A thrust reverser track beam is disclosed. The thrust reverser track beam may comprise a recess defined by a reception surface and/or a perimeter surface surrounding the reception surface and extending away from the reception surface, wherein the reception surface and the perimeter surface bound a recess that is configured to receive a noise suppressing structure. The thrust reverser track beam may further comprise the noise suppressing structure. The recess is generally triangular in shape and may extend away from a plane. The noise suppressing structure may be generally triangular in shape and may extend away from a plane. The noise suppressing structure may be coupled within the recess of the track beam and/or to the track beam.

An air flow guide cap for inducing an air flow into a through hole of the floor includes: an upper surface upwardly inclined relative to a horizontal plane; and a wall surface downwardly extending along edges of the upper surface except the edge adjacent to an air inlet.

An airfoil in a gas turbine engine includes opposed pressure and suction sides joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend spanwise from a root to a tip of the airfoil. The airfoil has a spanwise distribution of maximum thicknesses of chordwise cross-sections of the airfoil. The spanwise distribution of maximum thicknesses decreases from the root to the tip. In one aspect, the spanwise distribution is stepped between a first portion extending from the root and a second portion extending to the tip.

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 assembly is provided for a turbine engine. This assembly includes a static structure and an impeller rotor housed within the static structure. The impeller rotor includes a vane structure and a shroud. The vane structure includes a first sidewall, a second sidewall and a plurality of vanes arranged circumferentially about a rotational axis. The vanes include a first vane. The first vane includes a first portion, a second portion and a third portion. The first portion is axially between the first sidewall and the second sidewall. The second portion is radially between the first sidewall and the shroud. The third portion is radially between the second sidewall and the shroud. The shroud circumscribes the vane structure. A gap is formed by and extends between the shroud and the static structure. A dimension of the gap changes as the gap extends along the shroud.

An electric submersible pump (ESP) assembly bearing is described. A bearing set for an ESP assembly includes a rotatable sleeve, and a bushing outward of the rotatable sleeve, the bushing including a tubular portion, and a radial flange extending around a downstream side of the tubular portion. An ESP assembly includes a rotatable shaft, at least one stage stacked in series on the rotatable shaft, each stage including a diffuser, a stationary bearing member including a tubular portion secured within a working fluid exit of the diffuser, a stationary member flange extending radially outward from a top of the tubular portion, and a rotatable sleeve inward of the stationary bearing member and secured to the rotatable shaft. A bearing set for an ESP assembly includes a bushing including a tubular portion, and an annular retaining ring groove extending around an outer surface of the tubular portion.

A bladed rotor assembly includes a bladed rotor and a rotor housing. The bladed rotor has a plurality of blades arranged in a circumferential array around an axis of rotation, and the rotor housing encircles the bladed rotor and has a radially inwardly facing surface. Each of the blades comprises a first, radially extending, edge, a second opposite, radially extending, edge, and a radially distal edge. The radially distal edge has a first end, a second end, and a center portion, with the first end adjoining the first, radially extending, edge, and the second end adjoining the second, radially extending, edge. A clearance between the radially distal edge and the radially inwardly facing surface is a first clearance at the first end, and decreases to a second clearance across the center portion.

It is provided with: a variable nozzle mechanism for regulating a flow of exhaust gas to a turbine rotor; a link mechanism for converting reciprocal displacement from an actuator that operates a variable nozzle mechanism into rotational displacement and transmitting the rotational displacement to an inner section of a bearing housing; and an engaging part for engaging an output section of the link mechanism and an input section of the variable nozzle mechanism, and the engaging part is constituted by a pin and a pin insertion slot where the pin is inserted, and a smooth surface is formed around an insertion position of the pin so as to guide a tip of the pin to the insertion position.

A turbomachine component, particularly a gas turbine engine component, has at least one part built in parts from a curved or planar panel, particularly a sheet metal, the part having a plurality of cooling channels via which a cooling fluid, particularly air, is guidable, wherein at least one of the plurality of cooling channels has a continuously tapered section. The at least one of the plurality of cooling channels has a single inlet port from a first surface of the panel and a single outlet port for the cooling fluid to another surface, particularly a surface opposite to the first surface, or to the first surface. Further the panel is built via laser sintering or laser melting or direct laser deposition. A gas turbine engine is equipped with such a component. A method of manufacturing includes incorporating cooling channels having a continuously tapered section.

A component 2 for a bearing, the component 2 comprising a bearing surface 4, wherein the bearing surface 4 is formed so as to be tapered at rest, thereby offsetting deformation of the bearing during an operational condition which generates an induced angle in the bearing surface 4 or an opposing surface of the bearing. A method of manufacturing a bearing is also provided. The method comprises: determining an induced angle of a component 2 of the bearing caused by deformation of the bearing during an operational condition: and providing a surface 4 of the component 2 or an opposing component with a taper at rest so as to offset the induced angle generated during the operational condition.