Gas turbine engine airfoil

US10385866B2 · kind B2 · utility

Assignee

• UNITED TECHNOLOGIES CORPORATION · US

Inventors

• Edward J. Gallagher · Town of West Hartford, US
• Byron R. Monzon · Cromwell, US
• Ling Liu · Glastonbury, US
• Linda S. Li · Middlefield, US
• Darryl Whitlow · Middletown, US
• Barry M. Ford · Middletown, US

Key dates

• Filing date: Aug 25, 2014
• Grant date: Aug 20, 2019
• Expiry date: Jan 9, 2036

Classification

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

Abstract

In one exemplary embodiment, an airfoil for a turbine engine includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil geometry corresponds to tangential leading and trailing edge curves and a tangential stacking offset curve. The airfoil extends from a root. A zero tangential reference point corresponds to tangential center of the root. YLE corresponds to a tangential distance from a leading edge to the reference point at a given span position. YTE corresponds to a tangential distance from a trailing edge to the reference point at a given span position. Yd corresponds to a tangential stacking offset at a given span position. (YLE−Yd)/(Yd−YTE) at 40% span position is about 1.5 and (YLE−Yd)/(Yd−YTE) at 20% span position is about 2.