Patent ID: 8944770
Filing Date: 2015-02-03
Classification: F01D,F05D

Abstract:
1. A disk for a gas turbine engine comprising: a CMC hub defined about an axis; a rail integrated with said CMC hub, said rail defines a rail platform section that tapers to a rail inner bore; an arm integrated with said CMC hub, said arm extending axially from said CMC hub at a radial distance from said axis that is equal to a self-sustaining radius wherein mass radially inboard of said self-sustaining radius is load carrying and mass radially outboard of said self-sustaining radius is not load carrying and cannot support itself; and multiple CMC airfoils integrated with and extending radially outwards from said CMC hub in a circumferential arrangement, and said CMC hub, said rail, and said multiple CMC airfoils form a monolithic piece with a continuity of fibers.