A fan assembly includes a fan duct, an inlet fan, an outlet guide vane assembly, and a control system. The inlet fan includes fan blades adapted to rotate about a central axis to force fan exit air toward an aft end of the fan duct. The outlet guide vane assembly is located in the fan duct downstream of the inlet fan and is configured to adjust a direction of the fan exit air. The outlet guide vane assembly includes a plurality of guide vanes that extend radially relative to the central axis and are configured to rotate to a first vane-pitch angle. The control system is configured to rotate the guide vanes redirect the fan exit air, vary a pressure downstream of the fan inlet, minimize intake flow distortion experienced by the inlet fan, reduce inlet fan vibratory response and/or improve fan operability margins.

A fan assembly includes a fan duct, an inlet fan, and an outlet guide vane assembly. The inlet fan includes blades adapted to force fan exit air toward an aft end of the fan duct. The outlet guide vane assembly is located in the fan duct downstream of the inlet fan and is configured to adjust a direction of the fan exit air received from the blades. The outlet guide vane assembly includes a first plurality of vanes configured to rotate to redirect the fan exit air in a first direction, and a second plurality of vanes located downstream of the first plurality of vanes. The second plurality of vanes are configured to rotate to redirect the fan exit air flowing in the first direction in a second direction to minimize losses created by distortions in fan inlet air and created by the first vanes.

A fan assembly includes a fan duct, an inlet fan, and an outlet guide vane assembly. The inlet fan includes blades adapted to force fan exit air toward an aft end of the fan duct. The outlet guide vane assembly is located in the fan duct downstream of the inlet fan and is configured to adjust a direction of the fan exit air received from the blades. The outlet guide vane assembly includes a first plurality of vanes configured to rotate to redirect the fan exit air in a first direction, and a second plurality of vanes located downstream of the first plurality of vanes. The second plurality of vanes are configured to rotate to redirect the fan exit air flowing in the first direction in a second direction to minimize losses created by distortions in fan inlet air and created by the first vanes.

A measurement system for an aircraft gas turbine engine includes a probe and a heated-gas source in fluid communication with the pressure probe. The probe includes a probe body defining an internal cavity of the probe. The probe further includes a plurality of sensor inlet ports extending through the probe body and configured to receive a sensed fluid flow. The probe further includes a plurality of probe conduits. Each probe conduit of the plurality of probe conduits is coupled to a respective sensor inlet port of the plurality of sensor inlet ports and extending from the respective sensor inlet port to an exterior of the probe body. The heated-gas source is configured to supply a heated gas flow to one or both of: the plurality of sensor inlet ports via the plurality of probe conduits and an interior of the probe body outside of the plurality of probe conduits.

An instrumentation assembly configured to measure properties of an engine exhaust stream is disclosed in this paper. The instrumentation assembly may include an outer support ring that extends around a central axis, an inner support ring arranged radially inward of the outer support ring around the central axis, and a plurality of instrumentation rake assemblies. The plurality of instrumentation rake assemblies extends from the outer support ring to the inner support ring across an annular passageway defined between the outer support ring and the inner support ring configured to carry the engine exhaust stream.

A power-receiving-module-type telemeter transmitter of a telemeter measuring system that is provided in a rotor and that performs communication using power received from a power transmitting antenna formed in an arc shape on a stator side, includes: a plurality of power receiving modules disposed in the rotor at intervals in a circumferential direction; an OR circuit that outputs a highest voltage among voltages input from the plurality of power receiving modules; a sensor that measures a state of a monitoring target and that outputs measurement data indicating the state; and a transmitting unit that is driven by the voltage input from the OR circuit as a power source and that transmits a radio signal including the measurement data of the sensor.

According to an aspect, a waveguide system includes a first node, a second node, and a double-ridge waveguide. The double-ridge waveguide includes a metallic shell surrounding a waveguide core that forms a communication and radio frequency power transmission path in an aerospace environment. The first node is configured to propagate at least one communication channel and a radio frequency power transmission through the waveguide core to the second node during operation of the waveguide system in the aerospace environment.

The disclosure relates to a gas turbine engine and a method of controlling an upstream extent of a bow wave from an airfoil having a pressure side and a suction side in the turbine engine. In one aspect, the method includes forming a vortex at a leading edge of the airfoil.

A sign detection device is provided with a plurality of sensors, a data acquisition unit, a calculation unit, and a detection unit. The plurality of sensors are respectively disposed at a plurality of positions of a detection target to measure a physical parameter at each positions.

The data acquisition unit is configured to acquire time-series change data of the physical parameters from the plurality of sensors. The calculation unit is configured to calculate dynamic network information representing a time change of a complex network structure including a parameter indicating a correlation between the physical parameters at any two positions of the plurality of positions, on the basis of the time-series change data. The detection unit is configured to detect a sign of sudden change vibration of the detection target, on the basis of the dynamic network information.

A sign detection device is provided with a plurality of sensors, a data acquisition unit, a calculation unit, and a detection unit. The plurality of sensors are respectively disposed at a plurality of positions of a detection target to measure a physical parameter at each positions.

The data acquisition unit is configured to acquire time-series change data of the physical parameters from the plurality of sensors. The calculation unit is configured to calculate dynamic network information representing a time change of a complex network structure including a parameter indicating a correlation between the physical parameters at any two positions of the plurality of positions, on the basis of the time-series change data. The detection unit is configured to detect a sign of sudden change vibration of the detection target, on the basis of the dynamic network information.