Abstract: An airfoil having an overlapping herringbone filmhole pattern is disclosed. For instance, the airfoil may have filmholes arranged in filmrows, each filmrow divided into groups of filmholes. A first group may be oriented to direct cooling air generally radially outward over a surface of the airfoil and a second group may be oriented to direct cooling air generally radially inward over a surface of the airfoil. Between the first group and the second group of filmholes in each filmrow, a transition region exists. A transition region filmrow group may be disposed within the transition region and may be co-linear with or staggered relative to the first group and/or the second group. In this manner, the transition region filmrow group enhances the effectiveness of the cooling proximate to the transition region.

Abstract: Embodiments of the present invention provide methods and apparatus for increasing turbulent mixing in the wake of at least one wind turbine. Doing so, increases efficiency of a wind turbine located in the wake by transferring energy to the wake that was lost when the wind passed through the upwind turbine. Turbulent mixing may be increased by changing the induction factor for a rotor by, for example, altering the pitch of the blades, the RPMs of the rotor, or the yaw of the nacelle. These techniques may be static or dynamically changing. Further, the different induction factors for a plurality of wind turbines may be synchronized according to a predetermined pattern to further increase turbulent mixing.

Abstract: A test blade for use in a blade-release test in which the blade is mounted on a rotatable hub and at least a portion of the blade is released therefrom by the action of a controlled explosion. The blade has a root portion for mounting on said rotatable hub and the root portion comprises a radially inner surface having a channel extending at least partly along or proximal the camber line. The channel is for receiving at least one explosive charge and at least one detonator which may be contained within a charge carrier.

Abstract: A turbocharger system may include a turbine housing and a tongue insert. The turbine housing may include an inlet, an outlet, and a gas pathway between the inlet and outlet. The gas pathway may include a volute portion and an inlet portion extending approximately tangent to the volute portion. The turbine housing may be formed from a first material. The tongue insert may be received in the turbine housing and may at least partially define the volute portion and the inlet portion. The tongue insert may be formed from a second material that is more heat resistant than the first material.

Abstract: A rotor blade system includes a first hub assembly having a first set of rotor blades and rotatably attached to a rotor mast, a second hub assembly having a second set of rotor blades and rotatably attached to the rotor mast, the second hub assembly being positioned at a space relative to the first hub assembly, a torque splitter device engaged with both the first hub assembly and the second hub assembly, and a locking device operably associated with the torque splitter device. The method includes rotating the first hub relative to the second hub via the torque splitter until the first set of rotor blades align with the second set of rotor blade about a common horizontal axis.

Abstract: Recirculation systems for engine intake air are disclosed having a turbocharger compressor with an inlet and an outlet, a recirculation pathway connecting fluid flow from the outlet of the turbocharger compressor to fluid flow into the inlet of the turbocharger compressor, and a recirculation valve assembly controlling fluid flow through the recirculation pathway. The recirculation valve assembly includes an actuator operating a valve coupled to an aspirator assembly that produces vacuum when the fluid flows through the recirculation pathway from the inlet to the outlet and when fluid flows through the recirculation pathway from the outlet to the inlet. Fluid flows through the recirculation pathway from the outlet to the inlet when the turbocharger generates boost. The vacuum generated by the aspirator assembly is in fluid communication with the actuator to move the valve between two or more positions.

Abstract: A rotor blade vibration damper for a gas turbine engine includes an elongated damper body including a top portion extending longitudinally between a front end and a rear end. The top portion has a width defined between spaced apart lateral sides and is substantially flat between the front and rear ends and between the lateral sides such as to define a longitudinal plane within which the top portion lies. A front tab extends downwardly from the front end of the top portion relative to the longitudinal plane. The rear end of the top portion is flat and generally contained in the longitudinal plane. A pair of lateral tabs extends downwardly from each of said lateral sides of the top portion relative to the longitudinal plane.

Abstract: A fan cover (10), on which a fan motor (11) is mounted, includes: a fan cover flat portion in which an opening portion (12) is formed; a protruding portion (13) extending from the fan cover flat portion around the opening portion; and a supporting portion (14), which is arranged on the protruding portion, for supporting the fan motor, wherein a distance between the fan cover flat portion and the supporting portion of the protruding portion is smaller than the thickness of the fan motor.

Abstract: A cooling system for a turbine engine for directing cooling fluids from a compressor to a turbine blade cooling fluid supply and from an ambient air source to the turbine blade cooling fluid supply to supply cooling fluids to one or more airfoils of a rotor assembly is disclosed. The cooling system may include a compressor bleed conduit extending from a compressor to the turbine blade cooling fluid supply that provides cooling fluid to at least one turbine blade. The compressor bleed conduit may include an upstream section and a downstream section whereby the upstream section exhausts compressed bleed air through an outlet into the downstream section through which ambient air passes. The outlet of the upstream section may be generally aligned with a flow of ambient air flowing in the downstream section. As such, the compressed air increases the flow of ambient air to the turbine blade cooling fluid supply.

Abstract: A ceramic shroud seal has a roughed inner surface for contacting a rotating turbomachine component.

