Patent ID: 7284958
Filing Date: 2007-10-23
Classification: F01D,F05D,Y02T

Abstract:
1. A gas turbine engine blade platform comprising: a main body having a leading edge and a trailing edge with an outer surface extending substantially therebetween, said outer surface further extending between a first blade engagement side and a second blade engagement side; and at least one pair of platform retention members extending from said main body, one of said pair of platform retention members located at said first blade engagement side and the other of said pair of platform retention members spaced from said one of the pair of platform retention members and located at said second blade engagement side, wherein said pair of platform retention members are adapted to be located on opposites sides of a disk lug to restrain radial movement of said main body; and a plurality of blade prelocating members adapted to engage with a gas turbine engine blade.