Abstract: A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.

Abstract: A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.

Abstract: A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.

Abstract: A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.

Abstract: Embodiments of a turbomachine, such as a gas turbine engine, are provided. In one embodiment, the turbomachine includes an impeller, a main intake plenum in fluid communication with the inlet of the impeller, and an impeller shroud recirculation system. The impeller shroud recirculation system includes an impeller shroud extending around at least a portion of the impeller and having a shroud port therein. A shroud port cover circumscribes at least a portion of the shroud port and cooperates therewith to at least partially define an impeller recirculation flow path. The impeller recirculation flow path has an outlet positioned to discharge airflow into the main intake plenum at a location radially outboard of the shroud port when pressurized air flows from the impeller, through the shroud port, and into the impeller recirculation flow path during operation of the turbomachine.

Abstract: Embodiments of a Gas Turbine Engine (“GTE”) are provided, as are embodiments of a plasma flow-controlled intake system for deployment on a GTE. In one embodiment, the GTE includes a turbine section, a combustion section upstream of the turbine section, a compressor section upstream of the combustion section, and intake section upstream of the compressor section. The intake section includes a plenum, a first inlet fluidly coupled to the plenum, and a flow-obstructing structure projecting into the plenum and having an outer surface impinged by the airflow directed into the plenum through the first inlet during operation of the GTE. A first array of plasma actuators is disposed on flow-obstructing structure and, when activated, suppresses vortex shedding of the air flowing over the outer surface of the flow-obstructing structure.

Abstract: Embodiments of a gas turbine engine cooling system for deployment within a gas turbine engine are provided, as are embodiment of a method for producing a gas turbine engine cooling system. In one embodiment, the gas turbine engine cooling system includes an impeller having a hub, a plurality of hub bleed air passages, and a central bleed air conduit. The plurality of hub bleed air passages each have an inlet formed in an outer circumferential surface of the hub and an outlet formed in an inner circumferential surface of the hub. The central bleed air conduit is fluidly coupled to the outlets of the plurality of hub bleed air passages and is configured to conduct bleed air discharged by the plurality of hub bleed air passages to a section of the gas turbine engine downstream of the impeller to provide cooling air thereto.

Abstract: Embodiments of a Gas Turbine Engine (“GTE”) are provided, as are embodiments of a plasma flow-controlled intake system for deployment on a GTE. In one embodiment, the GTE includes a turbine section, a combustion section upstream of the turbine section, a compressor section upstream of the combustion section, and intake section upstream of the compressor section. The intake section includes a plenum, a first inlet fluidly coupled to the plenum, and a flow-obstructing structure projecting into the plenum and having an outer surface impinged by the airflow directed into the plenum through the first inlet during operation of the GTE. A first array of plasma actuators is disposed on flow-obstructing structure and, when activated, suppresses vortex shedding of the air flowing over the outer surface of the flow-obstructing structure.

Abstract: Embodiments of a turbomachine, such as a gas turbine engine, are provided. In one embodiment, the turbomachine includes an impeller, a main intake plenum in fluid communication with the inlet of the impeller, and an impeller shroud recirculation system. The impeller shroud recirculation system includes an impeller shroud extending around at least a portion of the impeller and having a shroud port therein. A shroud port cover circumscribes at least a portion of the shroud port and cooperates therewith to at least partially define an impeller recirculation flow path. The impeller recirculation flow path has an outlet positioned to discharge airflow into the main intake plenum at a location radially outboard of the shroud port when pressurized air flows from the impeller, through the shroud port, and into the impeller recirculation flow path during operation of the turbomachine.

Abstract: A flow discouraging system includes a stator assembly, a rotor assembly, and a plurality of fingers. The stator assembly includes one or more stationary components forming a side wall, the side wall including an annular groove defined by an outer axially-extending surface, an inner axially-extending surface, and a radial surface extending between the outer and inner axially-extending surfaces. The rotor assembly is disposed adjacent to and spaced apart from the stator assembly to form a portion of a cavity and includes an annular rim extending at least partially into the annular groove. The plurality of fingers is disposed in the annular groove and extends from the one or more stationary components the annular rim.

