Abstract: Disclosed is a multiple blade wind turbine (MBWT). The MBWT includes: at least one rotor comprising two closed loop tracks positioned parallel or equidistant to one another and a plurality of airfoils interspaced within the tracks. The plurality of airfoils are connected at each end to one of said tracks and are fully rotatable with respect to said closed loop tracks. A transmission is connected to one of the tracks. The track drives the transmission and an electric generator is connected to said transmission for generating electricity. The rotors are oriented vertically or horizontally with respect to a vertical support structure that is used to support the rotors. The MBWT's design allows the electric generator(s) and transmission system to be housed relatively close to ground level. This configuration reduces the mass of the central support tower and reduces the construction and ongoing maintenance costs.

Abstract: A slurry seal assembly for use about a rotatable shaft between a process side and an atmosphere side is presented. The slurry seal assembly includes a sleeve, a rotatable seal ring, a stationary seal ring, a floating bushing seal assembly, and a plurality of slots. The sleeve is disposed about and rotatable with the shaft. The rotatable seal ring contacts and is rotatable with the sleeve. The stationary seal ring is arranged to form a sealing interface with the rotatable seal ring. The floating bushing seal assembly is disposed about the sleeve so that an inner annular surface along the floating bushing seal assembly is separated from an outer annular surface along the sleeve by a gap. The slots are disposed along the sleeve within the process side adjacent to the floating bushing seal assembly. The slurry seal assembly is applicable to devices whereby a fluid is movable between an inlet and an outlet.

Abstract: A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.

Abstract: There is provided a wind turbine rotor blade comprising a rotor blade root region, a rotor blade tip region, a pressure side, a suction side, at least one fin which extends along a longitudinal direction of the rotor blade and at least one deflection unit between an end of the at least one fin and the rotor blade tip region. The at least one deflection unit is adapted to deflect an air flow which is propagated along the at least one fin. In addition there is provided at least one fin drop-shaped portion arranged in the region of the at least one fin to reduce turbulence in the air upon deflection.

Abstract: A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.

Abstract: A case cooling calibration system for a gas turbine engine includes a rotor casing, and a stage, rotatably mounted within the rotor casing. The rotor-casing includes in-series fluid communication, a duct, a flow control valve, and a manifold. The valve regulates an air flow through the duct to the manifold, which is arranged radially outwardly around the casing radially coplanar with the rotor stage. A temperature sensing apparatus is positioned on the rotor casing, radially outwardly of the rotor stage. A controller regulates the valve in a stepwise manner providing a variable cooling air-flow to the rotor-casing. A processor calculates a correction depending on a comparison between the rotor casing temperature and a predicted rotor-casing temperature for a given engine power condition. An engine controller controls the valve depending on the correction characteristic to maintain a predetermined operational radial clearance between the rotor-stage and the rotor-casing.

Abstract: An embodiment device includes a clamp body having a clamp opening, an extension opening and a traverse block having an internally threaded portion, a reaction plate having a recess in a first face at a first side of the reaction plate and one or more pins disposed in the recess extending away from the first face, and further having an extension extending along a long axis of the reaction plate through the extension opening, and bearing blocks disposed on a second side of the reaction plate opposite the first side, where the traverse block is disposed between the bearing blocks. An actuator is aligned parallel to the long axis of the reaction plate and extending through each of the bearing blocks and through the traverse block, and the actuator has an eternally threaded portion engaged with the internally threaded portion of the clamp body.

Abstract: A fan of a gas turbine engine is provided. The fan having: a plurality of fan blades secured to a rotor, each of the plurality of fan blades having an airfoil secured to the rotor at one end and a tip portion that is secured to a shroud that circumscribes the plurality of fan blades.

Abstract: A propeller blade assembly comprises a propeller blade having a blade root for attaching the propeller blade to a hub. The blade root has a radially outer surface. The assembly further comprises a collar mounted to the blade root. The collar comprises at least two collar segments assembled around the radially outer surface of the blade root. Each collar segment has a radially inner surface, an opposed radially outward surface and first and second circumferential end lugs. The lugs receive fasteners for coupling the collar segments together to form the collar. The collar segments are formed from a flexible plastics material and the radially inner surface of each collar segments engages the radially outer surface of the blade root only over a limited circumferential extent of the collar segment.

Abstract: A stator vane arrangement for a turbomachine comprises a radially inner annular structure, a radially outer annular structure and a plurality of circumferentially spaced vanes extending radially between the inner annular structure and the outer annular structure. At least one of the vanes has a passage extending from the inner annular structure to the outer annular structure. The inner annular structure has at least one radially inwardly extending boss and each boss has a passage extending there-through. The passage in each boss is aligned with a corresponding passage in a vane. Each boss comprises a first portion having a first cross-sectional area and a second portion having a second cross-sectional area which is greater than the first cross-sectional area. The first portion of each boss is positioned between and interconnecting the second portion of the boss and the inner annular structure.

Abstract: Apparatus suitable for use in positioning ceiling or wall panels in predetermined locations. The apparatus includes one or more channel means shaped to receive at least part of a panel in use, said channel means at least partially defined by one or more substantially planar outer walls and at least one inner wall. At least part of the inner wall depends away from the outer wall thereby forming the opening into said channel means through which the ceiling or wall panel is inserted in use.

