公开(公告)号：US20190071984A1

公开(公告)日：2019-03-07

申请号：US15694394

申请日：2017-09-01

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： JEFFREY LEON ,  WILLIAM INDOE ,  BRIAN J. BURKE ,  KIMBERLY CARUSO ,  SANTIAGO ORELLANA ,  KURT LEACH ,  FABIAN D. BETANCOURT

IPC: F01D5/30 ,  F01D5/02

Abstract: A turbine rotor disk for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a number of blade posts, tabs and slots circumferentially disposed about a rim portion of the disk. The tabs each include a blade post transition portion, a slope portion radially inward of the blade transition portion and a face portion radially inward of the slope portion. The blade posts, tabs and slots are circumferentially oriented about the rim portion such that a tab or slot is positioned radially inward of each blade post.