A turbine blade that includes an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The turbine blade further may include a rib configuration that partitions the chamber of the airfoil into radially extending flow passages. A first flow passage may include a first side on which turbulators are positioned, wherein each of the turbulators comprises a canted configuration.

A centrifugal pump for delivering coolant in vehicles and providing a centering of a pump impeller and a dampening of motor vibrations. The centrifugal pump having a pump housing consisting of a pump head, which forms a single part with a suction nozzle, a discharge nozzle, a spoke, and a bearing support, in which a counter bearing is mounted, in which a first region of a shaft is supported, around which a pump impeller is rotatably mounted via a slide bearing secured in the pump impeller, the spoke retaining the bearing support in a central position within the pump head and having a containment shell, which separates a wet chamber from a dry chamber and in which a second region of the shaft is supported. The invention seeks to solve the problem of providing in a generic centrifugal pump.

In a centrifugal compressor including an impeller rotatably disposed in a housing, the housing includes a shroud wall and a hub wall, which define a diffuser passage communicating with an outlet of the impeller. The diffuser flow passage includes a pinched part configured such that the shroud wall is closer to the hub wall radially outward of the centrifugal compressor from the outlet of the impeller, and a parallel part communicating with the pinched part on a radially outer side of the centrifugal compressor than the pinched part, the parallel part being configured such that the shroud wall and the hub wall are parallel to each other. The shroud wall has a surface facing the impeller and the hub wall, the surface having a cross-sectional shape where a tangent line exists at any position in a cross-section including an axis of the impeller.

A nozzle vane for a variable geometry turbocharger satisfies 0.45<(Xp/L)≤0.60, where L is a chord length of the nozzle vane, and Xp is a distance between a leading edge of the nozzle vane and a rotation center of the nozzle vane.

Variable stator vanes with anti-lock trunnions are disclosed. An example apparatus disclosed herein includes an airfoil to be disposed within a flow path of a gas turbine engine, the gas turbine engine defining an axial axis, a radial axis and a circumferential axis, an outer trunnion, and an inner trunnion including a curved surface in an axial-radial plane, the inner trunnion enabling the airfoil to be rotatably mounted to an inner shroud of the gas turbine engine.

A recuperator disposed in the exhaust duct of a gas turbine engine includes a plurality of recuperator plates arranged in a spaced-apart relationship to define therebetween a plurality of interstices and fluid channels, the plurality of interstices adapted to direct therethrough at least one first stream received at a leading plate edge of the recuperator plates and the plurality of fluid channels adapted to direct therethrough at least one second stream to effect heat exchange between the at least one first stream and the at least one second stream. Each recuperator plate includes, formed at the leading plate edge thereof, a first concavity extending along the leading edge in a direction substantially parallel to a longitudinal axis of the plate. The first concavity extends transversely to a direction of the at least one first stream flowing over each recuperator plate.

An intermediate element is for a blade/rotor disk connection in a rotor of a fluid flow machine. The intermediate element is adapted to a shape of a blade root of a blade and to a blade root slot in a rotor disk for receiving the blade root such that, when arranged between the blade root and rotor disk, the intermediate element prevents contact between the blade root and rotor disk. The intermediate element has, on an outer surface that faces the rotor disk, at least one protrusion to reduce an air flow parallel to an axis of rotation of the rotor between the rotor disk and the intermediate element; and on an inner surface that faces the blade root, a recess that corresponds to the at least one protrusion.

A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a contoured flow surface including a purge valley, an elevated bulge and a bowl. The purge valley has a maximum depth at an elevation equal to or greater than a nominal axisymmetric platform surface of the corresponding platform. The purge valley extending tangentially against a purge cavity wall and into the blend area and extending axially from proximate the leading edge of a first airfoil toward the suction side of the first airfoil, and toward the leading edge of a second adjacent airfoil to channel a purge flow. The elevated bulge adjoins the pressure side aft of the leading edge and the bowl adjoins the suction side aft of the leading edge.

A vane configured to be disposed in a gas path defined in part by an inner surface of a case of a gas turbine engine is provided. The vane comprises a vane body configured to extend through an aperture in the case and a vane head disposed at an end of the vane body. The vane head has an abutting surface configured to contact an outer surface of the case when the vane body extends through the aperture, and a groove configured to receive a sealing member. The groove opens to the abutting surface and is outwardly open relative to an inner region surrounded by the groove. The groove has an inner seating surface that hinders movement of the sealing member toward the abutting surface and can facilitate installation of the vane in the engine.

A housing section of a turbine engine compressor stage or a turbine engine turbine stage that, in particular, has a closed and annular-shaped, radially outer casing. The radially outer casing has radially inwardly extending webs that are angled at a slant relative to the radius.