Patent Number: 6,254,345

Title: Internally cooled blade tip shroud

Abstract: A gas turbine engine turbine blade shrouded tip has an airfoil tip with a cross-sectional airfoil shape, a blade tip shroud attached to the tip, and a shroud cooling circuit disposed within the blade tip shroud. The shroud cooling circuit is operable for cooling substantially all of the shroud and is in fluid communication with a hollow interior of the tip. One embodiment of the invention includes two circumferentially extending forward and aft seal teeth on a radially outer shroud surface of the shroud extending in a radial direction away from the hollow interior of the tip. The shroud cooling circuit includes circumferentially extending shroud cooling passages between clockwise and counter-clockwise shroud side edges of the shroud. Forward and aft pluralities of the shroud cooling passages within the tip shroud are in fluid communication with first and second cavities respectively in the hollow interior.

Inventors: Harris; Daniel J. (West Chester, OH), Frederick; Robert A. (West Chester, OH), Timko; Lawrence P. (Fairfield, OH)

Assignee: General Electric Company

International Classification: F01D 5/18 (20060101); F01D 5/12 (20060101); F01D 5/22 (20060101); F01D 005/18 ()

Expiration Date: 07/03/2018