Combustor-vane interface feather seal

A gas turbine engine comprising:

• a combustor disposed about an engine central axis and including a combustor wall and a combustion chamber, the combustor wall having a lip at an exit region of the combustion chamber;
• a vane adjacent the exit region, the vane including a platform and an airfoil section extending along a radial axis from the platform, the platform defining forward and trailing edges and first and second circumferential side edges joining the forward and trailing edges,
• the vane having rotational play about the radial axis under aerodynamic loads such that the vane moves relative to the combustor between a seated state in which the forward edge abuts the lip of the combustor wall and an unseated state in which there is a divergent gap between the forward edge and the lip of the combustor,
• the lip defining a first slot extending circumferentially and the forward edge defining a second slot extending circumferentially, the first and second slots together defining a seal slot;
• and
• an annular feather seal extending in the seal slot, the annular feather seal being wider than the divergent gap to maintain sealing when the vane is in the unseated state.