A gas turbine engine blade (10, 40, 70, 100, 140, 170) comprising: a dovetail portion (16, 46, 76, 106, 146, 176) comprising a first ceramic matrix composite; an airfoil portion (12, 42, 72, 102, 142, 172) comprising the first ceramic matrix composite, wherein the gas turbine engine blade (10, 40, 70, 100, 140, 170) defines a radial axis extending from a first end (26, 116, 156, 186) of the airfoil portion (12, 42, 72, 102, 142, 172) to a second, opposite end (24, 114, 154, 184) of the dovetail portion (16, 46, 76, 106, 146, 176) and an axial plane substantially normal to the radial axis; a transition portion (14, 44, 74, 104, 144, 174) between the airfoil portion (12, 42, 72, 102, 142, 172) and the dovetail portion (16, 46, 76, 106, 146, 176), wherein the airfoil portion (12, 42, 72, 102, 142, 172), the transition portion (14, 44, 74, 104, 144, 174), and the dovetail portion (16, 46, 76, 106, 146, 176) comprise a plurality of fibers (54, 58, 84, 88) extending continuously from adjacent the first end (26, 116, 156, 186) to adjacent the second end (24, 114, 154, 184); and a platform portion (22, 52, 82, 112, 152, 182) that substantially surrounds the transition portion (14, 44, 74, 104, 144, 174), wherein at least part of the platform portion (22, 52, 82, 112, 152, 182) extends parallel to the axial plane, characterised in that the airfoil portion (12, 42, 72, 102, 142, 172) defines a capture feature (20, 50, 80, 110, 150, 180) that forms a mechanical stop configured to engage with and mechanically restrain the platform portion (22, 52, 82, 112, 152, 182) from moving beyond the capture feature (20, 50, 80, 110, 150, 180) toward the first end (26, 116, 156, 186) of the airfoil portion, wherein the capture feature (20, 50, 80, 110, 150, 180) is located closer to the first end (26, 116, 156, 186) of the airfoil than at least part of the platform portion (22, 52, 82, 112, 152, 182), wherein the capture feature (20, 50, 80, 110, 150, 180) extends in a direction parallel to the axial plane, and wherein the capture feature (20, 50, 80, 110, 150, 180) extends further in the direction parallel to the axial plane than a part of the transition portion (14, 44, 74, 104, 144, 174) adjacent to the capture feature (20, 50, 80, 110, 150, 180). a dovetail portion (16, 46, 76, 106, 146, 176) comprising a first ceramic matrix composite; an airfoil portion (12, 42, 72, 102, 142, 172) comprising the first ceramic matrix composite, wherein the gas turbine engine blade (10, 40, 70, 100, 140, 170) defines a radial axis extending from a first end (26, 116, 156, 186) of the airfoil portion (12, 42, 72, 102, 142, 172) to a second, opposite end (24, 114, 154, 184) of the dovetail portion (16, 46, 76, 106, 146, 176) and an axial plane substantially normal to the radial axis; a transition portion (14, 44, 74, 104, 144, 174) between the airfoil portion (12, 42, 72, 102, 142, 172) and the dovetail portion (16, 46, 76, 106, 146, 176), wherein the airfoil portion (12, 42, 72, 102, 142, 172), the transition portion (14, 44, 74, 104, 144, 174), and the dovetail portion (16, 46, 76, 106, 146, 176) comprise a plurality of fibers (54, 58, 84, 88) extending continuously from adjacent the first end (26, 116, 156, 186) to adjacent the second end (24, 114, 154, 184); and a platform portion (22, 52, 82, 112, 152, 182) that substantially surrounds the transition portion (14, 44, 74, 104, 144, 174), wherein at least part of the platform portion (22, 52, 82, 112, 152, 182) extends parallel to the axial plane, characterised in that the airfoil portion (12, 42, 72, 102, 142, 172) defines a capture feature (20, 50, 80, 110, 150, 180) that forms a mechanical stop configured to engage with and mechanically restrain the platform portion (22, 52, 82, 112, 152, 182) from moving beyond the capture feature (20, 50, 80, 110, 150, 180) toward the first end (26, 116, 156, 186) of the airfoil portion, wherein the capture feature (20, 50, 80, 110, 150, 180) is located closer to the first end (26, 116, 156, 186) of the airfoil than at least part of the platform portion (22, 52, 82, 112, 152, 182), wherein the capture feature (20, 50, 80, 110, 150, 180) extends in a direction parallel to the axial plane, and wherein the capture feature (20, 50, 80, 110, 150, 180) extends further in the direction parallel to the axial plane than a part of the transition portion (14, 44, 74, 104, 144, 174) adjacent to the capture feature (20, 50, 80, 110, 150, 180).