Composite fan blade platform double wedge centrifugal seal

Claim 1

In a turbojet engine having a rotatable turbine wheel, turbine blades with blade platforms secured about the periphery of the wheel, said blade platforms being provided with clearance gaps between the adjacent edges thereof to allow for individual relative rotational movement of said turbine blades around their minor root axes; sealing means for preventing turbine air from escaping through the gaps between the blade platforms, said sealing means comprising an elongated flexible ribbon-like member having a left leg portion extending outwardly to the left and a right leg portion extending outwardly to the right, a central wedge portion between said left and right leg portions, at least one invagination on the inner side of said wedge portion facing the turbine wheel axis, said central wedge portion being positioned directly under the gap between two adjacent blade platforms, the left leg portion of said sealing means being fixedly bonded to the underside of one blade platform, the sealing means being urged radially outward at the engine operating speed in response to centrifugal force causing the wedge portion of the sealing means to enter and fill the gap between the blade platforms causing the invagination to close and the right leg portion of the sealing means to press against the underside of the next adjacent blade platform thereby providing the required seal.