Siemens Aktiengesellschaft

Steven Coppess

Ching-Pang Lee

Kok-Mun Tham

Eric Joseph Schroeder

Erik Johnson

Manjit Shivanand

Dustin Jaime Muller

Kahwai G Muriithi

A seal assembly between a disc cavity and a hot gas path in a gas turbine engine includes a stationary vane assembly and a rotating blade assembly axially upstream from the vane assembly. A platform of the blade assembly has a radially outwardly facing first surface, an axially downstream facing second surface defining an aft plane, and a plurality of grooves extending into the second surface such that the grooves are recessed from the aft plane The grooves are arranged such that a circumferential space is defined between adjacent grooves During operation of the engine, the grooves impart a circumferential velocity component to purge air flowing out of a disc cavity through the grooves to guide the purge air toward a hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.

Seal assembly including grooves in an aft facing side of a platform in a gas turbine engine

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Cincinnati, OH, United States of America

Steven Coppess