A steam turbine apparatus includes: an exhaust chamber which defines an exhaust flow passage; an outside casing including a radially outer wall portion formed on a radially outer side of the exhaust flow passage; an inside casing including a radially inner wall portion disposed on an inner side of the radially outer wall portion; a flow guide disposed on an end portion at a downstream side of the radially inner wall portion, the flow guide having a tubular shape whose distance from an axial center of the steam turbine increases along the flow direction; and at least one bypass flow passage connecting a first inner space upstream of the last stage rotor blade and a second inner space positioned at an outer side of the flow guide. The at least one bypass flow passage extends along an outer peripheral surface of the flow guide.

A steam turbine exhaust chamber defining therein an exhaust passage through which steam having passed through a last-stage blade of a steam turbine is introduced to a condenser includes: a casing including an outer peripheral wall portion formed on an outer peripheral side of the exhaust passage; a bearing cone disposed on a radially inner side of the outer peripheral wall portion; and at least one bypass passage carrying a part of steam flowing through the exhaust passage from a high-pressure portion of the exhaust passage to a low-pressure portion of the exhaust passage or to the condenser, The at least one bypass passage includes a high-pressure-side opening formed in the bearing cone and a low-pressure-side opening facing steam having a lower pressure than steam facing the high-pressure-side opening.

A nacelle for a turbofan gas turbine engine, having in flow series an intake lip, a diffuser and a fan casing. The diffuser has, in flow series, a main section and a recessed section adjacent to the fan casing. A transition region, such as a step, slope or curve, is provided between the main section and the recessed section. In some arrangements the transition region may be configured to promote flow separation and the formation of a separation bubble in the recessed section.

Technologies are described herein for a drag recovery scheme using a boundary layer bypass duct system. In some examples, boundary layer air is routed around the intake of one or more of the engines and reintroduced aft of the engine fan in the nozzle duct in a mixer-ejector scheme. Mixer-ejectors mix the boundary layer flow to increase mass flow.

A centrifugal compressor includes a flow changing groove that is formed on an inner wall of the suction passage and extends in a rotation direction of the compressor wheel. A boundary part of a groove wall of the flow changing groove and the inner wall of the suction passage includes an upstream boundary part positioned on an upstream side in the circulation direction of the gas, and a downstream boundary part positioned on a downstream side in the circulation direction. The upstream boundary part is positioned on the inner side in a radial direction of the compressor wheel than the downstream boundary part, and the flow changing groove is positioned on the upstream side of the wheel in the circulation direction.

An intake for channeling air flowing past a propeller to an inlet of an aircraft engine that drives the propeller with a drive shaft, the intake including: a static cowling that extends along an axis and that flares outward at an upstream end of the static cowling, and an intake slot that is formed in the static cowling. The intake slot connecting to a passage of the inlet of the aircraft engine, the intake slot including an arched opening that extends less than 360 degrees of a circumference of the static cowling, and the intake slot having a downstream lip with a curved profile that blends into the static cowling.

A nozzle segment for a gas turbine engine has a turbine airfoil bound on a first side by an arcuate inner endwall having an inner platform and on a second side by an arcuate outer endwall having an outer platform. The airfoil extends outwardly from the inner platform toward the outer platform. The airfoil body includes opposed pressure and suction sidewalls extending between a leading edge and a trailing edge of the airfoil body. The airfoil body includes a first trailing edge fillet blending into the inner platform at a trailing edge of the airfoil body.

A turbomachine diffuser includes a body having an inner surface defining a diffuser flow path, a plurality of stationary struts extending from the inner surface, and a plurality of flow mixing lobes arranged in an annular array on the inner surface. The plurality of flow mixing lobes is configured and disposed to guide a substantially high momentum flow toward the inner surface of the body.

The present disclosure relates generally to a system for fan nacelle inlet flow control in a gas turbine engine, the nacelle comprising a nacelle inlet cowl including an inlet lip disposed at a leading edge of the nacelle inlet cowl, an inner surface extending aft from the inlet lip, and an outer surface extending aft from the inlet lip and positioned radially outward of the inner surface; and at least one flow control passage extending through the nacelle inlet cowl, each of the at least one flow control passage including a flow control passage inlet, disposed on the inlet lip, and a flow control passage outlet; wherein air may flow into the flow control passage inlet, through the flow control passage, and exits the flow control passage outlet.

Pre-cooler inlet ducts that utilize active flow-control and systems and methods including the same are disclosed herein. The systems include a pre-cooler inlet duct for a jet engine that is configured to receive a pre-cooler air stream and to direct the pre-cooler air stream into a heat exchanger. The pre-cooler inlet duct includes a flow-directing surface, which defines at least a portion of the pre-cooler inlet duct, and an active flow-control device. The active flow-control device is located to modify a boundary layer fluid flow within a boundary layer adjacent the flow-directing surface to resist separation of the boundary layer from the flow-directing surface when the pre-cooler air stream flows through the pre-cooler inlet duct. The methods include methods of resisting boundary layer separation in the pre-cooler inlet duct by flowing the pre-cooler air stream across the flow-directing surface and modifying the boundary layer with the active flow-control device.