Abstract: An airfoil for a gas turbine includes a leading edge, a trailing edge a tip plate, a first sidewall extending in radial span between an airfoil root and the tip plate, and a second sidewall connected to the first sidewall at the leading edge and the trailing edge to define a cooling cavity therein. The sidewall extends in radial span between the airfoil root and the tip plate. The airfoil also includes a plurality of longitudinally spaced apart trailing edge cooling slots arranged in a column extending through the first sidewall. The slots are in flow communication with the cooling cavity and arranged in a non-uniform distribution along the trailing edge so that the number of slots in at least one portion of the trailing edge is greater than a different portion of the trailing edge.

Abstract: A method and apparatus redundantly store data, in particular video data objects, in a distributed computer system having at least three processor systems, each processor system being connected in point to point two way channel interconnection with each other processor system. The data is stored in a redundant fashion both at the computer system level as well as the processor system level. Accordingly, the failure of a single processor does not adversely affect the integrity of the data. The computer system can also overlay a switching system connected in a ring fashion for providing a fault tolerance to the failure of a single connected processor system at the switch level. Accordingly, there results a fault tolerant data distribution system.

Abstract: A turbine bucket comprising an airfoil portion, a shank portion and a dovetail mounting portion; an internal cooling circuit including inlet passages in the shank portion and the dovetail mounting portion connected to a cooling circuit in the airfoil portion, the inlet passages including a primary inlet passage on one side of a radial centerline of the bucket, and a secondary inlet cavity on an opposite side of the radial centerline; and a purge passage connecting the secondary inlet passage to the primary inlet passage.

Abstract: The cooling system for the nozzle edges includes a chamber containing a cooling medium. First and second elongated plenums are disposed along opposite side edges of each platform. Inlet passages communicate cooling medium from the chamber into each plenum. Outlet passages from each plenum terminate in outlet holes in the side edges of the platform to cool the gap between adjacent nozzle segments. Passageways communicate with each plenum and terminate in film cooling holes to film cool platform surfaces. In each plenum, the inlet passages are not in direct line-of-sight flow communication with the outlet passages and passageways.