Rotor device of an aircraft engine with a damping device between turbines blades

US10450866B2 · kind B2 · utility

Assignee

• ROLLS-ROYCE DEUTSCHLAND LTD & CO KG · DE

Inventors

• Markus Weinert · Wurmlingen, DE
• Tobias Leymann · Berlin, DE

Key dates

• Filing date: Jul 22, 2016
• Grant date: Oct 22, 2019
• Expiry date: Oct 21, 2037

Classification

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

Abstract

A rotor of an aircraft engine includes a disk wheel and at least two turbine blades. A damping device is arranged below a blade platform and inside a cavity between the blades in the radial direction. The cavity is formed by a respective recess at adjoining blades, with respective recesses having an outer guide surface in the radial direction, acting together with the damping device during operation of the rotor. The guide surface extends radially, from the lateral edge area of the blade to the central area of the blade. The respective recess extends circumferentially from a boundary plane defined by the lateral edge area of the blade to a side surface that delimitates the guide surface towards the blade center. The recess of at least one of the adjacent blades completely receives the damping device.