Abstract: A nozzle assembly of a turbocharger includes a nozzle and a ring-shaped body. The nozzle has flow passages extending through the nozzle and configured to direct air received from a volute housing of the turbocharger through the nozzle to turbine blades of the turbocharger. The ring-shaped body is coupled with the nozzle and is configured to rotate around the nozzle. The ring-shaped body includes blocking segments that block the flow of the air and openings between the blocking segments that permit the air to flow through the ring-shaped body. The ring-shaped body is configured to rotate relative to the nozzle to change how many of the flow passages in the nozzle are blocked by the blocking segments of the ring-shaped body.

Abstract: Centrifugal compressor having flow-control blades in which each of the flow-control blades has a pressure side and an opposite suction side. Each of the flow-control blades includes a main section and an inducer section that project away from an impeller surface. The inducer section is positioned upstream from the main section. The inducer section includes a trailing edge and the main section includes a leading edge that is spaced apart from the trailing edge. The inducer sections are aligned with the respective main sections as the inducer and main sections project from the impeller surface to a designated point above the impeller surface. Each of the trailing edges of the inducer sections and the respective leading edge of the main section form a bleed gap therebetween after the designated point. The bleed gap is configured to permit fluid to flow therethrough from the pressure side to the suction side.

Abstract: An aspirating seal assembly for use in a turbine engine is provided. The aspirating seal assembly includes a face seal and a rotary component. The face seal includes a first annular seal surface, and the rotary component includes a second annular seal surface positioned adjacent the first annular seal surface and defining a seal interface therebetween. The face seal is configured to discharge a flow of air towards the seal interface. The seal assembly also includes a first seal member extending between the first and second annular seal surfaces such that the flow of air induces a back pressure across the seal interface, and a second seal member positioned radially inward from the first seal member and extending between the first and second annular seal surfaces. A length of the second seal member is selected to increase the back pressure induced across the seal interface.

Abstract: A nozzle assembly of a turbocharger includes a nozzle and a ring-shaped body. The nozzle has flow passages extending through the nozzle and configured to direct air received from a volute housing of the turbocharger through the nozzle to turbine blades of the turbocharger. The ring-shaped body is coupled with the nozzle and is configured to rotate around the nozzle. The ring-shaped body includes blocking segments that block the flow of the air and openings between the blocking segments that permit the air to flow through the ring-shaped body. The ring-shaped body is configured to rotate relative to the nozzle to change how many of the flow passages in the nozzle are blocked by the blocking segments of the ring-shaped body.

Abstract: An aspirating face seal assembly for a turbo-machine including a rotor assembly having a first radially extending portion defining a rotor surface is disclosed. The aspirating face seal assembly includes a seal body including a second radially extending portion defining a bearing surface and having a plurality of return channels. The second radially extending portion is disposed in the turbo-machine such that the bearing surface is disposed facing the rotor surface. The aspirating face seal assembly further includes an annular ring including one or more openings. The annular ring is concentrically disposed on the second radially extending portion and between the rotor surface and the second radially extending portion and configured to rotate in an event of rub between the first radially extending portion and the annular ring. A turbo-machine including the aspirating face seal assembly and a method for operating an aspirating face seal are also disclosed.

Abstract: Gas bearing for an aspirating seal assembly is disclosed. The gas bearing includes a bearing body having a bearing surface. The gas bearing further includes a first through-hole disposed in the bearing body, and a plurality of second through-holes spaced apart from each other and disposed around the first through-hole. The first through-hole is characterized by a size, and a first central axis. Each second through-hole is characterized by a size, and a second central axis. The second central axis of each second through-hole in the plurality of second through-holes intersects the first central axis at an angle in a range from about 30 degrees to about 150 degrees or at an angle in a range from about ?30 degrees to about ?150 degrees. Size of at least one through-hole in the plurality of second through-holes is different from the size of the first through-hole.

Abstract: Centrifugal compressor having flow-control blades in which each of the flow-control blades has a pressure side and an opposite suction side. Each of the flow-control blades includes a main section and an inducer section that project away from an impeller surface. The inducer section is positioned upstream from the main section. The inducer section includes a trailing edge and the main section includes a leading edge that is spaced apart from the trailing edge. The inducer sections are aligned with the respective main sections as the inducer and main sections project from the impeller surface to a designated point above the impeller surface. Each of the trailing edges of the inducer sections and the respective leading edge of the main section form a bleed gap therebetween after the designated point. The bleed gap is configured to permit fluid to flow therethrough from the pressure side to the suction side.

Abstract: Gas bearing for an aspirating seal assembly is disclosed. The gas bearing includes a bearing body having a bearing surface. The gas bearing further includes a first through-hole disposed in the bearing body, and a plurality of second through-holes spaced apart from each other and disposed around the first through-hole. The first through-hole is characterized by a size, and a first central axis. Each second through-hole is characterized by a size, and a second central axis. The second central axis of each second through-hole in the plurality of second through-holes intersects the first central axis at an angle in a range from about 30 degrees to about 150 degrees or at an angle in a range from about ?30 degrees to about ?150 degrees. Size of at least one through-hole in the plurality of second through-holes is different from the size of the first through-hole.

Abstract: An aspirating seal assembly for use in a turbine engine is provided. The aspirating seal assembly includes a face seal and a rotary component. The face seal includes a first annular seal surface, and the rotary component includes a second annular seal surface positioned adjacent the first annular seal surface and defining a seal interface therebetween. The face seal is configured to discharge a flow of air towards the seal interface. The seal assembly also includes a first seal member extending between the first and second annular seal surfaces such that the flow of air induces a back pressure across the seal interface, and a second seal member positioned radially inward from the first seal member and extending between the first and second annular seal surfaces. A length of the second seal member is selected to increase the back pressure induced across the seal interface.

