An alignment system includes a first visual indicia and a second visual indicia disposed on a first mobile unit, and a third visual indicia and a fourth visual indicia disposed on a second mobile unit. The alignment system also includes a visual inspection area configured to enable collective viewing of the first visual indicia, the second visual indicia, the third visual indicia, and the fourth visual indicia along a single direction. The alignment system is configured to align the first mobile unit with the second mobile unit along a vertical axis, a horizontal axis, and a rotational axis to help align a rotational coupling between the first mobile unit and the second mobile unit.

A digital inspection assistant and a system and a method of using the inspection assistant as an aid during a visual inspection of a gas turbine engine are provided. In one aspect, the inspection assistant receives data that includes images captured by an optical probe installed through an access port of a gas turbine engine. The images can be still images or video of the interior of a core of the engine. A gateway can route the data to the inspection assistant. The inspection assistant can provide interactive inspection guidance to an operator and can detect component defects. The inspection assistant can provide real time defect analysis to the operator by generating an alert upon detection of a defect. The generated alert can be audible, a visual graphic presented on a display of the visual inspection, and/or some other suitable alert. The analysis results can assist the operator during inspection.

A method of turbine engine annotation includes receiving data characterizing an image and/or a video of a predetermined region of a turbine engine, the turbine engine including a plurality of blades configured to move relative to the predetermined region. A first blade of the plurality of blades is located in the predetermined region during a first time duration. The method also includes receiving data characterizing inspection parameters from a turning tool device including a motor and a motor controller and receiving turbine engine information. The motor controller is configured to rotate the plurality of blades of the turbine via the motor coupled to the turbine engine. The method further includes identifying the first blade based on the inspection parameters including an initial configuration of the turning tool device and the first time duration. The method also includes generating an annotated image and/or an annotated video, the generating including annotating at least a portion of the turbine engine information and the identity of the first blade onto the received image and/or the received video.

An insertion tool is provided for an engine defining an access opening and including a component defining at least in part a cavity. The insertion tool includes: an insertion tool arm having a plurality of segments, the insertion tool arm configured for insertion through the access opening into the cavity and the plurality of segments configured to be in a fixed position relative to one another within the cavity; and a base coupled to the insertion tool arm and configured to be positioned outside the cavity and to move the insertion tool arm along at least two degrees of freedom.

An optical monitoring system includes a controller configured to determine a predicted status of a component based on an operational time of a rotary machine and an individual model. The controller is also configured to receive a first signal indicative of an infrared spectrum image of the component from one or more cameras. Further, the controller is configured to determine a current status of the component based on the first signal and compare the current status to the predicted status of the component. Additionally, the controller is configured to update the predicted status of the component such that the predicted status matches the current status of the component and update at least one parameter of the individual model of the component based on the comparison.

A tool for inserting into a cavity is provided. The tool includes a plurality of segments moveably coupled to one another, each segment moveable relative to an adjacent segment between a bent position and a coupled position, the plurality of segments including a first segment, the first segment including: a core formed of a first material; and a shell formed of a second material and comprising or defining a guide feature, a drive feature, a line guide, or a combination thereof; wherein the first material defines a greater stiffness than the second material.

A counter-rotating turbine of an aircraft turbomachine, includes a casing including an endoscopy port configured for an endoscopy plug of a non-destructive testing device to pass into the casing. The endoscopy plug includes a mechanism for acquiring and transmitting images. The non-destructive testing device includes a mechanism for receiving and displaying images connected to the mechanism for acquiring and transmitting images by a wireless connection. First and second rotors are configured to rotate in opposite rotation directions, the second rotor having an endoscopy port in which the endoscopy plug is removably attached.

A maintenance tool for gas turbine engine includes a rail system having a plurality of rail segments insertable through one or more inspection holes of the gas turbine engine for assembly within a core air flowpath of the gas turbine engine. The maintenance tool additionally includes a maintenance head movable along the plurality of rail segments of the rail system for performing maintenance operations within the core air flowpath.

A robotic assembly configured to service an engine, wherein the robotic assembly includes an environmental capture device configured to provide information associated with an environment in which the engine is disposed to one or more computing devices, and wherein the one or more computing devices are configured to use the information to inspect the engine before and after repair operations associated with the service to check for repair equipment, or parts thereof, left in the engine after the repair.

A method of servicing aviation equipment including at least partially-autonomously inspecting components of the equipment using an environmental capture device, wherein at least partially-autonomous inspection includes: capturing information associated with the equipment using the environmental capture device; identifying the components of the equipment using one or more computing devices; determining, by the one or more computing devices, whether each identified component is properly positioned relative to the equipment using reference information; and for components not properly positioned relative to the equipment, determining if there is damage to the component or equipment.