Abstract: A method of making a turbomachine part, wherein the method can include machining a blank into a base having blades extending therefrom, the blades defining a channel therebetween. The method can also include forming a bridge constructed from refractory material in the channel between the blades, and forming a cover on the tops of the blades and over the channel, such that the base, the blades, and the cover form a single substantially homogenous turbomachine part once the bridge is removed.

Abstract: A method of making a turbomachine part, wherein the method can include machining a blank into a base having blades extending therefrom, the blades defining a channel therebetween. The method can also include forming a bridge constructed from refractory material in the channel between the blades, and forming a cover on the tops of the blades and over the channel, such that the base, the blades, and the cover form a single substantially homogenous turbomachine part once the bridge is removed.

Abstract: A method of making a turbomachine part, wherein the method can include machining a blank into a base having blades extending therefrom, the blades defining a channel therebetween. The method can also include forming a bridge constructed from refractory material in the channel between the blades, and forming a cover on the tops of the blades and over the channel, such that the base, the blades, and the cover form a single substantially homogenous turbomachine part once the bridge is removed.

Abstract: A method of making a turbomachine part, wherein the can include machining a blank into a base having blades extending therefrom, the blades defining a channel therebetween. The method can also include forming a bridge in the channel between the blades, and forming a cover on the tops of the blades and over the channel, such that the base, the blades, and the cover form a single substantially homogenous turbomachine part once the bridge is removed.

Abstract: A method of making a turbomachine part, wherein the can include machining a blank into a base having blades extending therefrom, the blades defining a channel therebetween. The method can also include forming a bridge in the channel between the blades, and forming a cover on the tops of the blades and over the channel, such that the base, the blades, and the cover form a single substantially homogenous turbomachine part once the bridge is removed.

Abstract: A damper film bearing assembly for supporting a rotatable shaft of a turbomachine includes a housing having a central bore sized to receive the bearing member, and an annular cavity formed within the housing around the central bore. The annular cavity includes an outer wall that is concentric with the central bore. A bearing member having an annular outer surface and an inner bearing surface is mounted within the cavity and engages the shaft to support the shaft within the housing. A fluid film damper mechanism acts between the annular outer surface and the outer wall of the cavity for damping radial movement of the bearing member within the cavity. A resiliently adjustable dead weight hanging spring support system acts between the housing and the bearing member to support the dead weight of the shaft within a vertically centered position within the central bore so that the fluid film damper means functions to maintain the shaft centered within the bore when vibrations occur during rotation of the shaft.