Abstract: A method for locating probes within a gas turbine engine may generally include positioning a plurality of location transmitters relative to the engine and inserting a probe through an access port of the engine, wherein the probe includes a probe tip and a location signal receiver configured to receive location-related signals transmitted from the location transmitters. The method may also include determining a current location of the probe tip within the engine based at least in part on the location-related signals and identifying a virtual location of the probe tip within a three-dimensional model of the engine corresponding to the current location of the probe tip within the engine. Moreover, the method may include providing for display the three-dimensional model of the engine, wherein the virtual location of the probe tip is displayed as a visual indicator within the three-dimensional model.

Abstract: A method for performing a visual inspection of a gas turbine engine may generally include inserting a plurality of optical probes through a plurality of access ports of the gas turbine engine. The access ports may be spaced apart axially along a longitudinal axis of the gas turbine engine such that the optical probes provide internal views of the gas turbine engine from a plurality of different axial locations along the gas turbine engine. The method may also include coupling the optical probes to a computing device, rotating the gas turbine engine about the longitudinal axis as the optical probes are used to simultaneously obtain images of an interior of the gas turbine engine at the different axial locations and receiving, with the computing device, image data associated with the images obtained by each of the optical probes at the different axial locations.

Abstract: A method for locating probes within a gas turbine engine may generally include positioning a plurality of location transmitters relative to the engine and inserting a probe through an access port of the engine, wherein the probe includes a probe tip and a location signal receiver configured to receive location-related signals transmitted from the location transmitters. The method may also include determining a current location of the probe tip within the engine based at least in part on the location-related signals and identifying a virtual location of the probe tip within a three-dimensional model of the engine corresponding to the current location of the probe tip within the engine. Moreover, the method may include providing for display the three-dimensional model of the engine, wherein the virtual location of the probe tip is displayed as a visual indicator within the three-dimensional model.

Abstract: Methods are provided for repairing a surface of a component within a gas turbine engine. A first bladder and a second bladder can be installed (simultaneously or independently) within the gas turbine engine. The first bladder and the second bladder can then be inflated with an inflating fluid to form a first circumferential seal and a second circumferential seal to define an isolated area within the gas turbine engine. All the surfaces within the isolated area can then be coated with a masking layer. At least a portion of the masking layer can then be removed to expose a working area, and a coating can be formed on the working area.

Abstract: A monitoring system for monitoring a plurality of components is provided. The monitoring system includes a plurality of client systems. The plurality of client systems is configured to generate a plurality of component status reports. The plurality of component status reports is associated with the plurality of components. The monitoring system also includes a component wear monitoring (CWM) computer device configured to receive the plurality of component status reports from the plurality of client systems, generate component status information based on a plurality of component status reports, aggregate the component status information to identify a plurality of images associated with a first component, and compare the plurality of images associated with the first component. The plurality of images represents the first component at different points in time. The CWM computer device is also configured to determine a state of the first component based on the comparison.

Abstract: Methods are provided for securing a tool within a gas turbine engine. The method can include inserting a tool into the engine; inserting a bladder between a portion of the tool and a component in the engine; and inflating the bladder to temporarily secure the tool in its position. For example, two tools (or more) can be inserted into the engine and secured by the bladder.

Abstract: A system includes one or more processors and a memory that stores a generative adversarial network (GAN). The one or more processors are configured to receive a low resolution point cloud comprising a set of three-dimensional (3D) data points that represents an object. A generator of the GAN is configured to generate a first set of generated data points based at least in part on one or more characteristics of the data points in the low resolution point cloud, and to interpolate the generated data points into the low resolution point cloud to produce a super-resolved point cloud that represents the object and has a greater resolution than the low resolution point cloud. The one or more processors are further configured to analyze the super-resolved point cloud for detecting one or more of an identity of the object or damage to the object.

Abstract: A system includes one or more processors configured to analyze obtained image data representing a rotor blade to detect a candidate feature on the rotor blade and determine changes in the size or position of the candidate feature over time. The one or more processors are configured to identify the candidate feature on the rotor blade as a defect feature responsive to the changes in the candidate feature being the same or similar to a predicted progression of the defect feature over time. The predicted progression of the defect feature is determined according to an action-guidance function generated by an artificial neural network via a machine learning algorithm. Responsive to identifying the candidate feature on the rotor blade as the defect feature, the one or more processors are configured to automatically schedule maintenance for the rotor blade, alert an operator, or stop movement of the rotor blade.

