公开(公告)号：US20170159449A1

公开(公告)日：2017-06-08

申请号：US14960924

申请日：2015-12-07

Applicant: General Electric Company

Inventor： Jared Peter Buhler ,  Ronald Scott Bunker ,  Victor Hugo Silva Correia ,  Brian Kenneth Corsetti

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/188 ,  F05D2260/202 ,  Y02T50/676

Abstract: An airfoil for a gas turbine engine can have an exterior wall and an interior wall, with each wall having a thickness. The walls can intersect to define a corner at the intersection. A cooling passage can be defined by the walls at or near the corner to provide fluid communication between the interior and exterior of the airfoil. A film hole can be disposed in the walls and can have a length and diameter to define a ratio of length to diameter, L/D. An arcuate fillet can be located in the corner to define an effective radius for the fillet. The effective radius can be at least 1.5 times larger than the thicknesses of the walls to provide for an increased length to diameter ratio for the film hole.