Abstract: The method includes moving at least one of a first support and a second support to vary a position of the plurality of main blades and tandem blades relative to each other to control one or more flow control characteristics across the turbine. The turbine includes a nozzle having the plurality of main blades and tandem blades. The plurality of main blades are coupled to the first support and the plurality of tandem blades are coupled to the second support disposed spaced apart from the first support.

Abstract: Various systems and apparatuses are provided for a fluid transfer system for an engine. In one example, a system includes a first turbine having an exit for discharging a main fluid flow and a second turbine having an inlet for receiving at least a portion of the main fluid flow. A main conduit fluidically couples the exit of the first turbine to the inlet of the second turbine. A transition conduit is coupled with the main conduit and includes a volute passageway curving around the main conduit. The volute passageway includes a slot that follows a route around the curving volute passageway and opens into an interior of the main conduit. The slot is defined at least in part by a lip and establishes a path for either a secondary fluid flow to enter the main conduit or a portion of a main fluid flow to exit the main conduit.

Abstract: Various apparatuses and systems are provided for a turbocharger. In one example, the turbocharger system includes a first turbine having an exhaust flow outlet and a second turbine having an exhaust flow inlet. The turbocharger system further includes a transition conduit fluidically coupling the outlet of the first turbine to the inlet of the second turbine, the transition conduit including an expansion region upstream of a first bend, and a bypass which routes exhaust flow around the first turbine, the bypass having an exhaust flow outlet fluidically coupled to the transition conduit downstream of the expansion region.

Abstract: An exemplary turbocharger system for an internal combustion engine is provided. The turbocharger system includes a first turbine and a second turbine. The first turbine is in fluid communication with the internal combustion engine. The first turbine receives a first portion exhaust gas discharged from the internal combustion engine and provides a first turbine exhaust gas. The second turbine is in fluid communication with the first turbine via an inter-stage channel. The inter-stage channel transports the first turbine exhaust gas from the first turbine to the second turbine. The inter-stage channel is in thermal connection with an exhaust gas recirculation channel defined between an inlet and an outlet of the internal combustion engine. The first turbine exhaust gas flowing through the inter-stage channel is capable of being heated by a second portion exhaust gas discharged from the internal combustion engine and flowing through the exhaust gas recirculation channel.

Abstract: The method includes moving at least one of a first support and a second support to vary a position of the plurality of main blades and tandem blades relative to each other to control one or more flow control characteristics across the turbine. The turbine includes a nozzle having the plurality of main blades and tandem blades. The plurality of main blades are coupled to the first support and the plurality of tandem blades are coupled to the second support disposed spaced apart from the first support.

Abstract: A brush seal assembly for turbomachinery having a rotor can include a stationary seal component, a floating seal component coupled to the stationary seal component and circumferentially angled bristles arranged in a bristle pack, disposed in the floating seal component and extended axially with respect to the rotor.

Abstract: A seal assembly for a turbomachine includes a seal ring rotatable between a first position and a second position and having a plurality of tunnels. Also included is a back ring located adjacent the seal ring and having a plurality of apertures that align with more of the plurality of tunnels of the seal ring when at the second position than at the first position. Further included is a retention piece operably connecting the seal ring and the back ring.

Abstract: Various systems and apparatuses are provided for a fluid transfer system for an engine. In one example, a system includes a first turbine having an exit for discharging a main fluid flow and a second turbine having an inlet for receiving at least a portion of the main fluid flow. A main conduit fluidically couples the exit of the first turbine to the inlet of the second turbine. A transition conduit is coupled with the main conduit and includes a volute passageway curving around the main conduit. The volute passageway includes a slot that follows a route around the curving volute passageway and opens into an interior of the main conduit. The slot is defined at least in part by a lip and establishes a path for either a secondary fluid flow to enter the main conduit or a portion of a main fluid flow to exit the main conduit.

Abstract: An exemplary turbocharger system for an internal combustion engine is provided. The turbocharger system includes a first turbine and a second turbine. The first turbine is in fluid communication with the internal combustion engine. The first turbine receives a first portion exhaust gas discharged from the internal combustion engine and provides a first turbine exhaust gas. The second turbine is in fluid communication with the first turbine via an inter-stage channel. The inter-stage channel transports the first turbine exhaust gas from the first turbine to the second turbine. The inter-stage channel is in thermal connection with an exhaust gas recirculation channel defined between an inlet and an outlet of the internal combustion engine. The first turbine exhaust gas flowing through the inter-stage channel is capable of being heated by a second portion exhaust gas discharged from the internal combustion engine and flowing through the exhaust gas recirculation channel.

Abstract: An exemplary compressor is provided. The compressor includes a plurality of blades, a hub defining a front surface and a back surface, and a first flow restriction structure provided at the back surface of the hub. The plurality of blades are arranged in a predefined manner on the front surface for receiving input air flow at a first pressure and compressing the input air flow to provide an output air flow at a second pressure higher than the first pressure. The first flow restriction member is configured for preventing at least a portion of the output air flow at the second pressure from entering into the back surface of the hub to reduce an air pressure at the back surface of the hub.

Abstract: A seal assembly for a turbomachine includes a seal ring rotatable between a first position and a second position and having a plurality of tunnels. Also included is a back ring located adjacent the seal ring and having a plurality of apertures that align with more of the plurality of tunnels of the seal ring when at the second position than at the first position. Further included is a retention piece operably connecting the seal ring and the back ring.