Variable area vane endwall treatments

A gas turbine engine comprising:

• a compressor section;
• a combustor section downstream of the compressor section;
• and
• a turbine section downstream of the combustor section, the turbine section including at least one variable vane stage having an outer diameter endwall, an inner diameter endwall spaced radially inward of the outer diameter endwall, and at least one variable vane airfoil supported between the outer and inner endwalls for rotation about an axis, the variable vane airfoil including an outer diameter surface spaced from the outer diameter endwall by a first gap and an inner diameter surface spaced from the inner diameter endwall by a second gap, and wherein the outer and inner diameter surfaces and the outer and inner diameter endwalls are configured such that the first and second gaps remain generally constant in size as the variable vane airfoil rotates about the axis.