An assembly is provided for a turbine engine. This turbine engine assembly includes a turbine engine structure and a sensor system. The sensor system includes a probe and an optical sensor. The probe is connected to the turbine engine structure. The probe projects into a gas path of the turbine engine. The sensor system is configured to measure a temperature of the probe using the optical sensor.

There is described a fixture for supporting a plurality of gas turbine engine blades that are to be imaged. The mobile fixture comprises a plurality of interconnected mounts arranged to lie within a common plane, wherein each mount comprises at least one support surface for holding a respective blade. Support surfaces of respective mounts are oriented such that their respective normal vectors have the same angle with respect to the common plane.

According to an aspect, a bowed rotor sensor system for a gas turbine engine is provided. The bowed rotor sensor system includes a bowed rotor sensor operable to transmit a sensing field in an observation region and receive a signal indicative of a gap between an air seal and a blade tip within the gas turbine engine. The bowed rotor sensor system also includes a controller operable to monitor a plurality of gap data from the bowed rotor sensor indicative of the gap between the air seal and the blade tip of a plurality of blades passing through the observation region and determine a bowed rotor status of the gas turbine engine based on the gap data.

The present application discloses a method of determining one or more fuel characteristics of an aviation fuel suitable for powering a gas turbine engine of an aircraft. The method comprises: determining, during use of the gas turbine engine, one or more exhaust content parameters by performing a sensor measurement on an exhaust of the gas turbine engine; and determining one or more fuel characteristics of the fuel based on the one or more exhaust parameters. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.

A system and method of using a tool assembly is provided. The system includes a body, a first camera and a second camera fixed to the body, and a controller. The controller is configured to receive data indicative of images of a reference feature from the first camera, determine data indicative of a first spatial position of the first camera based at least in part on the received data indicative of the images of the reference feature, and determine data indicative of a second spatial position of the second camera based on the first spatial position, a known spatial relationship between the first location and the second location, or both. Further, the controller may be configured to receive data indicative of images of a target feature using the second camera, derive dimensions of the target feature based on the images, and generate a three-dimensional representation of the target feature.

A method for creating a three-dimensional (3D) mark in a protective coating including at least one of a TBC and a bond coating over a metal part, is provided. The method may include positioning a mask over the protective coating, the mask including an opening pattern therein; and performing an abrasive waterjet process on the protective coating using the mask. The abrasive waterjet erodes a first portion of the protective coating exposed through the first opening pattern to create the 3D mark. The mask is removed, leaving the 3D mark in the protective coating. The 3D mark only partially penetrates through the protective coating. A metal part may include a metal body, a protective coating over the metal body, and the 3D mark in the protective coating, is also provided. The 3D mark in the protective coating may include an opening having a width of between 30 and 300 micrometers.

An aircraft includes a gas turbine engine and an optically-based measurement system. The gas turbine engine is configured to ingest a first mass flow and to exhaust a second mass flow. The optically-based measurement system is configured to determine the first and second mass flows in response to performing an imaging process on the gas turbine engine.

A vacuum pump is provided that can remove deposits without overhauling and also detect completion of removal of deposits. A cleaning function portion for a cleaning function that performs cleaning of a deposit in a vacuum pump and a deposition sensor for a deposition detection function that detects the deposit are provided. A reading circuit portion and a cleaning completion determination circuit portion for a cleaning completion determination function that determines completion of cleaning are provided. The cleaning completion determination circuit portion outputs a cleaning completion signal indicating completion of the cleaning, based on a detection result of the deposition sensor.

An imaging device includes a plurality of electronic components, a phase change material, and a heat transfer structure. The plurality of electronic components is configured to collect data and have a predetermined temperature parameter. The plurality of electronic components is disposed within the phase change material. The phase change material has a first material phase and a second material phase. The phase change material has a first material phase and a second material phase. The phase change material is configured to absorb heat through changing from the first material phase to the second material phase. The heat transfer structure is disposed within the phase change material. The heat transfer structure is configured to conduct heat within the phase change material. The phase change material and the heat transfer structure are further configured to regulate a temperature of the electronic components below the predetermined temperature parameter.

For alignment of rotational shafts, two devices for attachment to circular faces of two shaft segments. Each of the two devices has a laser photoelectric device for ascertaining a dimension of displacement of the two shafts from a desired axis of rotation relative to each other. Each of the two devices having a base surface with two linear contact edges designed to engage with a circumferential surface of a shaft and to ensure alignment between the device and an axis of rotation of the shaft to within a tolerance compatible with alignment tolerances of the shaft. Each of the two linear contact edges includes at least two terminal end regions and a center region together defining a line contact at linear intersection of two surfaces meeting at a non-zero angle linear contact edges designed to affix and release from the shaft surface, and to ensure parallel alignment between the device and an axis of rotation of the shaft to a precision allowing measurements to within tolerances required by machinery driven by the shaft. The base surface of at least one of the devices has been modified from its commercially-delivered condition to provide raised rails designed to improve tactile feedback of to a user of the alignment between the base and an axis of rotation of the shaft, and has affixed thereto two rails designed to improve tactile feedback of to a user of the alignment between the base and an axis of rotation of the shaft. Each base has a magnet and a switch to vary magnetic flux for affixation and release from the shaft surface. Each device has brackets designed to securely and reproducibly position laser photoelectric devices relative to the base and axis of rotation of the shaft. The attaching includes a human placing at least one of the devices slightly askew relative to the axis of rotation of the shaft, and the human gently twisting the device to allow the liner contact edges to seat on the circumferential surface of the shaft, to provide tactile feedback to the human to confirm parallel alignment between the at least one device's laser photoelectronic device and the axis of rotation of the shaft.