Abstract: An air temperature sensor with a housing having a skin with a first and second portion, a temperature sensor having at least a portion extending through the housing, a set of fluid passageways defined within an interior of the housing, and a tube to receive bleed air from an aircraft engine located within the interior and to allow hot bleed air into the set of fluid passageways.

Abstract: A separator for separating at least a part of particles from an air flow flowing inside a conduit comprises at least one separating unit. Each separating unit comprises: a protrusion, extending inwardly from an inner surface of the conduit and configured to direct at least a part of the particles towards a wall of the conduit. The separating unit further comprises a hole throughout a thickness of the wall, positioned downstream of and adjacent to the protrusion, and configured to pass the particles moving towards the wall to an outer side of the conduit.

Abstract: An air temperature sensor with a housing having a skin with a first and second portion, a temperature sensor having at least a portion extending through the housing, a set of fluid passageways defined within an interior of the housing, and a tube to receive bleed air from an aircraft engine located within the interior and to allow hot bleed air into the set of fluid passageways.

Abstract: A total air temperature sensor can include an airfoil portion. The airfoil portion can an inlet and an outlet through which a diverted airflow path can flow. The total air temperature sensor can include a temperature sensor located within a housing defining the total air temperature sensor and a sheath surrounding the temperature sensor. The temperature sensor can be configured to take a total temperature of the diverted airflow path.

Abstract: A total air temperature sensor can include a first airfoil having a heated first surface, a second airfoil having a second surface spaced from the first surface and defining a sensor chamber, a temperature sensor located within the chamber, and a sheath surrounding the temperature sensor.

Abstract: A temperature sensor assembly includes a bluff body, and a first member spaced apart from the bluff body that defines a first flow channel in relation to the bluff body. The temperature sensor assembly also includes a second member spaced apart from the bluff body that defines a second flow channel in relation to the bluff body. The first member and the second member further define a third flow channel in fluid communication with and downstream of the first flow channel and the second flow channel. The temperature sensor assembly also includes a sensor element spaced apart from the bluff body and disposed at least partially within the third flow channel.

Abstract: A temperature sensor assembly includes a body configured to receive a heated flow of air therein. The body, in turn, includes a leading surface in thermal communication with the heated flow of air, a first concave surface including a first plurality of vents, a second concave surface including a second plurality of vents, and an air injector disposed within the body. The air injector is configured to apply a suction pressure to the first plurality of vents and to the second plurality of vents.

Abstract: A hybrid variable bleed valve includes a static bleed slot disposed in a transition duct defining a flow path for a core air flow, a variable bleed valve door disposed radially outwardly of the transition duct and the static bleed slot, a radially inward bleed cavity defined radially outwardly of the transition duct and radially inward of the variable bleed valve door for collection of a plurality of particulates and a pressure recovery return duct in fluid communication with the radially inward cavity and the transition duct. The hybrid variable bleed valve apparatus operable to open and close the variable bleed valve door to a booster bleed flow, flowing radially outwardly from the static bleed slot, for extraction of the particulates and provide a pressure recovery flow into the core air flow via the pressure recovery return duct. The hybrid variable bleed valve configured for use in a gas turbine engine.

Abstract: A separator for separating at least a part of particles from an air flow flowing inside a conduit comprises at least one separating unit. Each separating unit comprises: a protrusion, extending inwardly from an inner surface of the conduit and configured to direct at least a part of the particles towards a wall of the conduit. The separating unit further comprises a hole throughout a thickness of the wall, positioned downstream of and adjacent to the protrusion, and configured to pass the particles moving towards the wall to an outer side of the conduit.

Abstract: A total air temperature sensor can include a first airfoil having a heated first surface, a second airfoil having a second surface spaced from the first surface and defining a sensor chamber, a temperature sensor located within the chamber, and a sheath surrounding the temperature sensor.

Abstract: A total air temperature sensor can include an airfoil portion. The airfoil portion can an inlet and an outlet through which a diverted airflow path can flow. The total air temperature sensor can include a temperature sensor located within a housing defining the total air temperature sensor and a sheath surrounding the temperature sensor. The temperature sensor can be configured to take a total temperature of the diverted airflow path.

