Siemens Energy, Inc.

Siemens Aktiengesellschaft

Shantanu P Mhetras

Ching-Pang Lee

Kok-Mun Tham

Alexander Ralph Beeck

Vincent Paul Laurello

Gm Salam Azad

Abdullatif M Chehab

Christopher K Rawlings

Manjit Shivanand

Glenn E Brown

A gas turbine having rotor discs (), a disc cavity () and a stator stage () extending to the disc cavity (). Seal housing flanges () extend from a seal housing () of the stator stage (). Rotor flanges () extend from a rotor disk (-). An inner rotor flange () and first seal housing flange () are inward from a second seal housing flange (). One rotor flange () is outward from the second seal housing flange (). The inner rotor flange () and first seal housing flange () extend toward one another to limit movement of main gas flow (). An inlet () injects air () between the outward rotor flange () and second seal housing flange ().

Flow discourager integrated turbine inter-stage U-ring

In a gas turbine engine, adjoining pairs of airfoil structures include airfoils mounted to respective platforms. The platforms have side edges defining matefaces that form a mateface gap extending from an upstream edge of the platforms to a downstream edge of the platforms. A flow field of working gas adjacent to endwalls of the platform comprises streamlines extending generally transverse to the axial direction from a first airfoil toward an adjacent second airfoil. To achieve improved aerodynamic performance, the mateface gap has portions oriented transverse to the streamlines and oriented aligned with the streamlines. A step in elevation of the side edges at the transverse portion can include injected cooling flow in a direction that enhances attachment of the flow at a downstream side.

Mateface gap configuration for gas turbine engine

A squealer tip formed from a pressure side rib and a suction side rib extending radially outward from a tip of the turbine blade is disclosed. The pressure and suction side ribs may be positioned along the pressure side and the suction side of the turbine blade, respectively. The pressure and suction side ribs may include chamfered leading edges with film cooling holes having exhaust outlets positioned therein. The film cooling holes may be configured to be diffusion cooling holes with one or more tapered sections for reducing the velocity of cooling fluids and increasing the size of the convective surfaces.

Turbine blade with chamfered squealer tip and convective cooling holes

The tip cooling arrangement of the present application reduces large cooling flow requirements which can compromise turbine performance. The tip cooling arrangement of the present application provides convective cooling of a turbine blade tip end, whether a flat tip or a squealer, by extending holes that provide fluid for film cooling the tip end. The holes are thus lengthened and extend from the relatively cooler suction side of the blade to the pressure side of the blade in close proximity to the floor of the tip end.

Extended length holes for tip film and tip floor cooling

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Orlando, FL, United States of America

Shantanu P Mhetras