Abstract: A bearing support that includes a body through which a bore extends and a plurality of grooves formed in a wall of the bore. Each groove extends from a first end of the bore and terminates prior to a second end of the bore. A bearing can be secured within the bearing support by injecting adhesive into one or more of the grooves.

Abstract: A rotor assembly includes a first rotor having first tabs and a second rotor that is arranged coaxial with the first rotor and that includes second tabs that are interlocked with the first tabs. A retainer locks the first tabs and the second tabs together.

Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.

Abstract: An airfoil includes a leading edge, a trailing edge, a pressure side surface extending from the leading edge to the trailing edge, a suction side surface extending from the leading edge to the trailing edge and generally opposite the pressure side surface and a plurality of cooling holes. The cooling holes are positioned on the airfoil in accordance with X, Y and Z Cartesian coordinate values set forth in an accompanying Table.

Abstract: An offshore wind turbine comprising a tower, where said wind turbine at a level above sea level comprises at least one structure for storing at least one container, said container having the size and measures of a standard container, where said structure is arranged on the side of the tower, and a method of manufacturing such a concrete structure for an offshore wind turbine. The structure for storing one or more containers includes a deck, and at least one bed for supporting at least one container along the container's lower surface and/or edges, where the structure is a concrete structure. By manufacturing the structure from concrete, a very robust and strong structure is achieved.

Abstract: A hybrid drive system in a vehicle includes a prime mover, a starting device connected to the prime mover, and a transmission having a transmission input shaft connected to the starting device. A pump/motor is functionally interconnected between the starting device and the transmission. A first accumulator is in fluid communication with the motor/pump for storing a hydraulic fluid under pressure and a second accumulator is in fluid communication with the pump/motor for storing hydraulic fluid discharged from the first accumulator. Discharge of the first accumulator drives the pump/motor to provide a drive torque to the transmission input shaft and to provide a drive torque to the prime mover for starting the prime mover.

Abstract: A ceiling fan blade includes a blade having at least one locking plate embedded in the interior. The locking plate is provided thereon with at least one locking base protruding out of the reverse side of the blade. A blade holder to be locked with the blade is bored with a locking hole at a location corresponding with the locking base for the locking base to be inserted therein. The blade is firmly locked on the blade holder via at least one locking member. By so designing, there is not any locking member on the downward obverse side of a ceiling fan blade, able to maintain a smooth and pretty external appearance of the ceiling fan blade.

Abstract: The present application provides a variable stator vane control system. The variable stator vane control system may include a variable stator vane positioned by an actuator and a trimmer motor, a resolver to determine a position of the variable stator vane, and a controller in communication with the resolver, the actuator, and the trimmer motor to prevent over travel of the variable stator vane.

Abstract: A link includes a link body with two ends, a ring bore with a ring bore axis and a bearing, a mount bore with a mount bore axis and a bearing. The link also has an end curvature at the end having the ring bore wherein the curvature axis is substantially perpendicular to the ring bore axis.

Abstract: A turbine blade having a tip including a tip shelf through which pass one or more diffuser cooling holes, the diffuser cooling holes directing the flow of cooling gas along the tip shelf, spreading the flow of cooling gas more evenly along the tip shelf and enhancing the formation of a curtain of cooling air along the tip shelf, leading to lower blade tip temperatures, reduced diversion of cooling air, and greater turbine blade life.

Abstract: A mechanical joint for joining two components, the joint having a male part on one component and a corresponding female part on the other component. The male and female parts have respective castellations which intercalate on insertion of the male part into the female part along a direction of insertion. Respective abutment surfaces are formed on the projections of the castellations. The castellations are configured such that, after the insertion of the male part into the female part, the male and female parts can be rotated relative to each other around the direction of insertion to bring: (i) the abutment surfaces into facing alignment and thereby prevent the parts from being pulled apart, and (ii) the indentations of the castellations into facing alignment. The joint has one or more locking members which are insertable into the facing indentations to prevent further relative rotation of the male and female parts.

