Stress-reducing indentor profile for gas turbine engine blade mountings and other applications

摘要

An indentor, (eg. forming part of a disc 50, in a gas turbine engine) for contacting a bearing surface 60 (eg. forming part of a dove-tail blade root in a gas turbine engine) comprises a contact surface 58, complimentary to that of the bearing surface 60, and an integral tapering portion 100, which defines part of the contact surface 58, and defines an edge of contact 74, between the contact surface 58, and the bearing surface 60. Various profiles of the tapering portion are disclosed and the indentor arrangement may be applied to roller bearings, railway wheels and tracks, toothed shaft connections, and pins passing though holes in walls.