Oil slinger systems include a seal runner comprising an annular radial member having a radius (R) and an outer axially extending member having an axial length (L), wherein a proximal surface of the outer axially extending member comprising a plurality of helical grooves. Methods of radial convective cooling include pumping a cooling liquid through the oil slinger system and convectively cooling the oil slinger.

A rotor wheel for an engine includes a plurality of impeller vanes and a plurality of fluid passages defined by adjacent impeller vanes. The fluid passages are radially disposed across at least a portion of the rotor wheel. One or more impeller inserts may be disposed within one or more of the plurality of fluid passages, respectively. The impeller inserts define an impeller passage with a passage shape that controls a flow of fluid through the one or more of the plurality of fluid passages.

A cooling device for an annular casing of a turbomachine includes a collector housing having ejection openings in a radially inner part of the collector housing facing the annular casing and at least two cooling tubes extending circumferentially from the collector housing and having election openings in a radially inner part of the tubes facing the annular casing. The collector housing having an air passage formed by a radial groove extending radially from a radially inner end of the collector housing to a radially outer end of the collector housing and an axial groove extending from a first axial end to a second axial end of the collector housing.

A gas turbine engine includes a compressor section, combustion section, and turbine section. The turbine section includes a turbine component stage, the turbine component stage including a plurality of turbine components together including a flowpath surface along a circumferential direction of the gas turbine engine. The flowpath surface defines in part a core air flowpath of the gas turbine engine and further defines a contour along the circumferential direction. The contour repeats less frequently than once per turbine component to accommodate a hot gas streak through the turbine section.

Gas turbine engines generally comprise a first-stage nozzle guide vane. Temperatures in a trailing-edge area of the suction-side wall of such vanes can exceed material and coating limits. While an insert can be used to form passages for cooling air to flow along the inner surfaces of the vane walls, design constraints prevent the insert from extending beyond a certain point into the trailing edge of the vane. Accordingly, a fin is disclosed for insertion downstream of the insert. By eliminating sudden expansion beyond the downstream end of the insert and maintaining the speed of the cooling air across the trailing-edge area of the suction-side wall, the fin improves the cooling coefficient for the trailing-edge area, so as to prevent or reduce excessive temperatures in the trailing-edge area.

A gas turbine engine comprises a fan rotor, a lower speed compressor rotor and a higher speed compressor rotor, and a lower speed turbine rotor and a higher speed turbine rotor. The lower speed turbine rotor rotates the lower speed compressor rotor, and rotates a gear reduction to, in turn, rotate the fan rotor. The higher speed turbine rotor rotates the higher speed compressor rotor. An electrical generator is driven to rotate with one of the lower speed turbine rotor and the fan rotor.

An embodiment of an independent cooling circuit for selectively delivering cooling fluid to a component of a gas turbine system includes: a plurality of independent circuits of cooling channels embedded within an exterior wall of the component, wherein the plurality of circuits of cooling channels are interwoven together; an impingement plate; and a plurality of feed tubes connecting the impingement plate to the exterior wall of the component and fluidly coupling each of the plurality of circuits of cooling channels to at least one supply of cooling fluid, wherein, in each of the plurality of circuits of cooling channels, the cooling fluid flows through the plurality of feed tubes into the circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels of the circuit of cooling channels.

A turbine includes: a turbine impeller; a housing disposed so as to enclose the turbine impeller, and including a scroll passage positioned on an outer circumferential side of the turbine impeller and an inner circumferential wall part defining an inner circumferential boundary of the scroll passage; a plurality of nozzle vanes disposed inside an intermediate flow passage which is positioned, in an exhaust gas flow direction, on a downstream side of the scroll passage and on an upstream side of the turbine impeller; and a plate disposed on a side of the intermediate flow passage with respect to the inner circumferential wall part so as to face the intermediate flow passage such that a gap is formed between the plate and the inner circumferential wall part in an axial direction. The plate has at least one through hole through which the intermediate flow passage and the gap are communicated with each other. The at least one through hole opens to a surface of the plate facing the intermediate flow passage, at a position on a radially outer side with respect to a suction surface of at least one of the plurality of nozzle vanes.

A vacuum pump includes a housing having an inlet port, a stator column provided upright inside the housing, a rotating body having a shape surrounding an outer periphery of the stator column, a support means for rotatably supporting the rotating body, and a driving means for driving the rotating body to rotate, wherein gas is sucked in from the inlet port by rotation of the rotating body, and the stator column is constituted of a cast material of aluminum alloy having a mechanical material property of an elongation of 5% or more.

A compressor includes a purge flow extraction path extending radially and configured to direct an airflow radially inwardly. Also included is a center bore at least partially defined by a rotor structure extending axially and fluidly coupled to the purge flow extraction path. Further included is an airflow manipulation device disposed entirely within the center bore, the airflow manipulation device having a plurality of vanes defining at least one vane slot.