Gas turbine engines typically include a compressor section to pressurize inflowing air, a combustor section to burn a fuel in the presence of the pressurized air, and a turbine section to extract energy from the resulting combustion gases. The compressor section may include a plurality of rotor blades separated by a plurality of stator vane assemblies mounted within the engine casing. Each stator vane assembly may comprise one or more stator shrouds coupled together end to end to form an annular structure. Typically, a small, flat metal part (sometimes referred to as a feather seal) may be inserted horizontally between the connected ends of stator shrouds to minimize air flow leakage from the pressurized gas path. However, gaps on the radially inward and/or radially outward side of the feather seal may still exist as the adjacent stator shrouds separate due to thermal and gas loads, resulting in air flow leakage in the radial and axial direction. Air flow leakage may result in overall loss in performance to the gas turbine engine.