Abstract: Aerodynamic element having a cross section in an airflow direction with a suction side surface, a pressure side surface, and a trailing edge extending between the suction side surface and the pressure side surface. The aerodynamic element further comprises an extension body attached to the trailing edge near the suction side surface of the aerodynamic element. A top surface of the extension body is flush with the suction side surface. The aerodynamic element (10) is e.g. applied in a rotor blade for a wind turbine.

Abstract: A method for optimizing power production of a wind turbine includes determining at least one operational constraint for the wind turbine. The method also includes operating the wind turbine with at least one operational constraint being activated. Further, the method includes varying a tip speed ratio for the wind turbine while the at least one operational constraint is activated so as to maximize a power coefficient of the wind turbine.

Abstract: A method and system for operating a gas turbine engine coupled to an aircraft propeller are described herein. The method comprises detecting a command for unfeathering the propeller, inhibiting shaft shear detection logic in response to detecting the command for unfeathering the propeller, detecting completion of the unfeathering of the propeller, and enabling the shaft shear detection logic in response to detecting the completion of the propeller unfeathering.

Abstract: A tie shaft assembly for a gas turbine engine includes a compressor tie shaft that has an upstream end and a downstream end. The downstream end includes a radially outer threaded surface and a radially inner threaded surface. A turbine tie shaft has an upstream end with a radially outer threaded surface in engagement with the radially inner threaded surface on the compressor tie shaft.

Abstract: A two-wheel air cycle machine includes a tie rod defining an axis, a turbine mounted on the tie rod, and a compressor mounted on the tie rod and having a rotor portion and a disk portion with at least one aperture. The air cycle machine further includes a compressor inlet fluidly connecting the compressor and an inlet air source, at least one thrust bearing disposed between the turbine and the compressor, and a compressor end shaft coaxial with the tie rod and abutting the compressor disk portion. The compressor end shaft includes a radially-extending seal disk portion and an axially-extending shaft portion having at least one shaft aperture. The at least one disk aperture and the at least one shaft aperture are fluidly connected by a compressor disk cavity defined by a gap between the tie rod and the compressor disk portion. The at least one disk aperture, the compressor disk cavity, and the at least one shaft aperture at least partially define a compressor inlet flow path.

Abstract: A system for delivering a flow stream of a gas to a compressor. A shroud extends from an inlet to the compressor and defines a main inlet passage configured to direct the flow stream from the inlet to the compressor. A communication plenum is separated from the main inlet passage. A port system includes first and second port subsystems that each provide an opening between the main inlet passage and the communication plenum. The first port subsystem is disposed further from the compressor than the second port subsystem. The port system is configured so that a portion of the gas enters or exits the compressor through the second port subsystem, depending on operating conditions of the compressor.

Abstract: A synchronizing ring assembly includes a synchronizing ring portion that has a first and a second distal end, the first and the second distal end each form an integrated surge bumper.

Abstract: A seal assembly includes a first and second seats. The first seat includes an axial portion extending circumferentially around a center axis and extending axially from a first end to a second end. A radial portion extends circumferentially around the axial portion and extends radially from the axial portion between the first end and the second end. A cavity is formed in the radial portion and extends circumferentially around the axial portion. A second seat includes a radial segment extending circumferentially around the center axis and extending radially from an inner surface to an outer surface of the radial segment. An axial segment extends circumferentially around the first end of the first seat, and extends axially from the radially segment to a distal end. The axial segment includes a tapered outer surface that tapers radially inward toward the distal end. The distal end is received in the cavity.

Abstract: An aerofoil component (10) defining an in use leading edge (16) and a trailing edge (18), the leading edge (16) comprising at least one serration (22) defining a sawtooth profile projecting in a generally upstream direction, each serration (22) comprising a plurality of rectangular-wave projections (26) extending in an upstream chordwise direction from the sawtooth profile.

Abstract: A radial fan that includes a fan wheel, which can be rotated about an axis and which comprises a base plate and airfoils protruding from the base plate, wherein the airfoils each comprise an upstream edge in a first spacing (r1) from the axis and a downstream edge in a second spacing (r2) from the axis, and an end wall, which together with the base plate, delimits a flow channel in which the airfoils engage. The cross-sectional area (A) of the flow channel between the upstream edge and the downstream edge passes through a maximum in a third spacing (r3) from the axis. The difference between a fourth spacing (r4) and a fifth spacing (r5), at which the cross-sectional area (A) in each case assumes nearest adjacent minima to the maximum, is at least half of the difference (r2?r1) between the first and the second spacing.

