General Electric Company

Siemens Aktiengesellschaft

Dustin Jaime Muller

Ching-Pang Lee

William Scott Zemitis

Kok-Mun Tham

Melbourne James Myers

Richard Ryan Pilson

Eric Joseph Schroeder

Manjit Shivanand

Erik Johnson

Steven Coppess

Kahwai G Muriithi

A turbine blade includes an airfoil that includes a root end and a tip end. The tip end is radially spaced from the root end. A tip shroud extends from the tip end. The tip shroud includes a shroud plate. The shroud plate includes a plurality of undulating ridges.

Undulating tip shroud for use on a turbine blade

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

Growing community of inventors

Cincinnati, OH, United States of America

Dustin Jaime Muller