A method of balancing a gas turbine engine rotor comprises the step of obtaining a rotor disc with a circumferential array of balance tabs projecting from a peripheral rim of the disc. Stress shielding scallops are defined in the rotor disc between the tabs. The balancing is achieved by removing material from at least one of the tabs.

An assembly for a dual-walled component of a gas turbine engine and methods of forming and repairing a dual-walled component. The assembly includes a cold section part having an outer surface that defines a plurality of impingement apertures, a hot section part including a pre-sintered preform, the hot section part positioned over the outer surface of the cold section part, and a plurality of support structures including the pre-sintered preform, the plurality of support structures positioned between the hot section part and the cold section part, the plurality of support structures separating the hot section part from the cold section part to define at least one cooling channel therebetween.

An assembly for a dual-walled component of a gas turbine engine and methods of forming and repairing a dual-walled component. The assembly includes a cold section part having an outer surface that defines a plurality of impingement apertures, a hot section part including a pre-sintered preform, the hot section part positioned over the outer surface of the cold section part, and a plurality of support structures including the pre-sintered preform, the plurality of support structures positioned between the hot section part and the cold section part, the plurality of support structures separating the hot section part from the cold section part to define at least one cooling channel therebetween.

A method for manufacturing a blade, the method includes casting a nickel alloy blade precursor having an airfoil and a root. The airfoil and the root are solution heat treating differently from each other. After the solution heat treating, the root is wrought processed. After the wrought processing, an exterior of the root is machined.

A method for manufacturing a blade, the method includes casting a nickel alloy blade precursor having an airfoil and a root. The airfoil and the root are solution heat treating differently from each other. After the solution heat treating, the root is wrought processed. After the wrought processing, an exterior of the root is machined.

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.

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.

A system includes a machine tool having a clamp. The system also includes a processing head configured to be temporarily held by the clamp of the machine tool. The processing head is also configured to deposit one or more media onto a workpiece. The processing head includes a guide configured to direct energy from an energy source onto the workpiece and/or the one or more media. The processing head also includes one or more supplies including one or more reservoirs within the processing head. The one or more reservoirs are configured to receive the one or more media, store the one or more media as the processing head is moved from one location to another location, and provide the one or more media.

A system includes a machine tool having a clamp. The system also includes a processing head configured to be temporarily held by the clamp of the machine tool. The processing head is also configured to deposit one or more media onto a workpiece. The processing head includes a guide configured to direct energy from an energy source onto the workpiece and/or the one or more media. The processing head also includes one or more supplies including one or more reservoirs within the processing head. The one or more reservoirs are configured to receive the one or more media, store the one or more media as the processing head is moved from one location to another location, and provide the one or more media.

The system for designing advanced Kaplan turbine-based on advanced blade design of a hydro powered turbine comprises an EES for calculating and determining a set of parameters involved in the designing of Kaplan turbine blade; a designing user interface for designing a 3d-model of the Kaplan turbine blade; an analyzing unit for CFD analysis of the turbine models on based on the K-omega turbulent model with a Y+ of 1, wherein the turbulent model is used to ensure the near wall function of water and the rotational pressure applied on the blades thereby generating results of the analysis using CFD post and plotted on a table for the comparative study of the blade models; and a manufacturing unit for manufacturing Kaplan turbine blade based on comparative study of the blade models using a machine learning approach.