Blade platform with damper restraint

US10533431B2 · kind B2 · utility

Assignee

• UNITED TECHNOLOGIES CORPORATION · US

Inventors

• Charles Thistle · New Haven, US
• Mohamed Hassan · Berlin, DE

Key dates

• Filing date: Jan 3, 2017
• Grant date: Jan 14, 2020
• Expiry date: Nov 28, 2037

Classification

• Technology area (CPC —): General

Abstract

A blade for a gas turbine engine is disclosed herein. The blade having: a root; a platform located between the root and the blade, wherein the platform defines a cavity; a damper restraint located at a peripheral edge of the platform, wherein the damper restraint is a raised feature extending along at least a portion of the peripheral edge of the platform.