Abstract: A ported shroud for a compressor associated with a gas turbine engine includes a primary inlet configured to be in fluid communication with the compressor, and the primary inlet is defined to extend along a central axis of the ported shroud. The ported shroud includes a bellmouth that surrounds the primary inlet, and a port plenum configured to be in fluid communication with the compressor. The port plenum extends along an axis that is transverse to the central axis of the ported shroud and transverse to a direction of fluid flow. The port plenum has a port plenum inlet defined about the axis, and the port plenum inlet is defined through the bellmouth such that a tortuous path is defined to the port plenum inlet. The port plenum including a port plenum outlet downstream from the port plenum inlet configured to be in fluid communication with the compressor.

Abstract: A thermally isolated sensor associated with a gas turbine engine includes a sensor probe configured to measure a temperature of a fluid associated with the gas turbine engine, and a base to be coupled to the gas turbine engine. The thermally isolated sensor includes a leading projection coupled to the base that extends into the fluid. The leading projection is configured to be heated by a heat source associated with the gas turbine engine. The thermally isolated sensor includes a trailing projection coupled to the base that extends into the fluid. The trailing projection is downstream from the leading projection. The trailing projection includes an inlet, and the sensor probe is disposed within the inlet and thermally isolated from the leading projection.

Abstract: An ejector driven scavenge system for a particle separator having a scavenge branch associated with a gas turbine engine includes at least one anti-icing circuit to receive an anti-icing fluid. The at least one anti-icing circuit is to be coupled to the particle separator. The ejector driven scavenge system includes at least one flow ejector bank to be coupled to the scavenge branch and fluidly coupled to the anti-icing fluid to direct the anti-icing fluid through the scavenge branch to drive air with entrained particles and water droplets from the particle separator.

Abstract: A thermally isolated sensor associated with a gas turbine engine includes a sensor probe configured to measure a temperature of a fluid associated with the gas turbine engine, and a base to be coupled to the gas turbine engine. The thermally isolated sensor includes a leading projection coupled to the base that extends into the fluid. The leading projection is configured to be heated by a heat source associated with the gas turbine engine. The thermally isolated sensor includes a trailing projection coupled to the base that extends into the fluid. The trailing projection is downstream from the leading projection. The trailing projection includes an inlet, and the sensor probe is disposed within the inlet and thermally isolated from the leading projection.

Abstract: A ported shroud for a compressor associated with a gas turbine engine includes a primary inlet configured to be in fluid communication with the compressor, and the primary inlet is defined to extend along a central axis of the ported shroud. The ported shroud includes a bellmouth that surrounds the primary inlet, and a port plenum configured to be in fluid communication with the compressor. The port plenum extends along an axis that is transverse to the central axis of the ported shroud and transverse to a direction of fluid flow. The port plenum has a port plenum inlet defined about the axis, and the port plenum inlet is defined through the bellmouth such that a tortuous path is defined to the port plenum inlet. The port plenum including a port plenum outlet downstream from the port plenum inlet configured to be in fluid communication with the compressor.

Abstract: A thrust reverser system includes at least one hinge coupled to the thrust reverser system so as to be adjacent to at least one opening defined in the thrust reverser system. The thrust reverser system includes at least one body coupled to the at least one hinge. The at least one body has a first body end and an opposing second body end. The body pivotally coupled to the hinge such that a portion of the body is positionable within the at least one opening and the body includes at least one counterweight at the first body end or the second body end. The body is positioned within the at least one opening based on an operating condition of the gas turbine engine.

Abstract: A total air temperature (TAT) probe having a self-regulating heating system is provided. A TAT probe housing includes at least one heating cavity that is located proximate to a tip of the TAT probe. A heating element is received within the at least one heating cavity. The heating element is composed from a flexible material with a very high positive temperature coefficient (PTC) that provides non-linear resistance with temperature with generally relatively low electrical resistances at temperatures below freezing and relatively high electrical resistances above freezing. A power source is coupled to the heating element. The very high PTC material of the heating element causes less power to be drawn by the heating element from the power source at higher temperatures above freezing than the power drawn by the heating element from the power source at lower temperatures below freezing to maintain a desired temperature of the TAT probe.

Abstract: A thrust reverser system for a gas turbine engine includes at least one hinge coupled to the thrust reverser system so as to be adjacent to at least one opening defined in the thrust reverser system. The thrust reverser system includes at least one body coupled to the at least one hinge. The at least one body has a first body end and an opposing second body end. The body pivotally coupled to the hinge such that a portion of the body is positionable within the at least one opening and the body includes at least one counterweight at the first body end or the second body end. The body is positioned within the at least one opening based on an operating condition of the gas turbine engine.

Abstract: A thrust reverser system comprising a single row vane assembly is provided. The provided thrust reverser system is capable of meeting performance requirements for turbine engines with reduced weight and cost.

Abstract: A total air temperature (TAT) probe having a self-regulating heating system is provided. A TAT probe housing includes at least one heating cavity that is located proximate to a tip of the TAT probe. A heating element is received within the at least one heating cavity. The heating element is composed from a flexible material with a very high positive temperature coefficient (PTC) that provides non-linear resistance with temperature with generally relatively low electrical resistances at temperatures below freezing and relatively high electrical resistances above freezing. A power source is coupled to the heating element. The very high PTC material of the heating element causes less power to be drawn by the heating element from the power source at higher temperatures above freezing than the power drawn by the heating element from the power source at lower temperatures below freezing to maintain a desired temperature of the TAT probe.

