The present disclosure is directed to a system for bleeding air from a compressed gas path of a gas turbine engine. The system includes an impeller positioned at a downstream end of a compressor in the gas turbine engine. The impeller includes an impeller hub, an impeller arm coupled to the impeller hub, and a plurality of circumferentially spaced apart impeller vanes extending radially outwardly from the impeller arm. The impeller arm defines an impeller arm aperture extending therethrough. A vortex spoiler is positioned radially inwardly from the impeller arm and defines a vortex spoiler passage extending radially therethrough. Bleed air flows from the compressed gas path radially inwardly through both the impeller arm aperture and the vortex spoiler passage.

Sensor assemblies and methods of de-icing or preventing ice formation are provided. Compressed air may be supplied to a vortex tube. The vortex tube may separate the compressed air into a first stream and a second stream, the first stream hotter than the second stream. A sensor body may be warmed by the first stream, and the second stream may be directed away from the sensor body.

A method for abrasive flow machining includes moving an abrasive media through a high-aspect passage of a workpiece. Local pressure of the abrasive media is increased at target abrasion surfaces of the high-aspect passage using a passage geometry that is configured to direct flow of the abrasive media into the target abrasion surfaces such that the target abrasion surfaces are preferentially polished by the abrasive media over other, non-targeted surfaces of the high-aspect passage at which the flow of the abrasive media is not directed into.

A method for abrasive flow machining includes moving an abrasive media through a high-aspect passage of a workpiece. Local pressure of the abrasive media is increased at target abrasion surfaces of the high-aspect passage using a passage geometry that is configured to direct flow of the abrasive media into the target abrasion surfaces such that the target abrasion surfaces are preferentially polished by the abrasive media over other, non-targeted surfaces of the high-aspect passage at which the flow of the abrasive media is not directed into.

The present disclosure generally relates to separating solid particles from an airflow in a gas turbine engine. A separator includes a plurality of vortex chambers arranged about a longitudinal axis of the gas turbine engine, each vortex chamber having a clean air outlet at a first end, a dirty outlet at a second end, and an air inlet transverse to the vortex chamber located at the first end. The separator also includes a sealable collection chamber in fluid communication with the dirty outlet of the each of the plurality of vortex chambers.

A gas turbine engine is disclosed. The gas turbine engine includes a first rotor supporting a first plurality of circumferentially spaced rotor blades and a second rotor disposed axially downstream of the first rotor and supporting a second plurality of circumferentially spaced rotor blades, a first bore cavity between the first rotor and the second rotor, a first fluid passageway configured to provide cooled air to the first bore cavity and a first anti-vortex component positioned proximate the first bore cavity and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the first bore cavity.

A method and system for cooling an engine and/or vehicle using energy separation is disclosed herein. An energy separation device is operable for separating a compressed gaseous coolant stream into a first relatively cooler coolant flow stream and a second relatively hotter coolant flow stream. The relative cooler coolant flow stream is directed to a first region requiring increased cooling and the relative hotter coolant flow stream is directed to a second region requiring lower cooling than the first region in the engine or vehicle.

One exemplary embodiment of this disclosure relates to a gas turbine engine including a component having a body. The body includes a tortuous cooling passageway, which provides a flow path extending between an inlet in a first surface of the body and an exit in a second surface of the body.

Sensor assemblies and methods of de-icing or preventing ice formation are provided. Compressed air may be supplied to a vortex tube. The vortex tube may separate the compressed air into a first stream and a second stream, the first stream hotter than the second stream. A sensor body may be warmed by the first stream, and the second stream may be directed away from the sensor body

A cooling system is provided. The cooling system may comprise a heat exchanger and a first conduit fluidly coupled to an outlet of the heat exchanger. An annular passage may be fluidly coupled to the first conduit. A tangential onboard injector (TOBI) may be fluidly coupled to the annular passage. A gas turbine engine is also provided and may comprise a compressor, a combustor in fluid communication with the compressor, and a diffuser around the combustor and a turbine. A heat exchanger may have an inlet fluidly coupled to the diffuser. A second conduit may be fluidly coupled to an outlet of the heat exchanger. An annular passage may be fluidly coupled to the second conduit. A tangential onboard injector (TOBI) may be fluidly coupled to the annular passage.