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

US9181816B2 · kind B2 · utility

Assignee

• Siemens Aktiengesellschaft · DE

Inventors

• Ching-Pang Lee · Cincinnati, US
• Kok-Mun Tham · Oviedo, US
• Eric Schroeder · Loveland, US
• Erik Johnson · Cedar Park, US
• Dustin Muller · Cincinnati, US
• Steven Coppess · Cincinnati, US
• Manjit Shivanand · Oviedo, US
• Kahwai G. Muriithi · Simpsonville, US

Key dates

• Filing date: Feb 25, 2014
• Grant date: Nov 10, 2015
• Expiry date: Feb 25, 2034

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F05D2260/14
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

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.