A method of maintaining at least one gas turbine engine includes monitoring a compressor of the gas turbine engine. The compressor includes a compressor case at least partially defining a flow path, a plurality of stages and a vane actuator system configured to move at least one of the stages. The vane actuator system includes a vane mover having one or more slots formed therein and configured to actuate the at least one stage. The vane mover may be replaced after the gas turbine engine has experienced engine degradation.

A tool for performing inspection and/or maintenance operations on an engine defines a longitudinal direction and a tangential direction. The tool includes a base extending along the longitudinal direction and including a body, a first extension member extending from the body in the tangential direction at a first location, and a second extension member extending from the body in the tangential direction at a second location. The second location is spaced from the first location along the longitudinal direction. The tool also includes a pivot member rotatably coupled to the base and moveable between an insertion position in which the pivot member is oriented generally along the longitudinal direction and a deployed position in which the pivot member is oriented away from the longitudinal direction.

A method for inspecting an object includes receiving or determining inspection image data, the inspection image data including an inspection image pixel array with at least one inspection image pixel in the inspection image pixel array having a pixel property associated therewith. The method includes receiving via a processor a user input associated with a continuous segment of inspection image pixels in the inspection image pixel array. The method includes determining a property of the object based on the pixel properties associated with the continuous segment of inspection image pixels in the inspection image pixel array.

A system including: a journal bearing having a carrier, a rotor arranged rotatable about a rotational axis relative to the carrier, and a fluid in a clearance between the rotor and the carrier. A sensor measures a vibration signal of the rotor. A control system is adapted to determine a pressure set point for the fluid in the clearance based on the vibration signal, and to provide control signals generated based on the pressure set point. An active device is adapted to modify the pressure of the fluid in the clearance based on the control signals.

A method is provided including the steps: —first excitation of the object via a multifrequency signal; —detecting a first response signal of the object at one or multiple measuring points at the object; —transforming the first response signal from a time range into a frequency-dependent range; —selecting one or multiple frequencies, based on the frequency-dependent range; —second excitation of the object based on the selected frequencies; —detecting a second response signal of the object at one or multiple measuring points of the object; —ascertaining a mechanical parameter based on the second response signal.

An acquisition unit acquires a bundle of detection values for each of a plurality of sensor values pertaining to a plant. A distance calculation unit obtains the Mahalanobis distance of the bundle of detection values acquired by the acquisition unit using, as reference, a unit space constituted by a collection of bundles of detection values for each of the plurality of sensor values. A determining unit determines, based on whether the Mahalanobis distance is at or within a prescribed threshold, whether the operation state of the plant is normal or abnormal. A trend specification unit specifies a trend with regards to at least one sensor value. An abnormality cause estimation unit estimates an abnormality cause based on the trend for the sensor value(s), and a fault site estimation database for holding the relationship between abnormality causes that may occur in the plant and sensor values for each of the trends.

A measuring device with at least one fluid channel for conveying a measuring fluid, wherein the fluid channel includes at least one inlet for the entry of the measuring fluid into the fluid channel and at least one outlet for the exit of the measuring fluid from the fluid channel. The fluid channel includes a diamond-shaped cross-section and includes a course from the at least one inlet to the at least one outlet over which the measuring fluid entering the fluid channel is deflected by at least 90° before the measuring fluid exits the fluid channel at the at least one outlet.

A communication adapter of a gas turbine engine of an aircraft includes a housing configured to be coupled to the gas turbine engine, a plurality of antennas integrated in the housing, a memory system and processing circuitry. The processing circuitry is configured to establish communication with an engine control mounted on the gas turbine engine, establish wireless communication between the communication adapter and an offboard system external to the aircraft through at least one of the antennas integrated in the housing of the communication adapter, and authenticate communication requests at the communication adapter for data sent between the offboard system and the engine control.

A selectively flexible extension tool includes: a line assembly comprising a first line and a second line; and a plurality of sequentially arranged links, the line assembly operable with the plurality of sequentially arranged links to move the plurality of sequentially arranged links between a slacked position and a tensioned position, the plurality of sequentially arranged links together comprising a first line guide and a second line guide, the first line of the line assembly extending through the first line guide and the second line of the line assembly extending through the second line guide; wherein the first line defines a first displacement when the plurality of sequentially arranged links are moved from the slacked position to the tensioned position, wherein the second line defines a second displacement when the plurality of sequentially arranged links are moved from the slacked position to the tensioned position, and wherein the first displacement is substantially equal to the second displacement.

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.