Axially adjacent annular booster bleed aft and forward plenums with annular common wall therebetween extend radially outwardly from transition duct. Variable bleed valve includes bleed valve door in bleed inlet in transition duct, attached to rotatable valve body rotatable about axis of rotation, operable to open and close bleed inlet to aft plenum. Rotatable plenum door clocked or circumferentially spaced apart from variable bleed valve door and attached to rotatable valve body, operable to close and open up and control flow through an inter plenum aperture in common wall. Aft and forward bleed exhaust ducts extend from booster bleed aft and forward plenums to bypass flow path. One or more heat exchanger, such as from thermal management system, may be disposed in the bleed exhaust ducts. Heat exchangers may be used for cooling oil for power gear box and/or engine bearings, air conditioning, or variable frequency generator.

The present invention relates to a relief valve (1) for a turbocharger, in which the crank arm (3) is made of a first material and the shaft (4) is made of a second material different from the first material used for manufacturing the crank arm (3), each of the materials containing a composition that provides the necessary properties according to the application of each component of the relief valve (1). The present invention also relates to a process for manufacturing the relief valve (1), which allows the crank arm (3) and the shaft (4) to be manufactured separately, using different materials for the manufacture of each component.

A method and system for a turbofan gas turbine engine system is provided. The gas turbine engine system includes a variable pitch fan (VPF) assembly coupled to a first rotatable shaft and a low pressure compressor LPC coupled to a second rotatable shaft. The LPC including a plurality of variable pitch stator vanes interdigitated with rows of blades of a rotor of the LPC. The gas turbine engine system also includes a speed reduction device coupled to said first rotatable shaft and said second rotatable shaft. The gas turbine engine system further includes a modulating pressure relief valve positioned between an outlet of said LPC and a bypass duct and a controller configured to schedule a position of said plurality of variable pitch stator vanes and said modulating pressure relief valve in response to an operational state of said turbofan gas turbine engine system and a temperature associated with said LPC.

A turbocharger assembly may include a turbine wheel. A turbine housing may surround at least part of the turbine wheel. A wastegate port may be defined by the turbine housing and may provide a bypass around the turbine wheel. A valve plate may be movable between a first position closing the wastegate port and a number of additional positions opening the wastegate port. The valve plate may have a face that faces the wastegate port. A shaft may be connected to the valve plate and may rotate about an axis at a pivot point. The pivot point may be located on an opposite side of a line from the valve plate, wherein the line may extend from the face and in a plane within which the face exists when the wastegate port is closed by the valve plate.

A turbocharger system is disclosed, including a turbine and compressor and a rotary valve unit. The rotary valve unit comprises a fixed valve seat and a rotary valve member arranged coaxially with the valve seat. The valve member is disposed against the valve seat and is rotatable about the axis for selectively varying a degree of alignment between respective orifices in the valve seat and valve member. The valve unit includes a valve housing that defines a first flow passage and a second flow passage, and the valve member and valve seat are disposed in the second flow passage. A turbocharger system is also disclosed, including a turbine and compressor and the rotary valve unit. The rotary valve unit is coupled with the turbine such that exhaust gas that has passed through the turbine wheel is fed into the first flow passage of the rotary valve unit, and exhaust gas that has bypassed the turbine wheel is fed into the second flow passage of the rotary valve unit.

A number of variations may include a method for increasing peak flow in a variable geometry turbine turbocharger comprising: by-passing fluid flow to a turbine impeller by forming at least one internal by-pass passage through at least one of a lower vane ring of a vane pack assembly or a turbine housing below the lower vane ring; providing a first end of a vane component within the at least one internal by-pass passage; and using the first end of the vane component as a rotary valve to control fluid flow through the at least one internal by-pass passage.

A valve assembly includes an outer housing having a first opening in fluid communication with a first fluid, a second opening in fluid communication with a second fluid, a third opening in fluid communication with a third fluid and a fourth opening in fluid communication with a fourth fluid. The valve assembly includes a piston configured to slide within the outer housing into a first position at which the third opening is blocked from fluid communication with the fourth opening based on a fluid pressure of the first fluid being greater than a fluid pressure of the fourth fluid. The piston is further configured to slide within the outer housing into a second position at which the third opening is in fluid communication with the fourth opening based on the fluid pressure of the second fluid being greater than the fluid pressure of the fourth fluid.

A waste gate valve actuator, that may be used for an exhaust gas turbocharger of a motor vehicle, may have a flap with a base surface to be supported on an edge of an inlet or outlet opening of a waste gate channel and a channel-side elevation, which at least in one cross section along its axial direction exhibits an outer contour with a first section and an adjoining section facing away from the base surface. The outer contour in the first section may have at least one outer tangent that includes a first angle deviating from zero with the axial direction, and in the second section may have at least two outer tangents spaced apart from each other in an axial direction that include the same second angle angle deviating from zero and the first angle with the axial direction, and/or wherein the elevation exhibits in particular a flat front surface facing away from the base surface, which in relation to the base surface-side floor surface of the elevation is offset toward a rotational axis of the flap.

A turbocharger has an annular bypass valve disposed in an annular portion of a bypass passage of the turbine housing. The turbine housing defines an exhaust gas chamber having separate half-annular first and second scrolls, and a portion of the bypass passage is sector-divided by a pair of dividing walls that create two 180-degree bypass sectors respectively connected to the first and second scrolls. Each dividing wall has a through-hole. The valve rotor defines a pair of valve members that close the through-holes when the bypass valve is fully closed. When the valve rotor begins to rotate toward an open position, first the valve members open the through-holes to connect the two bypass sectors, and then the bypass flow passages begin to open.

A turbine frame cooling system for use with a gas turbine engine includes an outer ring defining a cavity and a hub positioned radially inward of the outer ring. The turbine frame cooling system also includes a plurality of circumferentially-spaced first fairings coupled between the outer ring and the hub and a plurality of circumferentially-spaced second fairings coupled between the outer ring and the hub, wherein the first and second fairings are alternatingly positioned about the hub. The turbine frame cooling system also includes a plurality of circumferentially-spaced air scoops coupled to the outer ring. The plurality of air scoops extend into a bypass stream and are configured to channel a bypass air cooling flow into the cavity of the outer ring.