Abstract: Embodiments of a gas turbine engine cooling system for deployment within a gas turbine engine are provided, as are embodiment of a method for producing a gas turbine engine cooling system. In one embodiment, the gas turbine engine cooling system includes an impeller having a hub, a plurality of hub bleed air passages, and a central bleed air conduit. The plurality of hub bleed air passages each have an inlet formed in an outer circumferential surface of the hub and an outlet formed in an inner circumferential surface of the hub. The central bleed air conduit is fluidly coupled to the outlets of the plurality of hub bleed air passages and is configured to conduct bleed air discharged by the plurality of hub bleed air passages to a section of the gas turbine engine downstream of the impeller to provide cooling air thereto.

Abstract: Embodiments of a multi-piece centrifugal impeller are provided, as are embodiments of a method for manufacturing a multi-piece centrifugal impeller. In one embodiment, the centrifugal impeller includes an inducer piece and an exducer piece. The inducer piece includes, in turn, an inducer hub and a plurality of forward blade segments, which extend radially outward from the inducer hub. The exducer piece includes an exducer hub, which is positioned axially adjacent the inducer hub, and a plurality of aft blade segments, which extending outward from the exducer hub. The plurality of aft blade segments interlock with the plurality of forward blade segments to form a plurality of contiguous blade structures, which extend from a forward portion of the inducer hub to an aft portion of the exducer hub.

Abstract: A flow discouraging system includes a stator assembly, fins, and a rotor assembly. The stator assembly includes stationary components forming a side wall including an annular groove defined by an outer axially-extending surface, an inner axially-extending surface, and a radial surface. One or more outer axial fins disposed in the annular groove extend along the outer axially-extending surface of the side wall. One or more inner axial fins disposed in the annular groove extend along the inner axially-extending surface of the side wall. One or more radial fins disposed in the annular groove extend axially from the radial surface of the side wall. The rotor assembly is disposed adjacent to and is spaced apart from the stator assembly to form a portion of a cavity and includes an annular rim extending at least partially into the annular groove and disposed between the outer and inner axial fins.

Abstract: A flow discouraging system includes a stator assembly, a rotor assembly, and a plurality of fingers. The stator assembly includes one or more stationary components forming a side wall, the side wall including an annular groove defined by an outer axially-extending surface, an inner axially-extending surface, and a radial surface extending between the outer and inner axially-extending surfaces. The rotor assembly is disposed adjacent to and spaced apart from the stator assembly to form a portion of a cavity and includes an annular rim extending at least partially into the annular groove. The plurality of fingers is disposed in the annular groove and extends from the one or more stationary components the annular rim.

Abstract: A flow discouraging system includes a stator assembly, fins, and a rotor assembly. The stator assembly includes stationary components forming a side wall including an annular groove defined by an outer axially-extending surface, an inner axially-extending surface, and a radial surface. One or more outer axial fins disposed in the annular groove extend along the outer axially-extending surface of the side wall. One or more inner axial fins disposed in the annular groove extend along the inner axially-extending surface of the side wall. One or more radial fins disposed in the annular groove extend axially from the radial surface of the side wall. The rotor assembly is disposed adjacent to and is spaced apart from the stator assembly to form a portion of a cavity and includes an annular rim extending at least partially into the annular groove and disposed between the outer and inner axial fins.

Abstract: A compressor includes an enhanced vaned shroud and is configured such that the flow area ratio is equivalent to that of a conventional, non-vaned shroud. The vaned shroud includes a plurality of airfoils that vary in thickness to obtain desired vibrational mode shapes and natural frequencies. A stiffening ring of limited axial extent is coupled to, and between, the airfoils, and the shroud is manufactured with a section of constant radius.