A tip shroud includes a pair of opposed, axially extending wings configured to couple to an airfoil at a radially outer end thereof. The tip shroud also includes a tip rail extending radially from the pair of opposed, axially extending wings. Tip shroud surface profiles may be of the downstream and/or upstream side of the tip rail, a leading Z-notch of the tip shroud, and/or downstream radially inner surface of a wing. The surface profiles may have a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X and Y, and perhaps Z and a thickness, set forth in a respective table. The radially inner surface of the wing may define a protrusion extending along the radially outer end of the airfoil, the suction side fillet, and a radial inner surface of the wing to an axial edge of the wing.

A stator vane segment includes: a plurality of airfoil portions; and one outer band and one inner band joined to a tip portion and a hub portion of each airfoil portion. Each airfoil portion is formed by stacking airfoil profiles in a spanwise direction from the hub portion to the tip portion. Each profile includes a leading edge, a trailing edge, a pressure surface, and a suction surface, in a stacking line connecting respective trailing edges of the profiles at spanwise positions. A portion from the tip portion to a predetermined position is a straight line in a radial direction. A portion from the predetermined position to the hub portion is shifted from the pressure surface toward the suction surface in a circumferential direction from the straight line parallel to the radial direction. An amount of the shift monotonically increases from the predetermined position to the hub portion.

A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor including a rotor hub and an array of blades circumferentially spaced about the rotor hub, a geared architecture, a compressor section and a turbine section. Each blade includes pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, adjacent blades in the array of blades including a first blade and a second blade, a facing pressure side of the first blade and a facing suction side of the second blade defining a channel having a width that varies in a chordwise direction between the facing pressure and suction sides at a given span position of the first and second blades. The width at each pressure side location of the first blade along the channel is defined as a minimum distance from the respective pressure side location to a location along the suction side of the second blade, and the width of the channel converges in the chordwise direction to establish a throat.

A rotor of a fluid machine includes a wheel with a plurality of blades. Furthermore, the rotor includes an inter-blade area defined circumferentially between a first blade and a second blade of the plurality of blades with respect to the axis of rotation. Moreover, the rotor includes a balancing mark on the wheel and within the inter-blade area. The balancing mark is elongate and has a first end and a second end. The first end and the second end are stepped axially into the inter-blade area. The balancing mark extends arcuately between the first end and the second end. The balancing mark has a depth that varies as the balancing mark extends arcuately between the first end and the second end. The balancing mark has a width that varies as the balancing mark extends arcuately between the first end and the second end.

A vacuum pump includes a plurality of exhaust stages provided between an inlet port and an exhaust port so as to function as means for exhausting gas molecules, and a number of blades provided between the inlet port and an uppermost exhaust stage of the plurality of exhaust stages so as to rotate together with a rotary blade that constitutes the uppermost exhaust stage as a particle transport stage for transporting particles in an exhaust direction of the gas molecules, the number being smaller than the number of rotary blades that constitutes the uppermost exhaust stage.

An impeller with impeller blades arranged around a rotational axis of the impeller. Integral, seamless, and notch-free transitions are formed into a disc body on at least one of their two axial sides. The disc body connects the impeller blades in the circumferential direction around the rotational axis. Covering portions, between the impeller blades, determine the flow channels of the impeller.

A seal device of a turbine includes: at least one step surface disposed on a radially outer surface of a rotor blade facing a first radial-directional gap or on an outer peripheral surface of a rotor facing a second radial-directional gap, the at least one step surface facing upstream in a flow direction of a fluid and dividing the radially outer surface of the rotor blade or the outer peripheral surface of the rotor into at least two sections in an axial direction of the rotor; at least two seal fins protruding toward the at least two sections, respectively, from a surrounding member or the stationary vane, and facing the at least two sections via a seal gap, respectively, the at least two seal fins forming a cavity which extends over the at least one step surface in the axial direction of the rotor between each other.

A blower apparatus according to an exemplary embodiment of the present invention includes a motor including a shaft arranged to extend along a central axis extending in a vertical direction, and a bearing arranged to rotatably support the shaft; an impeller coupled to the shaft on an upper end side of the shaft; an impeller housing arranged to house the impeller, and including an air inlet on an upper side; a plurality of stationary vanes arranged on a lower side of the impeller housing; a cylindrical first ring arranged radially inside of the stationary vanes; and a cylindrical second ring arranged radially outside of the stationary vanes, and fixed to the impeller housing. The stationary vanes, the first ring, and the second ring are defined by a single monolithic member, and together define at least a portion of a stationary vane support portion.

A blisk 10 for a gas turbine includes a rotor blade row 12 extending around a central axis X and, axially spaced therefrom and extending coaxially therewith, at least one annular sealing fin 11. The sealing fin has a radially outer annular portion 111 that is thickened as compared to a radially more inward annular portion 113. A compressor 1 includes a rotor and a casing 30. The casing includes at least one stator vane row having at least one abradable liner. The rotor includes at least one blisk 10, whose at least one sealing fin 11 at least partly engages in the abradable liner. A turbine is constructed analogously. A method for manufacturing a blisk 10 for a gas turbine includes producing a blisk 10 having least one annular sealing fin 11, as well as applying a coating 116 to a radially outer surface 115 of a thickened annular portion 111 of sealing fin 11.

A turbine housing assembly can include a turbine housing that defines a rotational axis for a turbine wheel; and a cartridge receivable by the turbine housing, where the cartridge includes a nozzle wall component with an upper nozzle surface and a plate component with a lower nozzle surface, where the upper nozzle surface and the lower nozzle surface define a nozzle space, and vanes positioned in the nozzle space, where the vanes are pivotable between a closed vanes position of 0 percent open and a fully open vanes position of 100 percent open, and where, for a vanes position of at least 50 percent open and less than 75 percent open, an axial dimension of the nozzle space increases with respect to decreasing radius as measured from the rotational axis.