Abstract: A method of machining a feature in a workpiece includes orienting a waterjet guided laser device about the workpiece, ejecting a waterjet from a nozzle of the waterjet guided laser device, impinging the waterjet against the workpiece along a tool path causing a corresponding removal of material therefrom, and generating a non-uniform electric field proximate the waterjet to cause a deflection of the waterjet as the waterjet is impinging against the workpiece.

Abstract: An ultrasonic impact grinding assembly includes a base with a mount for connecting a workpiece to the base and a first tool arm. The ultrasonic impact grinding assembly also includes a second tool arm. The first tool arm and the second tool arm each include a base end, a distal end, at least one joint between the base end and the distal end, and at least one actuator configured to move the at least one joint. A first ultrasonic impact grinding tool head is connected to the distal end of the first tool arm. A second ultrasonic impact grinding tool head is connected to the distal end of the second tool arm.

Abstract: A tool for ultrasonic impact grinding apparatus driven to vibrate along a longitudinal axis at an applied operating frequency includes a tool body disposed on the longitudinal axis, a first tip extending from an output end of the tool body, and a second tip extending in parallel to the first tip from the output end of the tool body. The first tip has a first length. The second tip has a second length greater than the first length. A mass of the first and second tip is substantially balanced across the output end of the tool body and with respect to the longitudinal axis.

Abstract: A tool for an ultrasonic impact grinding machine driven to vibrate along a longitudinal axis includes a hollow tool body and a hollow tip extending from an end of the hollow tool body. The hollow tip has an outer surface comprising a plurality of grooves. The hollow tool body and the hollow tip are disposed about the longitudinal axis and the hollow tip and hollow tool body are each defined in part by a common bore extending along the longitudinal axis.

Abstract: A method of machining ceramic matrix composite components includes providing an ultrasonic vibration tool having a tool tip, and exciting the tool by providing a control current, such that the tool tip is repeatedly vibrated towards and away from a ceramic matrix composite workpiece. A slurry feed is supplied including abrasive particles to a surface to be machined by the tool tip. A vibration amplitude of the tool tip is controlled by sensing load on the tool and communicating with a computing device. The computing device controls the vibration amplitude of the tool tip. The computing device is provided with at least one memory programmed with historic data, and is operable to modify the vibration amplitude signal being sent to the tool, and comparing resulting load levels due to the change in vibration amplitude signals, and storing the change in vibration amplitude signals at the memory.

Abstract: A method of applying a top coat to an article according to an exemplary embodiment of this disclosure, among other possible things includes applying a first feedstock comprising particles of oxide-based material having diameters between about 1 and about 80 microns via a thermal spray process to form a first top coat layer on an article having a bond coat and applying a second feedstock comprising particles of oxide-based material having diameters between about 15 and about 60 microns via the thermal spray process to form a second top coat layer on the first top coat layer. An article and a barrier layer for an article are also disclosed.

Abstract: A process for coating a component includes applying a bond coat on a substrate of a component; applying a thermal barrier material to the bond coat; and applying a conforming reflective layer to the thermal barrier material, the conforming reflective layer conforming to porous microstructure of the ceramic coating.

Abstract: A method of forming an aerodynamic component for use in a gas turbine engine using ceramic matrix composites (CMCs) is provided. The method includes executing a full densification of the CMCs once a final shape of the aerodynamic component is achieved, identifying first and second sectors of an exterior surfaces of the aerodynamic component which have a surface roughness of less than a first roughness level and identifying second sectors of the exterior surface of the component which have a surface roughness of greater than a second roughness level, machining the first sectors to increase the surface roughness to greater than the first roughness level and machining the second sectors to decrease the surface roughness to less than the second roughness level.

Abstract: A method of forming a component for a gas turbine engine using ceramic matrix composites (CMCs) is provided. The method includes preforming the aerodynamic component into an initial desired shape using the CMCs, executing partial densification of the CMCs, repeating the preforming operations and the executing of the partial densification until a final desired shape of the aerodynamic component is achieved, machining or cutting the CMCs during one or more of the preforming operations and the executing of the partial densification to remove defects from the CMCs and executing a full densification of the CMCs.

