A gas turbine engine rotor having an axis, comprising: a body about the axis having an inner surface, a seat having an outer seat edge at a first radial location surrounded by the inner surface at a second radial location, a lip along the inner surface having an inner lip edge spaced axially away from the seat to define a gap, the lip at a rated axial location between the inner lip edge and the seat facing toward the seat at a normal angle; a damper in the gap having first and second damper surfaces, the first damper surface adjacent the seat; and a split ring in the gap adjacent the second damper surface, having an outer ring edge spaced from the inner surface, engaging the lip at the rated axial location and resiliently expandable against the lip deflects the split ring to load the damper against the seat.

A blade cooling circuit feed and exhaust duct and related cooling structure are provided. The feed duct may include a feed chamber having a feed entrance fluidly coupled to a cooling fluid source and a feed exit to an elongate entrance to the cooling circuit, the feed exit including a ramped wall maintaining a flow velocity of the cooling fluid along the elongated entrance to the cooling circuit. The exhaust duct may include a substantially concave exhaust chamber including an exhaust entrance at a wider end of the exhaust chamber and in fluid communication with an elongated exit from the cooling circuit, and an exhaust exit at a narrower end of the exhaust chamber, the exhaust exit including an opening to an exhaust passageway from the exhaust chamber.

A system includes a drive shaft and a diffuser positioned around the drive shaft to transmit a flow of fluid. The system also includes an impeller that is rotatable with the drive shaft to induce the flow of fluid through the diffuser. Additionally, the system includes a tapered thrust bearing positionable to receive a downhole force from a pumping stage. The tapered thrust bearing includes a flange sleeve positioned around the drive shaft. The flange sleeve includes a tapered mating surface. The tapered thrust bearing also includes a stationary bushing positioned around the flange sleeve. The stationary bushing includes a tapered receiving surface to receive the tapered mating surface of the flange sleeve.

A boundary layer turbomachine can include a housing defining an interior space and having an inlet opening and an outlet opening to facilitate movement of a fluid through the housing. The boundary layer turbomachine can also include a rotor assembly disposed in the rotor chamber and configured to rotate about an axis of rotation. The rotor assembly can have a plurality of disks spaced apart along the axis of rotation and defining an interior opening along the axis of rotation. The fluid can pass through gaps between the disks and the interior opening as the fluid moves through the housing.

A system includes an exhaust collector tunnel (32) configured to mount inside an exhaust collector (30) of a gas turbine (12). The exhaust collector tunnel (32) has a tunnel wall (33) configured to extend around a turbine shaft (17, 19) of the gas turbine (12). The tunnel wall (33) has a variable diameter (98) along at least a portion of a length of the exhaust collector tunnel (32).

An electric motor assembly includes an electric motor, a fan assembly coupled to the electric motor and configured to rotate therewith about an axis. The fan assembly includes a hub including a cylindrical portion having an inlet end and an outlet end, the hub further including an inlet surface coupled to the inlet end. The fan assembly also includes a plurality of blades coupled to an outer periphery of the cylindrical portion, wherein the inlet surface is tapered to direct an inlet airflow toward the plurality of blades.

A vacuum pump comprises: a pump rotor portion configured such that multiple rotor blade stages including stacking portions formed in a ring shape and turbine blades radially formed on an outer peripheral side of the stacking portions are stacked on each other; a rotor shaft to which inner peripheral surfaces of the stacking portions of the multiple rotor blade stages stacked on each other are fixed; and a communication path allowing communication between a clearance space between the rotor shaft and each stacking portion and a pump exhaust path in which the turbine blades are arranged and discharging gas in the clearance space through the pump exhaust path.

A fan blade includes an arc-shaped body and a connecting portion. The arc-shaped body has a main portion and an end portion connected to the main portion, wherein a width of the end portion is gradually decreased in a direction away from the main portion. The connecting portion is connected to the main portion, and the end portion and the connecting portion are respectively located at two opposite sides of the main portion. A fan structure is also provided.

A ring assembly has a housing made of woven composite material carrying on its radially inner face an acoustic panel with a cellular structure covered with a composite material. The housing includes at least one radial recess in which is engaged at least one radially outwardly projecting part of the radially outer face of the acoustic panel.

To provide a turbine blade, a manufacturing method for a turbine blade, and a gas turbine. In the turbine blade including a cooling passage provided along a blade height direction, the cooling passage includes: a first cooling hole including one end opening toward a front end, and having an inner diameter that is constant along the blade height direction; and a second cooling hole including one end communicating with the other end of the first cooling hole without a level difference, and having an inner diameter that is increased toward a base end. A length from the one end of the first cooling hole to a position where the first cooling hole and the second cooling hole are communicated with is 40% to 60% of a length from the one end of the first cooling hole to a gas path surface on the base end.