Patent ID: 9181816
Filing Date: 2015-11-10
Classification: F01D,F05D

Abstract:
1. A seal assembly between a disc cavity and a hot gas path that extends through a turbine section of a gas turbine engine comprising: a stationary vane assembly including a plurality of vanes and an inner shroud; and a rotating blade assembly axially upstream from the vane assembly and including a plurality of blades that are supported on a platform and rotate with a turbine rotor and the platform during operation of the engine, the axial direction defined by a longitudinal axis of the turbine section, the platform comprising: wherein, during operation of the engine, the grooves impart a circumferential velocity component to purge air flowing out of the disc cavity through the grooves to guide the purge air toward the 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; wherein the grooves include first sidewalls and second sidewalls, the first sidewalls being located circumferentially upstream from the second sidewalls; and wherein the second sidewalls of the grooves include a generally planar circumferentially facing endwall that extends generally radially outwardly from entrances of the grooves to exits thereof.