Gas turbine engine component with combined mate face and platform cooling

US10227875B2 · kind B2 · utility

Assignee

• UNITED TECHNOLOGIES CORPORATION · US

Inventors

• Scott D. Lewis · Vernon, US
• Brandon M. Rapp · Town of West Hartford, US
• Jeffrey S. Beattie · South Glastonbury, US
• Matthew Andrew Hough · Town of West Hartford, US
• Bret M. Teller · Meriden, US
• Jeffrey Michael Jacques · Town of East Hartford, US
• Max Asterlin · Vernon, US

Key dates

• Filing date: Feb 7, 2014
• Grant date: Mar 12, 2019
• Expiry date: May 4, 2035

Classification

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

Abstract

A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge, circumferentially extends between a first mate face and a second mate face, and includes a gas path surface and a non-gas path surface. The component defines at least one cavity that extends at least partially inside of the component. A first plurality of cooling holes extends from the at least one cavity to at least one of the first mate face and the second mate face and a second plurality of cooling holes extends from either the at least one cavity or the non-gas path surface to the gas path surface.