Abstract: A turbocharger housing is divided along the longitudinal direction into at least two housing halves. The turbocharger housing includes a sealing device between the two housing halves for sealingly connecting the two housing halves.

Abstract: An apparatus, system and method for pumping gaseous fluid are described. The centrifugal pump of the invention homogenizes at least a portion of the gas and liquid contained in produced well fluid thereby improving the efficiency of the pump in electric submersible pump (ESP) applications and decreasing the downtime of the ESP system. The impeller of the invention comprises an increased inlet area. The centrifugal pump of the invention comprises a single shroud located on the bottom side of an impeller, an increased inlet area of the impeller and an increased clearance gap between the impeller and a diffuser. One or more truncated vanes extend substantially upstream from the single shroud, wherein each truncated vane sits at a mid-pitch location between untruncated vanes starting from the bottom side of the impeller.

Abstract: A wind turbine blade 2 comprises a profiled contour including a leading edge 34 and a trailing edge 33 as well as a pressure side and a suction side. The profiled contour is formed by a first shell part 10 and a second shell part 15 being bonded together in a bonding region between the first and the second shell part by a curable bonding means 40. The first and the second shell part 10; 15 are formed in a fiber-reinforced polymer. The wind turbine blade further comprises resistive heating means 50 being arranged in thermal connection with the bonding means 40 such that the resistive heating means 50 supplies heat for curing of the curable bonding means 40 during assembling of the wind turbine blade.

Abstract: A synthetic jet for a stationary vane for a turbo-machine is disclosed. The synthetic jet includes a backside cavity and a jet cavity. The jet cavity includes a frontside cavity adjoining the backside cavity and a jet passage extending from a fluid stream interfacing surface of the airfoil towards the frontside cavity. The jet passage is in flow communication with the frontside cavity. The synthetic jet also includes a disk located between the backside cavity and the frontside cavity. The disk includes a cylindrical disk and a coating on each side of the cylindrical disk. The coating is a piezo electric ceramic material.

Abstract: An aircraft gas-turbine engine has an engine cowling-nacelle which surrounds a core engine in a tubular way, characterized in that at least one inflow-side part of the engine cowling-nacelle is telescopically movable against the flow direction.

Abstract: Embodiments of a gas turbine engine rotor including stress relief features are provided, as are embodiments of method for producing a gas turbine engine rotor. In one embodiment, the method includes producing a hub preform in which a plurality of elongated sacrificial cores are embedded. Blades are attached to an outer circumference of the hub preform by, for example, bonding a blade ring to the outer circumference of the preform. The blades are spaced about the rotational axis of the gas turbine engine rotor and circumferentially interspersed with the plurality of elongated sacrificial cores. The plurality of elongated sacrificial cores are then removed from the hub preform to yield a plurality of stress distribution tunnels extending in the hub preform.

Abstract: A system and method are provided for controlling the movement of an aircraft engine cowl door between an open position and a closed position. The system includes an electric motor, at least one actuator, and an electrically operated brake. The actuator is coupled to the motor and is operable to move the cowl door between the closed and the open position. The electrically operated brake is coupled to the electric motor and the at least one actuator and is configured, upon being energized, to supply a unidirectional resisting torque load to the electric motor that does not prevent motor rotation.

Abstract: An exhaust-gas turbocharger (1) having a turbine housing (2), a compressor housing (3), a bearing housing (4) which has a bearing housing axis (L), and a connecting device (5) for connecting the bearing housing (4) to the turbine housing (2) and/or to the compressor housing (3). The connecting device has a multiplicity of screws (6), a number of screw holes (7, 7?) in the bearing housing (4) corresponding to the number of screws (6), and in the turbine housing (2) and/or in the compressor housing (3) a number of threaded holes (8) corresponding to the number of screws (6). The screw holes (7, 7?), the threaded holes (8) and the screws (6) are arranged at an acute angle (?) with respect to a joining surface (9) between the bearing housing (4) and the turbine housing (2) or between the bearing housing (4) and the compressor housing (3).

Abstract: Disclosed is a pump for conveying a pump having a pump rotor rotatably supported about an axis of rotation in a pump stator in the operating state and a rotor shaft is arranged in a shaft leadthrough such that a lubricating film of a lubricating fluid formed from the pump fluid can be formed in a ring gap between the rotor shaft and the shaft leadthrough; and wherein a separation device is provided at the rotor shaft by which a predefinable quantity of an ingredient can be separated from the pump fluid by means of a centrifugal force for providing the lubricating fluid at the ring gap in the operating state, wherein a recirculation device is provided so that a gas can be recirculated with the aid of the separation device.

Abstract: An attachment system for attaching at least one exhaust diffuser downstream from a turbine assembly in a gas turbine engine is disclosed. The attachment system may include at least one attachment flange extending from a downstream edge and attached to a spring plate diffuser support structure and at least one attachment flange extending from side edges of the exhaust diffuser to couple sections of the exhaust diffuser together. The diffuser may also include a thermal barrier/cooling system for controlling a temperature of an outer case of the gas turbine engine. The thermal barrier/cooling system may form a flow path for an ambient air flow cooling.

