Abstract: A build assembly and a method of manufacturing the same are provided. The build assembly includes a first component, a second component, and a support structure coupling the two components together to fix their relative position. The support structure may be a “ghost” structure that is not connected with or does not contact the components, but is positioned such that the components are restrained to prevent distortion. The support structure may also be connected to the components and may define channels for removing additive powder from within or around the components.

Abstract: A turbine having a stationary shroud ring formed about rotor blades. The stationary shroud ring may include an inner shroud segment. The inner shroud segment may include a cooling configuration that includes a crossflow channel. The crossflow channel may extend lengthwise between an upstream end and a downstream end, and, therebetween, include a junction point that divides the crossflow channel lengthwise into upstream and downstream sections, with the upstream section extending between the upstream end and the junction point, and the downstream section extending between the junction point and the downstream end. The crossflow channel may have a cross-sectional flow area that varies lengthwise such that a cross-sectional flow area of the upstream section decreases between the upstream end and the junction point, and a cross-sectional flow area of the downstream section increases between the junction point and the downstream end.

Abstract: A build assembly and a method of manufacturing the same are provided. The build assembly includes a first component, a second component, and a support structure coupling the two components together to fix their relative position. The support structure may be a “ghost” structure that is not connected with or does not contact the components, but is positioned such that the components are restrained to prevent distortion. The support structure may also be connected to the components and may define channels for removing additive powder from within or around the components.

Abstract: A turbine having a stationary shroud ring formed about rotor blades. The stationary shroud ring may include an inner shroud segment. The inner shroud segment may include a cooling configuration that includes a crossflow channel. The crossflow channel may extend lengthwise between an upstream end and a downstream end, and, therebetween, include a junction point that divides the crossflow channel lengthwise into upstream and downstream sections, with the upstream section extending between the upstream end and the junction point, and the downstream section extending between the junction point and the downstream end. The crossflow channel may have a cross-sectional flow area that varies lengthwise such that a cross-sectional flow area of the upstream section decreases between the upstream end and the junction point, and a cross-sectional flow area of the downstream section increases between the junction point and the downstream end.