An exhaust gas turbocharger coupling assembly configured to couple an exhaust gas turbocharger to an engine exhaust manifold is provided herein. The coupling assembly includes a first flange, the first flange being coupleable to either the engine exhaust manifold or the exhaust gas turbocharger; and one or more overhanging lips coupled to the first flange, the overhanging lips overhanging the first flange so as to define a slot between the first flange and the overhanging lip, where the slot is configured to receive a second flange associated with the other of the engine exhaust manifold or the exhaust gas turbocharger so as to restrict the first and second flanges moving apart when assembled.

A drive system for driving a fan in a wet cooling tower, wherein the fan has a fan hub and fan blades attached to the fan hub. The drive system has a high-torque, low speed permanent magnet motor having a motor casing, a stator and a rotatable shaft, wherein the rotatable shaft is configured for connection to the fan hub. The drive system includes a variable frequency drive device to generate electrical signals that effect rotation of the rotatable shaft of the motor in order to rotate the fan.

A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. At least one cooling fin is disposed on the radially outer face between the leading edge portion and the trailing edge portion.

A pump assembly comprises an inlet, an outlet and a housing having an inlet aperture in fluid connection with the inlet, and an outlet aperture in fluid connection with the outlet. A rotor located within the housing is shaped to form with an interior surface of the housing a chamber. On rotation of the rotor, the chamber conveys fluid from the inlet aperture to the outlet aperture. The housing carries a seal located in the inlet and urged into contact with the rotor to prevent the passage of fluid past the rotor from the outlet to the inlet. Center lines of the inlet and the outlet are parallel to one another. The outlet can be formed by linear movement of a mold core.

A system includes a multi-stage turbine that includes a first turbine stage having a first wheel having a plurality of first blade segments spaced circumferentially about the first wheel. The turbine also includes a second turbine stage having a second wheel having a plurality of second blade segments spaced circumferentially about the second wheel. The turbine also includes a seal assembly extending axially between the first and second turbine stages. The seal assembly includes a first coverplate coupled to the first turbine stage. The first coverplate includes a first air director. The seal assembly also includes a second coverplate coupled to the second turbine stage. The second coverplate comprises a second air director. The seal assembly also includes an interstage seal. The first coverplate, the second coverplate, or both are configured to support the interstage seal.

A synchronizing assembly for a gas turbine engine has a synchronizing ring. A bumper assembly has a cradle and a bumper held within the cradle. The cradle is secured to the synchronizing ring by at least one fastener without the fastener extending through the bumper. An engine is also disclosed.

A rotary machine is provided. The rotary machine includes a turbine section with a casing and a ring coupled within the casing. The ring has a groove. The rotary machine also includes a nozzle coupled to the ring. The nozzle has a first end, a second end, and an airfoil extending between the first end and the second end along a longitudinal axis. The first end includes a first hook and a second hook. The first hook has a first radially outer surface, and the second hook has a second radially outer surface. The ring and the first end of the nozzle cooperate to form an anti-rotation feature that extends from at least one of the radially outer surfaces along the axis and between the hooks.

A wind turbine includes a tower having an interior, an exterior, a lower end and an upper end; a nacelle coupled to the tower adjacent the upper end and movable to define at least two yaw positions of the nacelle; a rotor coupled to the nacelle; and an access apparatus disposed about the tower adjacent the upper end thereof, the access apparatus defining a passageway into the nacelle that is exterior of the tower, and the access apparatus providing access to the nacelle in the at least two yaw positions of the nacelle. A method for transporting equipment and personnel to the nacelle using the access apparatus is disclosed. A method for assembling a wind turbine having such an access apparatus is also disclosed.

A system includes a multi-stage turbine. The multi-stage turbine includes a first turbine stage with a first wheel having a plurality of first blade segments spaced circumferentially about the first wheel, a second turbine stage with a second wheel having a plurality of second blade segments spaced circumferentially about the second wheel, and an interstage seal assembly extending axially between the first and second turbine stages. The interstage seal assembly includes a first coverplate coupled to the first turbine stage. The first coverplate includes a first seal. The interstage seal assembly also includes a second coverplate coupled to the second turbine stage. The second coverplate includes a second seal. The interstage seal assembly also includes a spacer wheel extending from a rotor shaft and configured to engage with the first coverplate and the second coverplate.

A variable vane assembly for a gas turbine engine compressor and method of manufacturing same is described. A plurality of projections on the inner and/or outer shroud protrude into the annular gas path, each projection being at least partially circumferentially disposed between two variable vanes and located adjacent the overhang portion thereof. The projections have an angled planar surface that is substantially parallel to a plane defined by a terminal edge of the overhang portion of the variable vanes when pivoted through a vane pivot arc.