Invention Application
- Patent Title: GAS TURBINE ENGINE AIRFOIL
-
Application No.: US15706025Application Date: 2017-09-15
-
Publication No.: US20180016912A1Publication Date: 2018-01-18
- Inventor: Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
- Applicant: United Technologies Corporation
- Main IPC: F01D5/14
- IPC: F01D5/14

Abstract:
A gas turbine engine include a combustor section arranged between a compressor section and a turbine section. A fan section has multiple fan blades. A geared architecture couples the fan section to the turbine section or compressor section. The fan blades include an airfoil that has pressure and suction sides. The airfoil extends 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 has a relationship between a trailing edge dihedral and a span position. The trailing edge dihedral positive from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning and a negative dihedral corresponds to pressure side-leaning.
Public/Granted literature
- US09988908B2 Gas turbine engine airfoil Public/Granted day:2018-06-05
Information query