Abstract: The present invention relates to a cooling device for a jet engine having an axial compressor with several compressor stages including a rotor with rotor blades, a stator with stator vanes and an annulus. In order to reduce the temperature of the components at the outlet of the high-pressure compressor by simple measures and hence to increase the efficiency of a jet engine, a slot-like branch opening surrounding the rotor for a cooling airflow diverted from the main airflow into a first cavity upstream of the rotor is provided upstream of the last compressor stage of the axial compressor, with passage openings being arranged in the rotor for passing on the diverted cooling airflow from the first cavity into a second cavity downstream of the rotor.

Abstract: A gas turbine configured to prevent eccentricity of a rotor (14) due to heat is installed with a strut (23), an outer diffuser (24), an inner diffuser (25), a strut cover (26), and a partition wall (28), wherein the gas turbine includes an inflow hole (31) for cooling air (W), a first flow passage (R1) formed between a casing wall (21) and the outer diffuser (24), a second flow passage (R2) formed between the strut (23) and the strut cover (26), a third flow passage (R3) formed between the inner diffuser (25) and the partition wall (28), and an outflow hole (51) installed in the inner diffuser (25).

Abstract: A single-piece compressor nozzle stage for a turbine engine, the stage including two coaxial rings, connected together by radial vanes, the inner ring including an annular cavity for housing a damper for damping vibration by friction, which damper is secured to an annular abradable-material support.

Abstract: A gas turbine engine including at least a first composite part configured for mounting in a second metal part of the engine, the first composite part including an interface surface configured to be in surface contact with the second metal part, the engine including a metal protection removably mounted on the first composite part and configured to cover the interface surface.

Abstract: The present invention provides a cooling fan module for an automotive cooling system, comprising: a cooling fan having a hub and a plurality of fan blades extending from the hub; a motor for driving the cooling fan, the motor having a rotor mounted or supported for rotation about an axis on a fixed shaft or axle of the motor; and an adapter device by means of which the cooling fan is attached to the rotor, wherein the adapter device comprises a connection member for rotationally fixed connection to a body of the rotor, and an attachment member for attachment with the hub of the cooling fan. The connection member may comprise a stub, which is desirably inserted into a central opening or aperture of the rotor body and the adapter device desirably accommodates at least one bearing upon which the rotor is supported for rotation about the rotational axis.

Abstract: A turbocharger has a turbocharger housing having at least one section divided along a longitudinal axis into at least two housing halves. A bearing block device is provided in the turbocharger housing and receives a shaft and impellers of the turbocharger. The shaft with the impellers can be preassembled in the bearing block device and then inserted into the turbocharger housing.

Abstract: System for stabilizing an offshore horizontal axis wind turbine having a tower, the system comprising sensors for generating signals representing detected movements of the tower, and gyroscopes. Each gyroscope has a spinning axis, an input axis and an output axis, and a flywheel rotatable about the spinning axis. The system further comprises an actuator for each gyroscope, said actuator being arranged with its related gyroscope in such a way that this actuator can apply a torque about the input axis of the gyroscope. The system also comprises a control unit for receiving the signals representing detected movements of the tower, and for providing the actuator with suitable control signals for said actuator to apply a torque about the related gyroscope input axis, said torque about the input axis producing a torque about the output axis of the same gyroscope that at least partly dampens the detected movements of the tower.

Abstract: Generally, a mechanically self-regulating propeller is described which may have a central hub unit disposed around a shaft member, at least two blades coupled to the central hub unit, at least one timing hub coupled to each of the at least two blades, and a hydraulic unit coupled to the at least one timing hub. The at least one timing hub is slidably engaged to the shaft member. When not in use the blades lay substantially parallel to the central hub unit. When the central hub unit is rotated the blades begin to open or fan out to a position that is substantially perpendicular to the central hub unit. The propeller may be used any number of implementations including vehicles, generators, and any other mechanism requiring a propeller or similarly structured device.

Abstract: A contra-rotating propeller system for an aircraft turbine engine, including a free power turbine including a first rotor and a second rotor contra-rotating relative to the first rotor, a first contra-rotating propeller and a second contra-rotating propeller to be rotated about a longitudinal axis of the propeller system relative to a stator of the system, and a mechanical transmission device. The mechanical transmission system is provided between the first propeller and the second propeller.

Abstract: A retention system for a fan in a gas turbine engine includes a shaft that is rotatable relative to a bearing support structure about an axis. The retention system includes fore and aft bearings that rotatably support the shaft, with the fore and aft bearings being spaced apart from each other in a direction along the axis. A machined spring reacts between the bearing support structure and the fore bearing to provide a desired axial preload.