Abstract: A method of forming an aerodynamic component for use in a gas turbine engine using ceramic matrix composites (CMCs) is provided. The method includes executing a full densification of the CMCs once a final shape of the aerodynamic component is achieved, identifying first and second sectors of an exterior surfaces of the aerodynamic component which have a surface roughness of less than a first roughness level and identifying second sectors of the exterior surface of the component which have a surface roughness of greater than a second roughness level, machining the first sectors to increase the surface roughness to greater than the first roughness level and machining the second sectors to decrease the surface roughness to less than the second roughness level.

Abstract: A refractory metal core (RMC) finishing method according to an exemplary aspect of the present disclosure includes, among other things, performing a plurality of finishing operations on a plurality of RMC samples, analyzing one or more properties of at least a portion of the plurality of RMC samples and selecting a combination of finishing operations for generating an RMC having desirable properties for manufacturing a part free from defects.

Abstract: An airfoil for a gas turbine engine includes a substrate portion extending from an airfoil leading edge to an airfoil trailing edge portion. The airfoil trailing edge portion includes a flared portion wherein a substrate portion thickness increases along a camber line of the airfoil, and a trailing edge defined as a full constant radius extending from a pressure side of the airfoil to a suction side of the airfoil. A coating portion includes a coating applied over at least a portion of the substrate portion.

Abstract: A system for automated adaptive manufacturing of airfoil castings is disclosed. The system may receive a three dimensional scan of a work piece. The system may compare the three dimensional scan to a digital model of the work piece. The system may identify an area of dimensional abnormality on the work piece based on the comparison. The system may alter the area of dimensional abnormality on the work piece.

Abstract: A method of manufacturing a casting is provided and includes establishing desired dimensions of a nominal casting, executing a casting process to produce multiple actual castings with each of the multiple actual castings having respective dimensions that differ from each other and from the desired dimensions of the nominal casting and engaging one or more tools to adaptively machine, without rigidly-programmed toolpaths, each of the multiple actual castings to reduce the respective differences between the actual dimensions of each of the multiple actual castings and the desired dimensions.

Abstract: A process for coating a component includes applying a bond coat on a substrate of a component; applying a thermal barrier material to the bond coat; and applying a conforming reflective layer to the thermal barrier material, the conforming reflective layer conforming to porous microstructure of the ceramic coating.

Abstract: A method of coating a component having a multiple of cooling holes includes removing at least a portion of a prior coating; directing a gas through at least one of the multiple of cooling holes; and applying a coat layer while directing the gas through at least one of the

Abstract: A process for coating a component includes applying a bond coat on a substrate of a component; applying a thermal barrier material to the bond coat; and applying a conforming reflective layer to the thermal barrier material, the conforming reflective layer conforming to porous microstructure of the ceramic coating.

Abstract: A method of removing features from a cast workpiece includes generating a nominal toolpath for machining the cast workpiece. The cast workpiece is mounted onto a platform of a computer numeric control machine. The cast workpiece is inspected with a probe to generate probe data. Features to be removed are identified based upon the probe data generated during the inspection. Any expected features of the cast workpiece that are missing from the cast workpiece are identified. A transformation matrix is applied to the nominal toolpath with a controller of the computer numeric control machine, wherein the transformation matrix is based upon the probe data. Alignment of the cast workpiece is adjusted relative to the computer numeric control machine based on the transformation matrix with the computer numeric control machine. Features are removed from the cast workpiece that were identified during inspection.

Abstract: A method of manufacturing an aerodynamic element with an edge is provided. The method includes producing the aerodynamic element with an initial condition, cooling the aerodynamic element, generating a predefined number of data points sufficient to characterize contours of the edge and comparing the data points to a nominal condition to derive transformation parameters applicable to cutting toolpaths to adapt the cutting toolpaths to the initial condition.

Abstract: A process for coating a component includes applying a bond coat on a substrate of a component; applying a thermal barrier material to the bond coat; and applying a conforming reflective layer to the thermal barrier material, the conforming reflective layer conforming to porous microstructure of the ceramic coating.