Abstract: A hydrodynamic heater pump may include a housing and a stator fixed relative to the housing. A rotor may be coaxially aligned with and positioned adjacent the stator. The rotor and the stator define an interior region of a hydrodynamic chamber operable for heating a fluid present within the interior region of the hydrodynamic chamber. The rotor may be attached to a drive shaft for concurrent rotation therewith. The rotor may be moved axially along an axis of rotation of the drive shaft between a pumping mode position and a heating mode position. The rotor may be located a first distance from the stator when arranged in the heating mode position and a second distance from the stator when arranged in the pumping mode position. The second distance may be greater than the first distance.

Abstract: A nosecone assembly having an axially extending centerline is provided. The assembly includes a nosecone body and at least one access panel. The nosecone body has at least one wall that defines an interior cavity. The wall has an interior surface contiguous with the interior cavity, and at least one window aperture extending through the wall. The access panel has first and second face surfaces. The access panel is attached to the wall interior surface within an attachment region that includes first and second attachment region portions partially contiguous with one another. The first and second attachment region portions define an interior unattached region, and the interior unattached region is aligned with the window aperture.

Abstract: A turbine (1) for a conduit comprising a turbine unit (13) including a rotor (3), characterized in that the turbine (1) comprises a speed limiting device for said turbine unit (13), which device comprises at least one flexible element (4) connected to the turbine unit (13), so as to limit the flow rate of the fluid passing through the rotor (3) in order to limit the rotational speed of the rotor (3) of the turbine unit (13).

Abstract: A turbine is provided which effectively converts the kinetic energy of the wind, after its (wind) accelerating, to electrical power. The multi-stage wind turbine, which allows multiple accelerate directed air flow (wind), even of most minimal speed, up to strong wind and convert it's energy into electrical power, is proposed. It is achieved due to modularity of installation, where the wind is accelerated within each module due to the processes of capturing the initial wind flow, injection-ejection and aerodynamic Coanda effect as well, by virtual necks and conical confusors nested one into another. The system of truncated cones and virtual necks with optimum aerodynamic sizes provides the capture of the airflow not only perpendicular to the base of these cones, but also from lateral sides of these cones.

Abstract: A seal assembly extends along an axis and seals an axial (and/or radial) gap between a first component and a second component. The seal assembly includes a seal carrier and a seal element. The seal element extends axially (and/or radially) between a first portion and a second portion. The first portion of the seal element is slidingly arranged within a slot in an axial end (or a radial side) of the seal carrier. The second portion of the seal element is configured to axially (and/or radially) engage the second component.

Abstract: The present invention relates to a guide vane ring element for a turbomachine, such as a gas turbine, with at least one drilled hole for the at least partial uptake of a flange of a rotatable guide vane, wherein an edge of the drilled hole on the vane element side is designed convexly along the edge in a first circumferential portion and, in particular, has a radius.

Abstract: A vane comprises an airfoil extending from a radially outer platform to a radially inner platform. A pair of legs extend radially inwardly from the radially inner platform, and an air flow passage extends through the radially outer platform, through the airfoil, and into a chamber defined between the pair of legs. One of the pair of legs includes a plurality of injector holes, configured to allow air from the radially outer platform to pass outwardly of the holes. A gas turbine engine is also disclosed.

Abstract: The invention relates to an intermediate housing hub (2) comprising a discharge stream conduit (18) having a given length (L1), and discharge fins (22) extending in the discharge stream conduit (18) and having a given chord length (L2), the chord length (L2) of at least one of the discharge fins (22) being at least equal to 50% of the length of conduit (L1).

Abstract: A blade member includes a leading edge, a trailing edge, and a blade body extending therebetween. The blade member also includes a dovetail, a transition region, and a transition relief. The dovetail includes a dovetail chord line extending between an axially forward face of the dovetail and an axially aft face of the dovetail. The dovetail chord line has a dovetail chord length. The transition region is formed between the blade body and the dovetail. The blade body and the transition region form a blade body transition chord line at the interface of the blade body and the transition region which has a blade body transition chord length. The transition relief includes a geometric relief in at least one of a forward and an aft end of the transition region and the dovetail. The dovetail chord length is less than the blade body transition chord length.

Abstract: An impeller locking device for a wind generator is provided. The impeller locking device includes a locking hole formed on an impeller connecting disc, and a locking pin configured to fit into the locking hole. The locking pin is connected with a base of the wind generator; and when the locking pin is locked in the locking hole, a radial clearance is provided between the locking pin and the locking hole. When the axes of the locking pins and the locking holes are deviated radially, the locking pins can also be inserted into the locking holes, so that radial constraints of the locking pins and the locking holes are eliminated. A wind generator adopting the impeller locking device is further provided.