Abstract: A pump (1, 101) includes a pump housing (2, 102) having an intake opening (5, 105) and a plurality of outlet openings (6, 106). A pump wheel (9, 109) is accommodated in the housing (2, 102) in a rotationally drivable manner to effect a fluid stream from the intake opening (5, 105) to the respective outlet opening (6, 106). An adjustable ring element (13, 113) is provided radially outside the pump wheel (9, 109) and inside the housing (2, 102). The adjustable ring element (13, 113) enables the fluid stream through the respective outlet opening (6, 106) to be regulated.

Abstract: The present disclosure is directed to a gas turbine engine defining an axial centerline, a longitudinal direction, a radial direction, and a circumferential direction. The gas turbine engine includes one or more frames in which the frame defines an inner ring and an outer ring generally concentric to the inner ring about the axial centerline. The frame defines a plurality of struts extended outward along the radial direction from the inner ring to the outer ring. One or more struts define one or more service passages extended at least partially along the radial direction within the strut, and wherein the inner ring, the outer ring, and the struts together define an integral structure.

Abstract: A fan module includes a first casing, a driving motor disposed in the first casing, a first rotor connected to the first driving motor, a second casing, a second rotor pivotally configured in the second casing, at least one guiding member and a shift apparatus connected to the first casing and the second casing, the first rotor includes a first rotating shaft and a plurality of first blades, the second rotor includes a second rotating shaft and a plurality of second blades, the guiding member is disposed on the first blade and the second blade. The whole height of the blade is adjusted by adjusting the distance between the two group blades, then the efficiency of the fan is improved effectively to optimize the noise level and the air flow.

Abstract: An airfoil for a gas turbine having an outer shell with an inner volume and an inner shell arranged within the inner volume of the outer shell, wherein the inner shell has an aerodynamic profile having an inner nose section and an inner tail section. A first cooling channel and a second cooling channel merge into a common cooling channel at an inner tail section. A first tail fin is arranged between the first cooling channel and the common cooling channel such that a first mass flow rate of the cooling fluid flowing through the first cooling channel is controllable. A second tail fin is arranged between the second cooling channel and the common cooling channel such that a second mass flow rate of the cooling fluid flowing through the second cooling channel is controllable.

Abstract: An apparatus for a turbine engine, such as a gas turbine engine, can include an engine component such as an airfoil. The airfoil includes an outer wall with a pressure side and a suction side confronting a hot gas flow exterior of the airfoil. A cooling circuit can provide a flow of cooling fluid through the interior of the airfoil to cool the airfoil operating within the hot gas flow. The cooling circuit can include a pin bank to induce turbulence on the cooling fluid to improve cooling of the airfoil.

Abstract: A fan blade includes a tip assembly that is disposed on a blade body. The tip assembly has a leading edge wall disposed proximate a leading edge of the blade body, a trailing edge wall disposed proximate a trailing edge of the blade body, a suction side wall that extends between the leading edge wall and the trailing edge wall, a pressure side wall disposed opposite the suction side wall and extends between the leading edge wall and the trailing edge wall, and a tip wall that extends between the leading edge wall, the trailing edge wall, the suction side wall, and the pressure side wall and is disposed parallel to the tip.

Abstract: A fan assembly for a gas turbine engine includes a fan including a plurality of fan blades extending radially outwardly from a fan hub to a blade tip defining a fan diameter. A nacelle surrounds the fan and defines a fan inlet upstream of the fan, relative to an airflow direction into the fan. The nacelle has a forwardmost edge defining an inlet length from the forwardmost edge to a leading edge of a fan blade. A ratio of inlet length to fan diameter is between 0.20 and 0.45. A nacelle inner surface defines a nacelle flowpath having a convex throat portion and a diffusion portion between the throat portion and the leading edge of the fan blade at a topmost portion of the nacelle. The throat portion has a minimum throat radius measured from a fan central axis greater than a blade tip radius.

Abstract: The present disclosure provides a centrifugal blower assembly that includes a centrifugal fan and a scroll casing housing the centrifugal fan. The scroll casing includes a scroll starting position, a scroll ending position and an air passage extending between the scroll starting and ending positions. The scroll ending position is downstream from the scroll starting position relative to airflow through the scroll casing. The centrifugal blower assembly further includes an air outlet extending from the scroll ending position and a plurality of resonators mounted on an exterior surface of the air outlet. Each of the plurality of tuned resonators has respective cavities in fluid communication with inside of the air outlet. Each of the cavities has respective different volumes, heights, widths, and/or lengths from each other.

Abstract: Turbine housing assemblies and related turbocharger systems are provided. One exemplary turbine housing assembly includes a bypass valve assembly structure including a guide portion, an inner sheet metal shell including an inner inlet portion and a volute portion providing an outer contour of a volute, wherein an end of the inner inlet portion is surrounded by the guide portion and spaced apart from the bypass valve assembly structure, and an outer sheet metal shell radially surrounding at least a portion of the volute portion and including an outer inlet portion surrounding the inner inlet portion and contacting the guide portion of the bypass valve assembly structure.