Abstract: A control unit for controlling a flow rate control valve includes a first computing unit for determining an energy component that heats hydraulic oil, a first setting unit for setting a second relationship between a flow rate through an oil cooler and the energy component based on an experimentally or empirically known, first relationship between flow rate through the oil cooler and an amount of oil cooler heat radiation as derived by replacing the amount of oil cooler heat radiation in the first relationship to the energy component, and a second computing unit for determining the flow rate through the oil cooler based on the energy component determined by the first computing unit and the second relationship. The control unit controls the flow rate control valve according to the flow rate determined by the second computing unit.

Abstract: A gas turbine engine includes a shaft, a speed change device driven by the shaft, and a fan including a fan rotor driven by the speed change device. At least one inducer stage is positioned aft of the fan and is coupled for rotation with the fan rotor.

Abstract: An airfoil, a fan assembly and an unducted contra-rotating fan engine include fabricating at least one airfoil including a suction and a pressure side coupled together at a leading and a trailing edge and extending therebetween. The airfoil includes a plurality of chord sections having a chord length. The airfoil including a tip profile defining a reducing slope extending from the leading edge at the tip portion along at least a portion of the chord length. The tip profile is configured to reduce the high unsteady pressure near the tip portion of the airfoil.

Abstract: In one aspect, a winglet for a rotor blade is disclosed. The winglet may generally include a winglet body extending at least partially between a winglet origin and a blade tip. The winglet body may define a sweep and a pre-bend. The sweep defined between the winglet origin and the blade tip may range from about 0.5% to about 4.0% of a span of the rotor blade. The pre-bend defined between the winglet origin and the blade tip may range from about 1.5% to about 4.5% of the span of the rotor blade.

Abstract: A controller controls the solenoid-operated variable pressure relief valves that are provided to control, at set pressures that can be electrically commanded, pressure of hydraulic oil fed to an attachment cylinder. The controller is provided with a control logic that is capable of controlling the aforementioned solenoid-operated variable pressure relief valves. The control logic performs the aforementioned calculation by compensating for pressure override characteristics of each solenoid-operated variable pressure relief valve based on input signals related to the set relief pressure for and a relief valve passing flow rate of the solenoid-operated variable pressure relief valve, and outputting to the solenoid-operated variable pressure relief valve command signals related to the adjusted set relief pressure resulting from the compensation of the pressure override characteristics.

Abstract: The present application provides a stage of a turbine engine. The stage may include a bucket, a shroud facing the bucket, and a contoured honeycomb seal on the shroud. The contoured honeycomb seal may include a first step with a first shape and a second step with a contoured shape.

Abstract: A system includes at least one gas turbine blade that includes at least one recess disposed in a surface of the at least one gas turbine blade. The system also includes a porous insert that includes multiple pores that enable a cooling fluid to flow through the porous insert. The system further includes a cover plate, wherein the porous insert is disposed within the at least one recess, and the cover plate is disposed over the porous insert to enclose the porous insert within the at least one recess.

Abstract: An energy transfer system includes a power transfer mechanism, a first system, and a second system. The first system includes a first pump-motor operatively connecting the first system to the power transfer mechanism and a regenerative system operatively connected to the first pump-motor. The second system is operatively connected to the power transfer mechanism. Power is transferred between systems by the power transfer mechanism. A method of energy transfer is also provided.

Abstract: The present invention provides novel supersonic compressors comprising novel supersonic compressor rotors. The supersonic compressor rotors are designed to operate at very high rotational speed wherein the velocity of the gas entering the supersonic compressor rotor is greater than the local speed of sound in the gas, hence the descriptor “supersonic”. The new supersonic compressors comprise at least one supersonic compressor rotor defining an inner cylindrical cavity and an outer rotor rim and at least one radial flow channel allowing fluid communication between the inner cylindrical cavity and the outer rotor rim, said radial flow channel comprising a supersonic compression ramp. The novel supersonic compressor rotors are expected to enhance the performance of supersonic compressors comprising them, and to provide for greater design versatility in systems comprising such novel supersonic compressors.