Patent ID: 9200593
Filing Date: 2015-12-01
Classification: B64D,F01D,F02K

Abstract:
1. A gas turbine engine fan section comprising: a hub having a flange with an aperture; circumferentially spaced fan blades supported on the hub; and a spacer arranged between adjacent fan blades and operatively supported by the hub, the spacer configured to be collapsible in response to a fan blade load exerted on the spacer in excess of a threshold load, the spacer generally rigid at fan blade loads below the threshold load, wherein the spacer includes a base with an opening, and a fastener extends through the aperture and the opening to secure the spacer to the hub, wherein the spacer includes a wall providing a cavity, the wall including a notch providing a collapse-inducing structure deforming the cavity in response to the fan blade load.