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1. (WO2015126824) GAS TURBINE ENGINE AIRFOIL

Pub. No.:    WO/2015/126824    International Application No.:    PCT/US2015/016154
Publication Date: Fri Aug 28 01:59:59 CEST 2015 International Filing Date: Wed Feb 18 00:59:59 CET 2015
IPC: F01D 5/14
Applicants: UNITED TECHNOLOGIES CORPORATION
Inventors: GALLAGHER, Edward J.
MONZON, Byron R.
LIU, Ling
LI, Linda S.
WHITLOW, Darryl
FORD, Barry M.
Title: GAS TURBINE ENGINE AIRFOIL
Abstract:
An airfoil for a turbine engine includes pressure and suction sides that extend 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 total chord length and a span position and corresponds to a curve that has an increasing total chord length from the 0% span position to a first peak. The first peak occurs in the range of 45-65% span position, and the curve either remains generally constant or has a decreasing total chord length from the first peak to the 100% span position. The total chord length is at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm).