Abstract: An inlet particle separator system for an engine includes a hub section, a shroud section, a splitter, and a plasma flow control actuator. The shroud section surrounds at least a portion of the hub section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The plasma flow control actuator is coupled to the hub section and is disposed between the air inlet and the splitter.

Abstract: An inlet particle separator system for an engine includes an inner flowpath section, an outer flowpath section, a splitter, a first electrostatic discharge device, and a second electrostatic discharge device. The outer flowpath section surrounds at least a portion of the inner flowpath section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The first electrostatic charge device is disposed between the air inlet and the splitter and is electrostatically charged to a first polarity. The second electrostatic charge device is disposed downstream of the first electrostatic charge device and is electrostatically charged to a second polarity that is opposite to the first polarity.

Abstract: A system for directing airflow, a gas turbine engine, and a method for directing airflow exiting a cascade of internal airfoils are provided. An exemplary method for directing airflow exiting a cascade of internal airfoils includes coupling a first plasma generating device on a first surface and a rounded trailing edge of each of the internal airfoils. The method also includes coupling a second plasma generating device on an opposite second surface and the rounded trailing edge of each of the internal airfoils. Further, the method includes selectively energizing the first plasma generating device and the second plasma generating device on each of the internal airfoils to produce a plasma and to selectively alter a direction of local airflow around each of the internal airfoils to produce a combined airflow exiting the cascade in a desired direction.

Abstract: Multistage gas turbine engine (GTE) compressors having optimized stall enhancement feature (SEF) configurations are provided, as are methods for the production thereof. The multistage GTE compressor includes a series of axial compressor stages each containing a rotor mounted to a shaft of a gas turbine engine. In one embodiment, the method includes the steps or processes of selecting a plurality of engine speeds distributed across an operational speed range of the gas turbine engine, identifying one or more stall limiting rotors at each of the selected engine speeds, establishing an SEF configuration in which SEFs are integrated into the multistage GTE compressor at selected locations corresponding to the stall limiting rotors, and producing the multistage GTE compressor in accordance with the optimized SEF configuration.

Abstract: The present disclosure provides systems and apparatuses for use in turbine systems that integrate structural frame elements into a variable-vectoring flow control configuration in order to reduce the weight and length of such turbine systems. In one exemplary embodiment, an apparatus for directing a gas flow includes an annular outer structural casing, an annular central hub disposed within the outer structural casing, and a plurality of structural support elements extending radially between the central hub and the outer structural casing. The apparatus further includes a plurality of positionally-fixed, variable-vectoring flow control bodies extending radially between the central hub and the outer structural casing and positioned circumferentially along the central hub between ones of the plurality of structural support elements.

Abstract: An inlet particle separator system for an engine includes an inner flowpath section, an outer flowpath section, a splitter, a first electrostatic discharge device, and a second electrostatic discharge device. The outer flowpath section surrounds at least a portion of the inner flowpath section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The first electrostatic charge device is disposed between the air inlet and the splitter and is electrostatically charged to a first polarity. The second electrostatic charge device is disposed downstream of the first electrostatic charge device and is electrostatically charged to a second polarity that is opposite to the first polarity.

Abstract: An inlet particle separator system for an engine includes a hub section, a shroud section, a splitter, and a plasma flow control actuator. The shroud section surrounds at least a portion of the hub section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The plasma flow control actuator is coupled to the hub section and is disposed between the air inlet and the splitter.

Abstract: A diffuser system for a compressor for a gas turbine engine, the compressor having an impeller and the gas turbine engine having a combustor and a fuel injector proximate to the combustor, includes a first diffuser and a second diffuser. The first diffuser is configured to receive compressed air from the impeller. The second diffuser is coupled to receive the compressed air from the first diffuser. The second diffuser comprises a housing comprising a first wall and a second wall. The first and second walls form a diffuser flow passage therebetween. The first wall or the second wall, or both, further form an opening through the first and second walls for the fuel injector to pass through when removed from the combustor.

Abstract: Gas turbine engines and methods for cooling components thereof with mid-impeller bleed (MIB) cooling air having a pressure are provided. The gas turbine engine has a compressor comprising an impeller body and an impeller shroud at least partially surrounding the impeller body. The impeller shroud has a plurality of MIB openings disposed therein. At least one edge treatment is provided thereto. The edge treatment substantially preserves pressure of the cooling air during entrance into and discharge out of the MIB opening. The plurality of MIB openings may be extended MIB openings in a thickened impeller shroud. The centerline of the MIB openings may be oriented to be substantially aligned with an averaged local absolute flow velocity vector of the cooling air at the inlet section of the MIB opening in order to extract cooling air in a direction that has a vector component in a tangential, an axial, and a radial flow direction.

Abstract: A compressor includes a rotor platform; a rotor blade; and a casing having an inner surface surrounding the tip and spaced radially outwardly from the tip to define a gap. A secondary air flow system includes a bleed inlet configured to remove secondary air flow from the primary air flow; an injection opening disposed in the inner surface of the casing upstream of the bleed inlet; an accessory conduit; and a plenum fluidly coupled to the bleed inlet, the injection opening, and the accessory conduit. The bleed inlet and plenum at least partially define a secondary air flow path such that a first portion of the secondary air flow is directed in through the bleed inlet, through the plenum, and out through the injection opening and a second portion of the secondary air flow is directed in through the bleed inlet, through the plenum, and out through the accessory conduit.