Abstract: A thrust reverser system for a gas turbine engine includes at least one hinge coupled to the thrust reverser system so as to be adjacent to at least one opening defined in the thrust reverser system. The thrust reverser system includes at least one body coupled to the at least one hinge. The at least one body has a first body end and an opposing second body end. The body pivotally coupled to the hinge such that a portion of the body is positionable within the at least one opening and the body includes at least one counterweight at the first body end or the second body end. The body is positioned within the at least one opening based on an operating condition of the gas turbine engine.

Abstract: A thrust reverser system having an asymmetric vane assembly is provided. The provided thrust reverser system generates a desired vertical thrust component that at least partially offsets a potential nose-up pitch moment. The provided thrust reverser system employs a single row asymmetric vane geometry that reduces weight and material cost.

Abstract: An anti-icing exhaust system for an inlet of a gas turbine engine is provided. The system includes a first housing portion that at least partially defines a chamber to receive an anti-icing fluid and includes a projection. A second housing portion includes a leading edge. The system includes a support structure that couples the first housing portion to the second housing portion such that the projection of the first housing portion is spaced apart from the leading edge of the second housing portion to define a gap. The gap is in fluid communication with a manifold. The support structure defines at least one flow passage in fluid communication with the chamber and the manifold to exhaust the fluid. The system includes an insulation strip having a first end received in the gap and coupled to the leading edge; and a second end coupled to the second housing portion.

Abstract: Plenums for bifurcated ducts and bifurcated ducts are provided for stabilizing flow therethrough. The plenum comprises an outer cylindrical body intersected by a pair of exhaust duct stubs that are configured to be coupled to a corresponding pair of exhaust ducts and an inner body. The outer cylindrical body includes an axial rear end portion. The inner body is disposed in the axial rear end portion and increases in diameter in the aft direction. The inner body comprises one of a generally axi-symmetrical inner body or a non-axi-symmetrical inner body. The bifurcated duct comprises the plenum and the pair of exhaust ducts. Exhaust systems are also provided.

Abstract: An anti-icing system is provided for an inlet lip annularly extending about a nacelle of an aircraft engine assembly. The anti-icing system includes an interior wall structure at least partially forming an annular anti-icing chamber with the inlet lip and an annular shield with a first end coupled to the interior wall structure and a second end extending into the annular anti-icing chamber. The annular shield divides the annular anti-icing chamber into first and second chamber portions fluidly coupled together by a passage formed between the second end and the internal surface of the inlet lip. The anti-icing system further includes a nozzle at an inwardly radial position relative to the first end of the annular shield such that the heated air exits the nozzle into the first chamber portion in which the annular shield blocks direct impingement on the internal surface of the inlet lip.

Abstract: An anti-icing exhaust system for an inlet of a gas turbine engine is provided. The system includes a first housing portion that at least partially defines a chamber to receive an anti-icing fluid and includes a projection. A second housing portion includes a leading edge. The system includes a support structure that couples the first housing portion to the second housing portion such that the projection of the first housing portion is spaced apart from the leading edge of the second housing portion to define a gap. The gap is in fluid communication with a manifold. The support structure defines at least one flow passage in fluid communication with the chamber and the manifold to exhaust the fluid. The system includes an insulation strip having a first end received in the gap and coupled to the leading edge; and a second end coupled to the second housing portion.

Abstract: An air data probe comprises an elongated body structure having a proximal end and a distal end, with the elongated body structure including an outer surface and an opposing inner surface that defines an interior channel. A probe tip is located at the distal end of the elongated body structure, with the probe tip including an outer surface and an inner surface that are contiguous with the outer an inner surfaces of the elongated body structure. The probe tip has an opening in communication with the interior channel that allows outside air to pass from the probe tip into the interior channel. An electrical heater cable is coupled to the elongated body structure and the probe tip. The electrical heater cable comprises a compact double layer helix portion coupled to the elongated body structure or the probe tip, or coupled to both the elongated body structure and the probe tip.

Abstract: An air data probe includes a probe body. The air data probe also includes a housing surrounding the probe body, wherein a cavity is defined between the probe body and the housing. The air data probe also includes a heater element disposed within the cavity between the probe body and the housing. The air data probe also includes a low melting point metal disposed within the cavity between the probe body and the housing, wherein engaging the heater element causes at least a portion of the low melting point metal to transition from a solid state to a liquid state.

Abstract: An anti-icing system is provided for an inlet lip annularly extending about a nacelle of an aircraft engine assembly. The anti-icing system includes an interior wall structure at least partially forming an annular anti-icing chamber with the inlet lip and an annular shield with a first end coupled to the interior wall structure and a second end extending into the annular anti-icing chamber. The annular shield divides the annular anti-icing chamber into first and second chamber portions fluidly coupled together by a passage formed between the second end and the internal surface of the inlet lip. The anti-icing system further includes a nozzle at an inwardly radial position relative to the first end of the annular shield such that the heated air exits the nozzle into the first chamber portion in which the annular shield blocks direct impingement on the internal surface of the inlet lip.

Abstract: A thrust reverser system having an asymmetric vane assembly is provided. The provided thrust reverser system generates a desired vertical thrust component that at least partially offsets a potential nose-up pitch moment. The provided thrust reverser system employs a single row asymmetric vane geometry that reduces weight and material cost.