Turbine engine with composite airfoil assembly having dovetail portion

A turbine engine (10, fig 1) has a disk 102 (such as a rotor disk) and a composite airfoil (aerofoil) assembly 104 (such as a compressor blade or turbine blade). The disk is rotatable and has a slot 108 extending axially along a periphery 154 between a disk forward surface 150 and a disk aft surface 152 with an inner slot face (158, fig 4) radially opposite the periphery. The composite airfoil assembly comprises an airfoil portion 110 and a dovetail portion 112, the dovetail portion being slidably received in the slot with a gap (136, fig 4) between a radially inner surface 126 of the dovetail portion and the inner slot face. A pitch snubber 160 is provided on the slot or radially inner surface and extends radially into the gap. The pitch snubber has a total axial length less than or equal to 50% of a span of the dovetail, or the pitch snubber is integrally formed with at least one of the composite airfoil assembly or the disk, or the pitch snubber terminates within the gap at a non-zero radial distance from an opposing portion of one of the slot or the radially inner surface.