameter attains a maximum. The relative wind direction of the wind turbine is then adjusted as a function of the wind direction offset.

Abstract: A fan drive gear system for a turbofan engine includes a geared architecture and a gear controller supporting the geared architecture and controlling rotation of the geared architecture relative a static structure.

Abstract: A gas turbine engine for an aircraft having a centrifugal compressor including an impeller with impeller blades extending from a hub, the impeller mounted for rotation about a central longitudinal axis within an outer shroud. A main flow passage wall is located on a shroud side near the impeller exit, the main flow passage wall separating a cavity disposed on the shroud side from the main flow passage. One or more apertures are defined through the main flow passage wall and extending along a respective aperture axis between the cavity and the main flow passage. The apertures have a main flow passage side opening located radially outward from the impeller exit. The aperture axis is disposed at a radial angle relative to the central longitudinal axis.

Abstract: Disclosed herein is a sealing gas supply apparatus. In the sealing gas supply apparatus for supplying sealing gas to a turbomachine of a power generation system, a source comprises at least one low-temperature source for supplying a working fluid to the sealing gas supply apparatus and at least one high-temperature source for supplying a working fluid having a higher temperature than the low-temperature source to the sealing gas supply apparatus, and the working fluids are mixed in the sealing gas supply apparatus to be suitable for a sealing condition as a temperature condition required in a sealing system so as to be supplied to the sealing system of the turbomachine. In accordance with the present disclosure, since separate electric power is not consumed during normal operation by improving a turbine sealing gas source, it is possible to enhance power generation performance by a reduction in power consumption.

Abstract: A centrifugal pump that includes an inlet chamber having a distal end portion and an opposing proximal end portion with a longitudinal axis spanning therebetween. Further included in the centrifugal pump is a plenum chamber having an inlet end portion and an outlet end portion, the inlet end portion is in fluid communication with the inlet chamber proximal end portion, the outlet end portion having an aperture that is about a radial axis that extends radially a distance outward from the longitudinal axis. Wherein operationally for the centrifugal pump the inlet chamber and the inlet and plenum chambers are rotated about the longitudinal axis wherein a fluid is drawn through the distal end portion toward the proximal end portion and ultimately discharged therethrough the aperture.

Abstract: A system and method for improving sealing at a turbine blade tip shroud, while reducing weight associated with the improved sealing is disclosed. The gas turbine blade incorporates a tip shroud having one or more pockets located therein, where the one or more pockets remove weight from the shroud, thus reducing load on the blade attachment generated by additional sealing at the turbine blade shroud. Methods for incorporating the one or more tip shrouds in a new turbine blade or a repaired turbine blade are also disclosed.

Abstract: A molten metal pump includes an impeller, a pump base housing at least partially enclosing the impeller, a shaft connected to the impeller, a motor connected to the shaft, a motor mount plate for supporting the motor; and a post for connecting the motor mount plate to the pump base housing. The molten metal pump can include a connector that connects the post to the motor mount plate. The molten metal pump can include a socket for connecting the shaft to the motor. The shaft can comprise an assembly including an elongated metal rod having a first end and a second end and a metal non-circular drive member attached at the second end of the elongated metal rod.

Abstract: An airfoil includes a leading edge, a trailing edge, a pressure side extending between the leading and the trailing edge, and a suction side that is disposed opposite the pressure side extending between the leading edge and the trailing edge. The airfoil further includes a spar and a structural member. The spar defines the leading edge. The structural member is bonded to the spar.

Abstract: A sealing ring for a turbomachine, in particular a compressor or turbine stage of a gas turbine is provided, the sealing ring having an, in particular at least partially honeycomb-like and/or integral, seal, in particular an abradable coating (13); a profile cross section of the sealing ring, which is in particular at least partially manufactured by a generative manufacturing process, varying in the circumferential direction, in particular at least in some regions continuously and/or non-continuously at one or more circumferential positions, in particular separation points.

Abstract: A control assembly for a stage of variable-pitch vanes for a turbine engine generally includes an actuating ring having an annular body, a vane guidance means for connecting to the cylindrical pivots of the variable pitch vanes, a rotating means for rotating the actuating ring about a casing of the turbine engine, and a centering means for cooperating with the casing to center the actuating ring. The centering means may have at least one skid bearing against the casing. At least one of the skid or the rod may be configured to cooperate by radial sliding with an inner wall of a housing. The skid may be configured to be mobile during operation by sliding between a radially internal position and a radially external position.

Abstract: A supplemental cooling air system for a turbine engine may comprise a compressor having an inlet and an outlet, and an electric motor operatively coupled to the compressor and configured to drive the compressor. The inlet may receive air from at least one of a freestream flow path, a bypass flow path, or an engine bay. The outlet may supply the air to at least a portion of the turbine engine for cooling.

Abstract: A shroud assembly for a gas turbine engine including a plurality of rotor blades. The shroud assembly includes a plurality of tip shrouds, a plurality of flanges, and a plurality of first compressible elements. Each of the plurality of tip shrouds includes an outer band. Further each of the plurality of tip shrouds is coupled to one of the plurality of rotor blades at a tip end. Each of the plurality of flanges extends radially outward from one of the plurality of tip shrouds. Each of the plurality of first compressible elements is coupled to at least one of the plurality of flanges or one of the plurality of tip shrouds and oriented in a first circumferential direction. Further, each of the plurality of first compressible elements is oriented toward an adjacent tip shroud such that the tip shrouds mechanically engage to form a circumferential shroud.