Abstract: A method for manufacturing a joined body including two plate-like portions, the method including forming a joint part that comprises at least a portion of each of the two plate-like portions and joins the two plate-like portions; and irradiating the joint part with a beam, thereby to perform laser welding. The joint part includes at least one folded part, the at least one folded part is a bent part that is bent so as to be folded back in one of the two plate-like portions. First and second bases are formed at both ends of the bent part to face each other such that at least a portion of the other of the two plate-like portions is arranged between the first and second bases, the other of the two plate-like portions including no bent part.

Abstract: A working cylinder has a cylinder tube, a closure part and a further closure part disposed at cylinder tube ends. The closure part has a shaft portion and the cylinder tube has a cylinder tube end portion. The shaft portion and the cylinder tube end portion define a coupling portion where the shaft portion is axially inserted into the cylinder tube at the cylinder tube end portion. The shaft portion has a taper and is oversized, at least in part, relative to an inner diameter of the cylinder tube. The cylinder tube has an elastic circumferential expansion there. The coupling portion is constructed to axially couple the closure part and the cylinder tube. The cylinder tube end is bonded to the closure part by a circumferential annular weld seam that defines a sealing plane.

Abstract: A counter weight for use with a rotor module, including: a root portion; a main body portion that extends away from the root portion; a pair of side portions each extending from opposite sides of the main body portion; and at least one plate secured to one of the opposite sides of the main body portion in order to adjust a weight of the counter weight.

Abstract: The present disclosure relates to a method (100) of controlling operation of a wind turbine (10). The method (100) comprises receiving operational (215) data indicative of oscillations in a wind turbine rotor (18). The method (100) comprises deriving a first signal (224) representative of loads in a first direction in a reference plane and a second signal (226) representative of loads in a second direction in the reference plane. The second direction is different from the first direction. The method (100) further comprises determining an amplitude (A1, A2) of the first (224) and second (226) signals, as well as a phase offset (?1-?2) between the first (224) and second (226) signals. Finally, the method (100) comprises controlling the wind turbine (10) based on the amplitudes (A1, A2) and the phase offset (?1-?2). The disclosure also relates to a control unit (36) for controlling operation of a wind turbine (10) and to a wind turbine (10).

Abstract: An inflatable pump has a housing and a core disposed in the housing. The housing has a core chamber, an inlet at an end of the core chamber, a fan chamber with a volute chamber at the other end of the core chamber, and an outlet fluidly communicating with the fan chamber. The core is disposed in the core chamber and a fan wheel of an electric motor thereof is disposed in the fan chamber. When the electric motor is turned on, the fan wheel is driven to spin to direct air entering the housing from the inlet. Heat around the core is carried by the air passing the core and is directed into the volute chamber of the fan chamber, and is rapidly cast out from the housing via the outlet by a vortical flow generated by the rotation of the fan wheel in the volute chamber.

Abstract: A compressor case having a composition gradient defining a first coefficient of thermal expansion and a second coefficient of thermal expansion that differs from the first coefficient of thermal expansion; and a thermoelectric junction operationally coupled to the composition gradient, wherein the composition gradient is formed of either of a plurality of dissimilar metals or of plastic with fillings or fibers.

Abstract: A squeeze film damper assembly for a turbine engine includes an annular bearing support and an annular damper housing. The annular bearing support includes an inner support segment and an outer support segment located radially outward of the inner support segment. The inner support segment and the outer support segment are spaced apart to define a support channel therebetween. The annular damper housing is at least partially received in the support channel to define an inner damping chamber and an outer damping chamber, the inner damping chamber being radially inward of the outer damping chamber, the inner damping chamber and the outer damping chamber each capable of being filled with an amount of lubricant to provide a squeeze film damper at the inner damping chamber, the outer damping chamber, or both.

Abstract: Provided is a centrifugal compressor, including: a compressor impeller; and a plurality of diffuser blades arranged on an outer side of the compressor impeller in a radial direction so as to be spaced apart from each other in a circumferential direction of the compressor impeller, the diffuser blades each with: a blade angle having a local maximum value, the blade angle being an angle formed between a center line of the diffuser blade and the radial direction; and a thickness having a local maximum on a downstream side of a position at which the blade angle has the local maximum value.

Abstract: The rotor control system includes a main control valve having an inlet for receiving liquid and an outlet for issuing liquid to a rotor pitch change actuator. The rotor control unit is configured to control flow of liquid from the inlet to the outlet to modify pitch angle of rotor blades. A feathering system with a first conduit connected in fluid communication with the outlet of the main control valve, a second conduit for fluid communication with the rotor pitch change actuator, and a drain conduit. The feathering system has a normal operation mode for supplying liquid from the main control valve to the rotor pitch change actuator by allowing flow through the feathering system from the first conduit to the second conduit. The feathering system has a feathering mode for controlling drainage from the rotor pitch change actuator to the drain conduit.

Abstract: A method for a hybrid electric propulsion (HEP) system includes determining a target fan speed for a HEP system. The HEP system includes a gas turbine engine and at least one electric motor configured to rotate a respective shaft of the gas turbine engine. The method also includes determining an amount of electrical power that is currently available to the HEP system; utilizing a model predictive control (MPC) to determine, based on the amount of available electrical power and a plurality of operating limits of the HEP system, an effector command set that includes a power splitting profile indicating a power split between the gas turbine engine and the at least one electric motor for achieving the target fan speed; and implementing the effector command set. A controller for a hybrid electric propulsion (HEP) system is also disclosed.

