Redundant entry cooling air feed hole blockage preventer for a gas turbine engine

US11078796B2 · kind B2 · utility

Assignee

• RAYTHEON TECHNOLOGIES CORPORATION · US

Inventors

• Christopher Perron · Tolland, US
• Justin M. Aniello · Ellington, US
• Shawn M. McMahon · Manchester, US
• 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
• Mohamed Hassan · Berlin, DE

Key dates

• Filing date: Dec 14, 2018
• Grant date: Aug 3, 2021
• Expiry date: Apr 27, 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 includes a multiple of vanes that extend between the inner vane platform and the outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a respective one of a multiple of feed passages; a multiple of metering passages in the outer vane platform, each of the multiple of metering passages in communication with the respective one of the multiple of feed passages; and a multiple of secondary passages in the outer vane platform, each of the multiple of secondary passages in communication with the respective one of the multiple of metering passages.