Abstract: A method includes obtaining a series of images of a rotating target object through multiple revolutions of the target object. The method includes grouping the images into multiple, different sets of images. The images in each of the different sets depict a common portion of the target object. At least some of the images in each set are obtained during a different revolution of the target object. The method further includes examining the images in at least a first set of the multiple sets of images using an artificial neural network for automated object-of-interest recognition by the artificial neural network.

Abstract: The systems and methods herein relate to artificial neural networks. The systems and methods examine an input image having a plurality of instances using an artificial neural network, and generate an affinity graph based on the input image. The affinity graph is configured to indicate positions of the instances within the input image. The systems and methods further identify a number of instances of the input image by clustering the instances based on the affinity graph.

Abstract: The present disclosure is directed to an improved system and method for repairing a bend in a turbine blade of a turbine of a gas turbine engine. The system includes an articulating guide configured to fit into an access port of the turbine. The articulating guide includes a proximal end and a distal end. The system also includes a repair tool configured at the distal end of the articulating guide. Further, the repair tool is configured to fit over the turbine blade. Thus, the repair tool is configured to bend the turbine blade to an unbent position while the turbine blade is secured within the turbine.

Abstract: A system that generates training images for neural networks includes one or more processors configured to receive input representing one or more selected areas in an image mask. The one or more processors are configured to form a labeled masked image by combining the image mask with an unlabeled image of equipment. The one or more processors also are configured to train an artificial neural network using the labeled masked image to one or more of automatically identify equipment damage appearing in one or more actual images of equipment and/or generate one or more training images for training another artificial neural network to automatically identify the equipment damage appearing in the one or more actual images of equipment.

Abstract: Systems and methods are provided relating to artificial neural networks are provided. The systems and methods obtain a teacher network that includes artificial neural layers configured to automatically identify one or more objects in an image examined by the artificial neural layers, receive a set of task images at the teacher network, examine the set of task images with the teacher network, identify a subset of the artificial neural layers that are utilized during examination of the set of task images with the teacher network, and define a student network based on the set of task images. The student network is configured to automatically identify one or more objects in an image examined by the subset.

Abstract: A method for additively manufacturing a component is provided. The method may include forming a surface on the top layer of the component, scanning the surface of the top layer of the component to determine if a defect is present in the surface, and if detected, correcting the defect within the surface. Scanning the surface of the top layer of the component to determine if a defect is present in the surface may be performed by obtaining data indicative of the surface of the top layer of the component by interrogating the surface of the top layer of the component with a scanning device, and comparing the data with a reference database to determine if an irregularity is present.

Abstract: Methods for remotely joining material a surface area of a component of a gas turbine engine are provided. The method can include inserting an integrated repair interface attached to a cable delivery system within a gas turbine engine; positioning a tip of the integrated repair interface adjacent to a defect defined within a surface of the component; temporarily attaching the tip adjacent to the defect within the surface of the component; and supplying a new material to the area to fill the defect.

Abstract: A method includes determining object class probabilities of pixels in a first input image by examining the first input image in a forward propagation direction through layers of artificial neurons of an artificial neural network. The object class probabilities indicate likelihoods that the pixels represent different types of objects in the first input image.

Abstract: Methods for material build-up on a tip of a blade of a gas turbine engine are provided. The method can include inserting a material supply and an inflatable bladder between the tip and a shroud such that the material supply is exposed to the tip and the inflatable bladder is positioned between the material supply and a shroud, inflating the inflatable bladder to force contact between the material supply and the tip, and causing relative movement between the material supply and the tip. The relative movement, in combination with the radial biased contact between the material supply and the tip, creates heat through friction. As such, the relative movement can frictionally weld new material from the material supply onto the tip of the blade. For example, the heat created can be sufficient to melt the surface of the material supply to transfer material from the material supply to the tip.

Abstract: 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.

Abstract: A method for forming an in situ temporary barrier within a gas turbine engine is provided. The method can include installing a bladder within the gas turbine engine, wherein the bladder defines a bladder body, and inflating the bladder with an inflating fluid such that the bladder body forms a circumferential seal within the gas turbine engine. The bladder body can be positioned between a row of stator vanes and an annular array of rotating blades to form a circumferential seal therebetween. A second bladder may be positioned circumferentially within the gas turbine engine.

Abstract: The present disclosure is directed to a system for performing in-situ laser machining on a component within a gas turbine engine, in which the component includes a substrate defining a surface. The system includes a laser system disposed externally of the gas turbine engine, a focusing optic, and a conduit. The laser system includes a laser unit that produces an output beam. The focusing optic is disposed between the laser unit and the component. The conduit defines a first end external of the engine and a second end that ingresses into the engine through an access port. The conduit includes a plurality of mirrors within the conduit. The plurality of mirrors directs the output beam from the laser system onto the component.