公开(公告)号：EP2935793A4

公开(公告)日：2016-03-23

申请号：EP13863951

申请日：2013-11-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： THOMEN SETH J ,  CHLUS WIESLAW A

IPC: F01D5/30 ,  F01D11/00 ,  F01D11/08

CPC classification number: F01D11/006 ,  F01D5/3007 ,  F01D5/3092 ,  F05D2300/173

Abstract: A gas turbine engine stage includes a rotor having a slot. A blade has a root received in the slot, and a shank that extends radially outward from the root to a platform that supports an airfoil. A seal is supported on the shank and in engagement circumferentially between and with the shank and the rotor within the slot. A gas turbine engine includes compressor and turbine sections. The turbine section has a rotor with a slot. A combustor is provided axially between the compressor and turbine sections. A turbine blade in the turbine section includes a root received in the slot and a shank that extends radially outward from the root to a platform that supports an airfoil.