Abstract: The disclosure relates to a mobile crane, in particular an rough terrain crane, comprising a boom mounted so as to be pivotable about a horizontal pivot axis, a hydraulic luffing cylinder by means of which the boom can be luffed up and down about the pivot axis, a hydraulic control block for controlling the luffing cylinder and a first safety valve which is connected between the control block and the luffing cylinder and is configured to seal off a load-bearing cylinder chamber of the luffing cylinder in a blocking position. According to the disclosure, the crane further comprises a second safety valve, which is connected in series between the first safety valve and the control block and is configured to seal off the load-bearing cylinder chamber of the luffing cylinder in a blocking position.

Abstract: A diffuser stack for a centrifugal pump includes a first diffuser including a first rim having a first inner circumferential surface, a first outer circumferential surface, and protrusions extending radially inward from the first inner circumferential surface. The diffuser stack further includes a second diffuser including a second rim having a second inner circumferential surface and a second outer circumferential surface. Recesses are formed in the second diffuser. The recesses extend radially inward from the second outer circumferential surface. The second diffuser is configured to engage the first diffuser such that the second outer circumferential surface engages the first inner circumferential surface and the protrusions engage the recesses.

Abstract: A method is for repairing a wind turbine rotor blade. The rotor blade includes a component made of a fiber reinforced laminate, wherein the component has a defect. The method includes: providing a repair kit for bridging the defect, the repair kit having a first flange piece, a second flange piece, and a connecting bolt, wherein each flange piece has a mounting portion and a connecting portion; bonding the first flange piece with its mounting portion onto a first surface region of the component and the second flange piece with its mounting portion onto a second surface region of the component such that each flange piece is arranged at a predefined distance from the defect and the defect runs between the two flange pieces, and screwing the first flange piece and the second flange piece together at their connecting portions via the connecting bolt to bridge the defect.

Abstract: A propeller assembly, includes: a shaft having a cylindrical shape and connected to the drive shaft of a motor; a thrust washer provided on the outer surface of the shaft; a hub provided on the outer surface of the shaft, with a thrust washer arranged on one side and multiple ribs protruding from its outer surface; a bushing formed on the outer surface of the hub, having a polygonal column shape; a propeller provided on the outer surface of the bushing, with multiple blades arranged to generate thrust; and an after spacer provided on the outer surface of the shaft, positioned on one side to secure the propeller.

Abstract: A propeller. The blade thrust surfaces of the propeller correspond to the surface of a cone, and the hub axis is set at an angle relative to a first generator line of the cone which passes through the hub axis and a second generator line of the cone which passes through the blade thrust surface to achieve desired gamma angles over the blade thrust surface. A propeller whose blade center axis does not conform to a generator line of a cone also is disclosed.

Abstract: A separator system for a blade outer air seal cooling passage of a gas turbine engine includes a cooling passage defined between an engine casing on a radially outer boundary and alternating blade outer air seals and vanes on a radially inner boundary; and a support positioned along the cooling passage and dividing the cooling passage into an upstream portion and a downstream portion of the cooling passage; wherein the support further includes at least one cyclonic separator having a flow inlet opening to the upstream portion, and having a filtered air outlet feeding to the downstream portion, and a particulate outlet for particles separated from flow through the cyclonic separator.

Abstract: Provided is a fluid pressure actuator in which a bamboo shoot part is formed on a free end side of the sealing member to enable engaging and retaining a cover member that is separate from the fluid pressure actuator.

Abstract: A turbine includes a rotor and a plurality of turbine blades along the rotor. The plurality of turbine blades includes first turbine blades including first moving blades and first shrouds provided to tip ends of the first moving blades, and second turbine blades including second moving blades adjacent to the first moving blades in a first direction of the rotor and second shrouds provided to tip ends of the second blades; in an overlapping region in which at least a portion of a first direction side surface on a first direction side of the first shroud and at least a portion of a second direction side surface on a second direction side of the second shroud overlap in the peripheral direction, the first direction side surface being further outside the second direction side surface; and the second shroud is heavier than the first shroud.

Abstract: A tool (14) for reducing vibrations in wind turbine blades at scheduled standstill for example during turbine installation or service, the tool comprising an elongate flexible sock-like sleeve (16) for fitting over the blades (10) having an airflow-disrupting function and a guard (24) of semi-rigid material provided at an edge of the sleeve which overlies the blade trailing edge into which are received aerodynamic enhancing features such as serrations (20).

Abstract: A tool to generate airflow including a housing that has an intake port and an outlet port, and an impeller coupled to the housing. The housing at least partially defines a volute between the intake port and the outlet port, and the impeller is in airflow communication with the volute to generate an airflow between the intake port and the outlet port through the volute. The tool includes an airflow guide that is disposed in the housing and that has an air intake portion with a volute wall partially defining the volute and disposed in close proximity to the impeller. The air intake portion defines the intake port and a passageway extends from the intake port toward the impeller along an airflow axis.