Abstract: A control device of the pitch of blades of a rotor of a propeller is provided. The control device includes: a radial shaft; a pivot connected to the blade, the rotation of the radial shaft driving the rotation of the pivot for the modification of the pitch of the blade; an insert fixed rigidly to the pivot so as to block their relative displacement, the radial shaft being configured to drive in rotation the insert; at least one peg passing through the insert and the pivot for transmission of the rotation of the insert to the pivot; and a heat insulation element arranged between the insert and the pivot, whereof the thermal conductivity is less than the thermal conductivity of the pivot and of the radial shaft.

Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. The pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface. A baffle is arranged in the airfoil cavity and includes a supply hole. Ribs extend from the pressure and suction side walls into the airfoil cavity and engage the baffle. The ribs are configured to provide a serpentine cooling passage between the baffle and at least one of the pressure and suction side walls. The serpentine cooling passage has first and second passes joined by a bend. The ribs form a film cooling cavity between the first and second passes. The supply hole fluidly connects the baffle to the film cooling cavity. Film cooling holes extend through at least one of the pressure and suction side walls. The film cooling holes are in fluid communication with the film cooling cavity.

Abstract: A turbine assembly includes a turbine housing and a turbine wheel disposed within the turbine housing. The turbine wheel includes a rotational axis and a plurality of blades. The turbine assembly includes a turbine shroud disposed between the turbine housing and the turbine wheel along a radial direction. The turbine shroud is separate from the turbine housing. The turbine shroud includes an annular portion extending generally in an axial direction with respect to the rotational axis and a plate portion intersecting the annular portion to form a convex curved surface. At least a portion of the blades is disposed in at least a portion of the annular portion. Each blade includes a leading edge and a tip portion. Each leading edge is angled with respect to the rotational axis, and each tip portion forms a concave portion that curves around the curved surface of the turbine shroud.

Abstract: An airfoil for a gas turbine engine includes an airfoil body that extends in a radial direction from a support. The airfoil body has pressure and suction side walls joined at leading and trailing edges to provide an exterior airfoil surface. A chord-wise direction extends between the leading and trailing edges and a thickness direction transverse to chord-wise direction and extending between the pressure and suction side walls. Cooling passages extend from the support into the airfoil body. The cooling passages include adjacent passageways in the thickness direction and are separated by a chord-wise wall. One of the adjacent passageways is adjacent to another passageway in the chord-wise direction and is separated by a rib in the thickness direction. The rib is discontinued at a location along the radial direction to provide an opening that fluidly connects one of the adjacent passageways to the other passageway.

Abstract: A vane includes a pair of airfoils that have a plurality of film cooling holes that extend through an exterior surface of the airfoils. Each plurality of film cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1. Each geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.

Abstract: A latch device (12) for a hydraulic valve (10) is proposed. The latch device (12) comprises a housing (22) and a latch shaft (26), which is supported such that it can move in the housing (22). In order to create a latch device (12), independent of the hydraulic provisioning, the provision of at least one magnetizable ring beam arrangement (38), which is supported on the latch shaft (26), and an electric solenoid arrangement (40), located on the housing (22) around the ring beam arrangement (38) is also proposed, wherein by the supply of current to the solenoid arrangement (40), a positioning force can be produced on the ring beam arrangement (38). Furthermore, a hydraulic valve (10) with the corresponding latch device (12) and a hydraulic arrangement (92) for such a valve (10) are also proposed.

Abstract: The adjustable wall mounted fan is a device comprising a frame, a mounting plate, a detent, and a positioning device. The frame, mounting plate, and a fan are mounted on the wall. The positioning device raises and lowers the fan vertically and the detent is used to hold the fan is position. The adjustable wall mounted fan is used to improve ventilation in a room.

Abstract: A device recovers energy in working machines with at least one power drive actuated to move a load mass back and forth and with an energy storage system (16) absorbing the energy released in the movement of the load mass in one direction and making it available for a subsequent movement in the other direction. The energy storage system includes an accumulator cylinder (16) mechanically coupled to the load mass and storing pneumatic pressure energy for movement in one direction. For movement in the other direction, the accumulator cylinder acts as an auxiliary working cylinder supporting the power drive and converting the stored pressure energy into driving force.

Abstract: A shaftless fan includes a fan stator, a vane rotor and a rolling bearing. The rolling bearing is installed between the fan stator and the vane rotor and includes an inner ring, an outer ring, and a plurality of rolling elements rollably installed between the inner and outer rings, and the inner and outer rings of the rolling bearing are rotated in opposite direction with respect to each other, so that the vane rotor can be rotated on the fan stator to connect the fan stator with the vane rotor through the rolling bearing, so as to achieve the shaftless effect.

Abstract: A submersible pump assembly has a centrifugal pump with a number of stages, each of the stages having a rotatable impeller and a non rotating diffuser. The diffuser has vanes, each of the vanes curving radially inward from an outer end to an inner end. The vanes define vane passages between adjacent ones of the vanes through which well fluid flows. The vanes have thicknesses between inner and outer sides of each of the vanes that gradually increase from the outer ends toward the inner ends. At least one pocket is formed in each of the inner sides of each of the vanes. The pockets are open cavities to receive a portion of the well fluid flowing from the vane passages to the diffuser outlet.