Outer rim seal assembly in a turbine engine

US9260979B2 · kind B2 · utility

Assignee

• Siemens Aktiengesellschaft · DE

Inventors

• Ching-Pang Lee · Cincinnati, US
• Kok-Mun Tham · Oviedo, US
• Manjit Shivanand · Oviedo, US
• Vincent P. Laurello · Guilford, US
• Gm Salam Azad · Oviedo, US
• Nicholas Francis Martin · High Point, US

Key dates

• Filing date: Nov 18, 2014
• Grant date: Feb 16, 2016
• Expiry date: Nov 18, 2034

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F05D2260/202
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A seal assembly between a hot gas path and a disc cavity in a turbine engine includes a non-rotatable vane assembly including a row of vanes and an inner shroud, a rotatable blade assembly axially adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, and an annular wing member located radially between the hot gas path and the disc cavity. The wing member extends generally axially from the blade assembly toward the vane assembly and includes a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof. The flow passages each include a portion that is curved as the passage extends radially outwardly to effect a scooping of cooling fluid from the disc cavity into the flow passages and toward the hot gas path.