Abstract: A compressor includes a housing, a rotor, an impeller, and a ported shroud. The rotor is mounted within the housing, and has a first leading edge and a first trailing edge. The rotor is operable, upon rotation thereof, to compress air and to discharge the air in an approximately axial direction. The impeller is mounted within the housing, and has a second leading edge and a second trailing edge. The impeller is operable, upon rotation thereof, to receive the air discharged from the rotor, to further compress the air, and to discharge the air in an approximately radial direction. The shroud at least partially surrounds the impeller. The shroud has an opening therein to at least facilitate allowing the air to travel upstream of the opening.

Abstract: A compressor includes a diffuser, a recirculation duct, and a flow control valve. The recirculation duct has an inlet in fluid communication with the air outlet of the diffuser, and an outlet in fluid communication with the air inlet of the diffuser. The flow control valve is selectively moveable between open and closed positions, to thereby fluidly couple and isolate, respectively, the recirculation duct inlet and outlets. During operation of the compressor, the flow control valve may be opened, which circulates a portion of the compressed air discharged from the diffuser air outlet back to the diffuser air inlet. The air that is circulated back to the diffuser air inlet reduces the effective area of the diffuser air inlet, thereby increasing the surge margin of the compressor.

Abstract: A diffuser is provided that includes a first wall, a second wall, and a first plasma actuator. The first wall has a radially-extending section and a curved section. The second wall has a radially-extending section and a curved section that are spaced apart from the radially-extending section and the curved section of the first wall such that the curved section of the second wall is disposed radially inwardly from the curved section of the first wall and a flow path is defined therebetween. The first plasma actuator is disposed on the curved section of the second wall, and the first plasma actuator is adapted to generate a first electric field to ionize a first portion of air flowing along the flow path to form a plurality of ionized species capable of inducing a second portion of air to flow in a desired direction.

Abstract: A diffuser system for a compressor for a gas turbine engine includes a diffuser and a plasma actuator. The diffuser comprises a first wall and a second wall. The first and second walls form a diffuser flow passage therebetween. The plasma actuator is disposed at least partially proximate the second wall. The plasma actuator is adapted to generate an electric field to ionize a portion of air flowing through the flow passage.

Abstract: A housing is incorporated as part of a compressor having blades that impart to a fluid a momentum along a main gas flow direction and a swirl. The housing includes a channel that has at least one channel wall and defines an axis substantially aligned with the main gas flow direction. The channel is configured to duct at least some of the fluid. The channel wall defines an internal cavity that extends axially within the channel wall. A bleed passage connects and provides fluid communication between the channel and the cavity. The channel wall defines a plurality of injection passages providing fluid communication between the cavity and the channel at a location spaced in a direction opposite the main gas flow direction from both the bleed passage and the blades. The injection passages have a portion configured to direct fluid from the cavity into the channel with a component along the main gas flow direction and a component opposed to the swirl.

Abstract: A diffuser system for a compressor for a gas turbine engine includes a diffuser and a plasma actuator. The diffuser comprises a first wall and a second wall. The first and second walls form a diffuser flow passage therebetween. The plasma actuator is disposed at least partially proximate the second wall. The plasma actuator is adapted to generate an electric field to ionize a portion of air flowing through the flow passage.

Abstract: A compressor includes a housing, a rotor, an impeller, and a ported shroud. The rotor is mounted within the housing, and has a first leading edge and a first trailing edge. The rotor is operable, upon rotation thereof, to compress air and to discharge the air in an approximately axial direction. The impeller is mounted within the housing, and has a second leading edge and a second trailing edge. The impeller is operable, upon rotation thereof, to receive the air discharged from the rotor, to further compress the air, and to discharge the air in an approximately radial direction. The shroud at least partially surrounds the impeller. The shroud has an opening therein to at least facilitate allowing the air to travel upstream of the opening.

Abstract: A diffuser system for a compressor for a gas turbine engine, the compressor having an impeller and the gas turbine engine having a combustor and a fuel injector proximate to the combustor, includes a first diffuser and a second diffuser. The first diffuser is configured to receive compressed air from the impeller. The second diffuser is coupled to receive the compressed air from the first diffuser. The second diffuser comprises a housing comprising a first wall and a second wall. The first and second walls form a diffuser flow passage therebetween. The first wall or the second wall, or both, further form an opening through the first and second walls for the fuel injector to pass through when removed from the combustor.

Abstract: A diffuser is provided that includes a first wall, a second wall, and a first plasma actuator. The first wall has a radially-extending section and a curved section. The second wall has a radially-extending section and a curved section that are spaced apart from the radially-extending section and the curved section of the first wall such that the curved section of the second wall is disposed radially inwardly from the curved section of the first wall and a flow path is defined therebetween. The first plasma actuator is disposed on the curved section of the second wall, and the first plasma actuator is adapted to generate a first electric field to ionize a first portion of air flowing along the flow path to form a plurality of ionized species capable of inducing a second portion of air to flow in a desired direction.

Abstract: A nonlinearly stacked low noise turbofan stator vane having a characteristic curve that is characterized by a nonlinear sweep and a nonlinear lean is provided. The stator is in an axial fan or compressor turbomachinery stage that is comprised of a collection of vanes whose highly three-dimensional shape is selected to reduce rotor-stator and rotor-strut interaction noise while maintaining the aerodynamic and mechanical performance of the vane.