A steam turbine exhaust chamber includes a casing and a bearing cone disposed in the casing. The casing has a recess provided along at least a part of a circumference of the casing on a radially outer side of a downstream end of the bearing cone and recessed downstream in an axial direction with respect to the downstream end of the bearing cone.

Various methods and systems are provided for a fluidic variable turbine. In one example, a system for an engine comprises a turbocharger turbine including a nozzle ring, the nozzle ring including a plurality of stationary vanes, each vane of the plurality of stationary vanes including a plurality of injection ports arranged at an outer surface of the vane, and a gas supply system to supply variable gas flow to and out of the plurality of injection ports.

A rotor blade of a turbomachine includes an airfoil. The airfoil includes a root and a tip which define a span of the airfoil therebetween. The airfoil also includes a leading edge and a trailing edge downstream of the leading edge along a flow direction. The leading edge and the trailing edge each extend across the span of the airfoil from the root to the tip. The airfoil further includes a pressure side surface and a suction side surface. The pressure side surface and the suction side surface are continuous about the trailing edge and collectively define an arc centered on the trailing edge. The arc has a semi-major axis and a semi-minor axis. The semi-major axis and the semi-minor axis of the arc define an axis ratio, and the axis ratio varies over the span of the airfoil.

A turbocharger includes a shaft extending between a first shaft end coupled to a turbine wheel, and a second shaft end coupled to a compressor wheel. The turbocharger also includes a bearing housing assembly including a bearing housing presenting an interior surface having a first diameter. The interior surface defines a bearing housing interior. A bushing is disposed in the bearing housing interior, extends between first and second bushing ends, is coupled to the shaft, and includes a first anti-rotation component. A retention shoulder extends away from the interior surface and radially inward proximate to one of the first and second bushing ends, and presents an inner surface having a second diameter less than the first diameter to limit axial movement of the bushing. The retention shoulder includes a second anti-rotation component engagable with the first anti-rotation component to limit rotational movement between the bushing and the bearing housing.

A fiber-reinforced component for use in a gas turbine engine includes a fiber sleeve forming a cooling channel and a plurality of fiber plies enclosing the fiber sleeve, with the plurality of fiber plies forming first and second walls separated by the fiber sleeve. The fiber-reinforced component further includes a matrix material between fibers of the fiber sleeve and the plurality of fiber plies.

An airfoil for a turbine engine includes an array of pins positioned in an internal cavity of the airfoil, such that cooling channels are defined in the interspaces between adjacent pins. Each pin extends lengthwise from a first airfoil wall to a second airfoil wall and is connected thereto at a first intersection and at a second intersection respectively. The pin has a first cross-sectional shape at a respective intersection and a second cross-sectional shape at an intermediate plane located between the first and second intersections. The first cross-sectional shape includes a closed shape defined by relatively sharp corners and the second cross-sectional shape includes a closed shape defined by relatively rounded corners. A cross-sectional area of the pin at the intermediate plane is greater than a cross-sectional area of the pin at the respective intersection.

An impeller tube-type nozzle for a gas turbine, with an inlet section, a retraction section and an outlet section. The inlet section is a section of annular channel, the retraction section comprises multiple gas flow channels separated by multiple blades, each gas flow channel is encircled by an outer peripheral wall face, an inner peripheral wall face, a suction face of one of two adjacent blades and a pressure face of the other of the two adjacent blades, and inlets of the gas flow channels have a fan-shaped cross section. For each gas flow channel, along the direction of gas flow from the inlet of the gas flow channel to the outlet the fan-shaped cross section gradually smoothly transitions into a circular cross section.

An apparatus and method of forming an engine component having an outer wall forming an interior. The interior can be separated into two or more flow paths or flow channels. The two flow paths can be formed by casting having one or more core ties connecting the flow paths during casting. One or more core tie holes can be formed remnant of the core ties during casting in order to fluidly couple the two or more flow paths or flow channels.

A face skin for an acoustic panel may comprise a sheet defining a first surface and a second surface. A plurality of slots may be formed through the face skin using abrasive blasting. Each slot of the plurality of slots may comprise a first semi-circular wall and a second semi-circular wall opposite the first semi-circular wall.

A rotor blade of a turbomachine includes an airfoil. The airfoil includes a root and a tip which define a span of the airfoil therebetween. The airfoil also includes a leading edge and a trailing edge downstream of the leading edge along a flow direction. The leading edge and the trailing edge each extend across the span of the airfoil from the root to the tip. The airfoil further includes a pressure side surface and a suction side surface. The pressure side surface and the suction side surface are continuous about the trailing edge and collectively define an arc centered on the trailing edge. The arc has a semi-major axis and a semi-minor axis. The semi-major axis and the semi-minor axis of the arc define an axis ratio, and the axis ratio varies over the span of the airfoil.