Radial turbomachine includes fixed case; one rotor disc installed in case and having rotor blades mounted on front face thereof; plurality of elements projecting from case and terminating proximity to rotor disc, wherein projecting elements include seal elements acting against rotor disc are operatively active on rear face of rotor disc or stator blades radially interposed between rotor blades of rotor disc; and one support plate bearing projecting elements and installed in case. Support plate is radially extended across from rotor disc and includes plurality of first circular portions concentric with rotation axis of rotor disc and plurality of second circular portions radially interposed between first circular portions. Several of first circular portions bear projecting elements and second circular portions are more deformable, along radial directions, than first circular portions in manner to allow relative movements between first circular portions when support plate is subjected to action of thermal gradients.

A radial inflow turbine includes a scroll flow passage, a turbine wheel disposed radially inward of the scroll flow passage, a plurality of variable nozzle vanes disposed on a flow passage extending from the scroll flow passage toward the turbine wheel, at a radial position between the scroll flow passage and the turbine wheel, a nozzle mount rotatably supporting each of the plurality of variable nozzle vanes, a nozzle plate arranged to face the nozzle mount and forming the flow passage with the nozzle mount, and a swirl generating member disposed, radially outward of the plurality of variable nozzle vanes, on the nozzle plate in a height range which is smaller than that of a vane height of each of the plurality of variable nozzle vanes. A position of an end part of the swirl generating member on a side of the nozzle mount is farther away from the nozzle mount than a position of an end part of each of the plurality of variable nozzle vanes on the side of the nozzle mount in an axial direction.

A turbocharger includes a turbine housing and a wastegate valve. The turbine housing defines two bypass passages. The wastegate valve opens and closes the two bypass passages. The turbine housing has a valve seat surface that is a flat surface that the wastegate valve contacts. The wastegate valve has a valve surface and a depression. The valve surface is a flat surface that faces the valve seat surface when the wastegate valve is in a closed state. The depression is depressed from the valve surface. The depression is located at a portion that faces a region located between openings of the two bypass passages when the wastegate valve is in the closed state.

Turbine housing assemblies and related fabrication methods are provided. A turbine housing assembly includes a bearing flange, a tongue member, a first sheet metal structure providing an inner contour of an inlet passage and joined to the tongue member, and a second sheet metal structure including an inlet portion providing an outer contour of the inlet and a volute portion providing an outer contour of a volute in fluid communication with the inlet. The volute portion is joined to the tongue member to define the volute, and the inlet portion of the second sheet metal structure is joined to the first sheet metal structure to define the inlet passage.

A cooling system for cooling hot components of a radial or axial gas turbine engine, which includes a recuperator heat exchanger, provides engine cooling without loss of thermal efficiency. Air flow leaving a compressor is split between a recuperator flow path and a bleed flow path. Air in the bleed flow path flows through the hot parts of the engine, thereby cooling the engine and heating the air. The air in the bleed flow path is combined with the output flow from a combustor and directed into a turbine inlet. A reduction of air flow in the recuperator flow path increases the thermal effectiveness of the recuperator heat exchanger by increasing a ratio of hot and cold flows inside the heat exchanger. The increase in thermal effectiveness of the heat exchanger compensates for energy losses incurred by diverting a portion of the compressor air flow for cooling.

A cooling system for cooling hot components of a radial or axial gas turbine engine, which includes a recuperator heat exchanger, provides engine cooling without loss of thermal efficiency. Air flow leaving a compressor is split between a recuperator flow path and a bleed flow path. Air in the bleed flow path flows through the hot parts of the engine, thereby cooling the engine and heating the air. The air in the bleed flow path is combined with the output flow from a combustor and directed into a turbine inlet. A reduction of air flow in the recuperator flow path increases the thermal effectiveness of the recuperator heat exchanger by increasing a ratio of hot and cold flows inside the heat exchanger. The increase in thermal effectiveness of the heat exchanger compensates for energy losses incurred by diverting a portion of the compressor air flow for cooling.

Disclosed is a compressor housing and method of assembling. The compressor housing may comprise an outer volute, a cavity, an impeller cover, a compressor diffuser and an inner volute. The outer volute includes a back wall and a curved casing. The back wall may include a receptacle and a first plurality of annular steps. The receptacle configured to receive an alignment pin. The cavity is configured to receive the compressor impeller and is at least partially defined by the back wall of the outer volute and the impeller cover. The impeller cover is configured to fragment during impact with the compressor impeller during a failure condition of the compressor impeller. The impeller cover is disposed between the inner volute and the cavity. The compressor diffuser is disposed between the back wall and the impeller cover.

An entire scroll is effectively cooled. A scroll of an embodiment leads combustion gas to a turbine stage as a working medium for driving a turbine rotor in a gas turbine facility, and includes a scroll inner cylinder and a scroll outer cylinder. The working medium flows into the scroll inner cylinder. The scroll outer cylinder is provided to cover the scroll inner cylinder with a scroll cooling flow path therebetween where a cooling medium with a temperature lower than the working medium is supplied. The scroll cooling flow path includes an inner ring side flow path part located inside than the scroll inner cylinder in a radial direction of the turbine rotor and an outer ring side flow path part located outside than the scroll inner cylinder in the radial direction of the turbine rotor. Here, a dividing part dividing the outer ring side flow path part in an axial direction along a rotation axis of the turbine rotor is provided at the scroll inner cylinder.

Various systems are provided for an axially split turbocharger case housing each of a turbine of a turbocharger, a compressor of the turbocharger, and a bearing of the turbocharger. In one example, an apparatus for an engine includes a first monolithic component and a second monolithic component that, when coupled together, form a turbocharger case configured to house each of a turbine, a compressor, and a bearing, the first and second monolithic components, when coupled together, also forming a compressor shroud and a turbine shroud. In further examples of the system, portions of the turbocharger case are formed of a lattice structure.

The invention relates to an exhaust gas turbocharger with a manifold-flow casing, in particular a dual-flow casing (47) and a turbine wheel (34) which is rotatably arranged within said manifold-flow casing, onto which an exhaust gas flow (14; 16) may be led via at least one of several flow channels (18, 26), and an outlet opening (78; 80) following said one flow channel (18, 26) and covering an angle of 180° max. about an axis of rotation (44) of the turbine wheel (34), so that a shaft (38) is rotating which is arranged coaxially and non-rotationally relative to the turbine wheel (34), which is supported in a shaft bearing (42).