Siemens Energy, Inc.

Stuart Bishop

John P Dalton

Rex A Smith

Stefan Irmisch

Matthew Gent

Frank Maichle

George Obranic

Tilmann Auf Dem Kampe

Frank A Maichle

A sealing interface for a component in a turbine machine, wherein a plug is mechanically affixed within an entrance passage of an aperture. The plug is secured in place within the entrance passage through deformation of an inner end of the plug to cause the plug to mechanically engage a groove formed adjacent the entrance passage.

Mechanically affixed turbine shroud plug

Introducing a plurality of geometrically shaped members () into a cooling passage () of a gas turbine airfoil () will effectively reduce the cross-sectional flow area while simultaneously retaining a sufficiently thick external contour desired for proper gas path aerodynamic behavior. Small cooling sub-passages () formed around the geometric members will create a preferentially higher coolant flow rate and heat transfer coefficient at the cooled surface () when compared to the interior of the cavity. The geometric shapes may be metal or ceramic spheres retained in the cooling cavity by a retaining structure such as a screen grid () or perforated plate (). The openings () in the retaining structure may be unevenly distributed to preferentially allow more coolant to enter the cavity proximate the cooled walls. The size/shape of the geometrically shaped members may be varied to achieve a desired heat transfer coefficient along the cooled wall surface ().

Gas turbine component with reduced cooling air requirement

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Palm City, FL, United States of America

Stuart Bishop