Siemens Energy, Inc.

Mikro Systems, Inc.

John P Dalton

Rex A Smith

Stuart Bishop

Ching-Pang Lee

John Joseph Marra

Nan Jiang

Ronald J Rudolph

Stefan Irmisch

Matthew Gent

Frank Maichle

Tilmann Auf Dem Kampe

Frank A Maichle

George Obranic

A continuous serpentine cooling circuit forming a progression of radial passages (A,A) between pressure and suction side walls () in a MID region of a turbine airfoil (). The circuit progresses first axially, then tangentially, ending in a last radial passage (A) adjacent to the suction side () and not adjacent to the pressure side (). The passages of the axial progression () may be adjacent to both the pressure and suction side walls of the airfoil. The next to last radial passage (A) may be adjacent to the pressure side wall and not adjacent to the suction side wall. The last two radial passages (A,A) may be longer along the pressure and suction side walls respectively than they are in a width direction, providing increased direct cooling surface area on the interiors of these hot walls.

Integrated axial and tangential serpentine cooling circuit in a turbine airfoil

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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Wellington, FL, United States of America

John P Dalton