Abstract: Systems, devices, and methods for additive manufacturing of objects are provided. In some embodiments, a system for fabricating an object includes a flexible substrate, a carriage coupled to the flexible substrate, an actuator, at least one recoater supported by the carriage, and an energy source. The flexible substrate can be configured to carry a precursor material. The carriage can vertically displace an active region of the flexible substrate away from a remaining region of the flexible substrate and toward a build platform. The actuator can be configured to move the carriage relative to the flexible substrate. The at least one recoater can be configured to apply the precursor material to the flexible substrate. The energy source can be configured to output energy toward the precursor material at the active region of the flexible substrate to form a portion of an object on the build platform.

Abstract: Integrated core-shell investment casting molds that provide tongue or groove structures corresponding, respectively, to groove or tongue structures in the surface of the turbine blade or stator vane, including in locations that are otherwise inaccessible provide a pathway to restrict cooling flow between turbine blades to the flowpath.

Abstract: Integrated core-shell investment casting molds that provide tongue or groove structures corresponding, respectively, to groove or tongue structures in the surface of the turbine blade or stator vane, including in locations that are otherwise inaccessible provide a pathway to restrict cooling flow between turbine blades to the flowpath.

Abstract: The present disclosure generally relates to integrated core-shell investment casting molds that provide tongue or groove structures corresponding, respectively, to groove or tongue structures in the surface of the turbine blade or stator vane, including in locations that are otherwise inaccessible. The groove and tongue structures also provide a pathway to restrict cooling flow between turbine blades to the flowpath.

Abstract: A turbine nozzle segment may have a band having a flange extending radially from a non-flowpath side and an aft end. A plurality of airfoils may extend radially from a flowpath side of the band and may have trailing edges. A plurality of cooling holes may be disposed in the flange and directed at the aft end between the trailing edges.

Abstract: A method for repairing a turbine nozzle segment having a band and a plurality of airfoils, where the band has a flange is described. The method includes the steps of repairing a damaged area on the turbine nozzle segment and drilling a plurality of cooling holes in the flange.