Gas turbine engine active clearance control system using inlet particle separator

US10612466B2 · kind B2 · utility

Assignee

• UNITED TECHNOLOGIES CORPORATION · US

Inventors

• Jonathan Jeffery Eastwood · Newington, US
• Joseph F. Englehart · Gastonia, US
• Graham Ryan Philbrick · Durham, US
• Henry K. Webster · North Palm Beach, US
• Richard Seleski · North Palm Beach, US
• ChaiDee Woods Brown · Boca Raton, US
• Michael G. McCaffrey · Windsor, US

Key dates

• Filing date: Sep 11, 2017
• Grant date: Apr 7, 2020
• Expiry date: Apr 7, 2038

Classification

• Technology area (CPC Y): Emerging Cross-Sectional Technologies
• CPC primary: Y02T50/60
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A turbine section for a gas turbine engine includes blade outer air seals and stator vanes that provide a core flow path. A turbine case supports blade outer air seals and stator vanes. An annular cavity is provided between an interior surface of the turbine case and the blade outer air seals and the stator vanes. A hole extends through the turbine case from an exterior surface to the interior surface. The annular cavity extends axially to an exit. A manifold circumscribes the exterior surface of the turbine case and provides an annular space therebetween. The annular space is in fluid communication with the exit of the annular cavity via the hole.