US Patent 10253639 Ceramic matrix composite gas turbine engine blade

The disclosure describes a gas turbine engine blade that includes a dovetail portion comprising a first ceramic matrix composite, an airfoil portion comprising the first ceramic matrix composite, a transition portion between the airfoil portion and the dovetail portion, and a platform portion that substantially surrounds the transition portion. The airfoil portion may define a capture feature that is configured to engage with and mechanically restrain the platform portion from moving beyond the capture feature toward a tip of the airfoil portion.