Westinghouse Electric Corporation

Mark T Kennedy

William E North

Paul H Davis

An airfoil for use in a turbomachine such as a stationary vane in a gas turbine. The airfoil has a plurality of longitudinally extending ribs in its trailing edge region that form first cooling fluid passages extending from the airfoil cavity to the trailing edge of the airfoil. The first cooling fluid passages are tapered so that their height and width decrease as they extend toward the trailing edge. Turbulating fins are spaced along the length of each passage to increase the heat transfer. The ribs have a plurality of radially extending passages spaced along their length so as to form an array of interconnected longitudinal and radial passages. The airfoil is formed by a casting process using a core that has longitudinal and radial fingers that correspond to the longitudinal and radial passages of the airfoil.

Apparatus for cooling a gas turbine airfoil and method of making same

A gas turbine vane having an inner shroud that is cooled by a portion of the cooling air directed to a cavity between two adjacent rows of discs. A portion of the cooling air in the cavity flows through impingement plates and impinges on the inner surface of the inner shroud. Another portion of the cooling air flows through a passage in the leading edge of the inner shroud that has a pin fin array for enhanced cooling. The impingement plates form chambers that collect both the impingement air and the pin fin passage air and direct it through holes in the trailing edge of the inner shroud for cooling of the trailing edge. Longitudinal passages along the side of the inner shroud direct the cooling air from the pin fin passage tot the trailing edge.

Gas turbine vane with a cooled inner shroud

A gas turbine stationary vane having an airfoil portion and inner and outer shrouds. Five serpentine radially extending cooling air passages are formed in the vane airfoil. The first passage is disposed adjacent the leading edge of the airfoil and the second passage is disposed adjacent the trailing edge. A first portion of the cooling air enters the first passage, from which it flows sequentially to the second, third, fourth and fifth passages. Additional cooling air enters the third passage directly, thereby bypassing the first and second passages and preventing over heating of the cooling air by the time it reaches the fifth passage. A radial tube extends through the second passage and directs cooling air through the airfoil, with essentially no rise in temperature, to an interstage cavity for disc cooling. Fins project into each of the passages and serve to increase the effectiveness and flow rate of the cooling air. The fins in the first and fifth passages are angled so as to direct the cooling air toward the leading and trailing edges, respectively. In addition, the fins in the second through fifth passages are angled to retard flow separation as the cooling air turns 180.degree. from one passage to the next.

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Oviedo, FL, United States of America

Mark T Kennedy