Shape recessed surface cooling air feed hole blockage preventer for a gas turbine engine

US11073024B2 · kind B2 · utility

Assignee

• RAYTHEON TECHNOLOGIES CORPORATION · US

Inventors

• Christopher Perron · Tolland, US
• Justin M. Aniello · Ellington, US
• Shawn M. McMahon · Manchester, US
• Mohamed Hassan · Berlin, DE
• Ricardo Trindade · Coventry, US
• Steven Bruce Gautschi · Naugatuck, US
• David Barger · Town of East Hartford, US
• Brett Alan Bartling · Monroe, US
• Nicholas J. Madonna · Wallingford, US
• Robin Prenter · Avon, US
• Ryan Lundgreen · Granby, US
• Christopher Cosher · Vernon, US

Key dates

• Filing date: Dec 14, 2018
• Grant date: Jul 27, 2021
• Expiry date: May 21, 2039

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F05D2260/607
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooing airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.