Abstract: A temperature sensor assembly includes a body configured to receive a heated flow of air therein. The body, in turn, includes a leading surface in thermal communication with the heated flow of air, a first concave surface including a first plurality of vents, a second concave surface including a second plurality of vents, and an air injector disposed within the body. The air injector is configured to apply a suction pressure to the first plurality of vents and to the second plurality of vents.

Abstract: A temperature sensor assembly includes a bluff body, and a first member spaced apart from the bluff body that defines a first flow channel in relation to the bluff body. The temperature sensor assembly also includes a second member spaced apart from the bluff body that defines a second flow channel in relation to the bluff body. The first member and the second member further define a third flow channel in fluid communication with and downstream of the first flow channel and the second flow channel. The temperature sensor assembly also includes a sensor element spaced apart from the bluff body and disposed at least partially within the third flow channel.

Abstract: A system for extracting foreign matter in a gas turbine includes multiple variable bleed valve (VBV) doors disposed on the outer engine casing between a low pressure compressor and a high pressure compressor for bleeding a portion of flow from a core engine flow path into a bypass flow path. The system includes an outlet guide vane (OGV) assembly having multiple guide vanes disposed within the core flow path and multiple support struts positioned downstream from the multiple guide vanes. Each pairs of adjacent support struts comprises at least one VBV door therebetween and a section of the OGV assembly located at an upstream side of the fan hub frame before the each pairs of adjacent support struts. Each section of the OGV assembly includes a first side with one or more guide vanes with trimmed trailing edges configured for directing flow into the at least one VBV door.

Abstract: A hybrid variable bleed valve includes a static bleed slot disposed in a transition duct defining a flow path for a core air flow, a variable bleed valve door disposed radially outwardly of the transition duct and the static bleed slot, a radially inward bleed cavity defined radially outwardly of the transition duct and radially inward of the variable bleed valve door for collection of a plurality of particulates and a pressure recovery return duct in fluid communication with the radially inward cavity and the transition duct. The hybrid variable bleed valve apparatus operable to open and close the variable bleed valve door to a booster bleed flow, flowing radially outwardly from the static bleed slot, for extraction of the particulates and provide a pressure recovery flow into the core air flow via the pressure recovery return duct. The hybrid variable bleed valve configured for use in a gas turbine engine.

Abstract: A system for extracting foreign matter in a gas turbine is provided. The system includes a variable bleed valve (VBV) disposed between a booster and a high pressure compressor configured to bleed at least a first flow from a core engine flow path into a bypass flow path to extract foreign particles. The system also includes a wedge structure disposed in the core engine flowpath proximate to the variable bleed valve and configured to allow the at least first flow into the bypass flow path through an extraction passage or at least a second flow through a recovery passage into the core engine flow path.

Abstract: A system for extracting foreign matter in a gas turbine includes multiple variable bleed valve (VBV) doors disposed on the outer engine casing between a low pressure compressor and a high pressure compressor for bleeding a portion of flow from a core engine flow path into a bypass flow path. The system includes an outlet guide vane (OGV) assembly having multiple guide vanes disposed within the core flow path and multiple support struts positioned downstream from the multiple guide vanes. Each pairs of adjacent support struts comprises at least one VBV door therebetween and a section of the OGV assembly located at an upstream side of the fan hub frame before the each pairs of adjacent support struts. Each section of the OGV assembly includes a first side with one or more guide vanes with trimmed trailing edges configured for directing flow into the at least one VBV door.

Abstract: An engine strut for providing fan hub frame structural support and monitoring an air flow within an aircraft engine includes an airfoil coupled to the aircraft engine and has a first portion and a second portion. The first portion is positioned upstream of the second portion with respect to the air flow. A shield is coupled to the engine and positioned between the first portion and the second portion. The shield includes a first side spaced from the first portion and defining a first flow path with the first portion. The shield further includes a second side spaced from the second portion and defining a second flow path with the second portion. At least one sensor is coupled to the aircraft engine and positioned in flow communication with the second flow path.