Abstract: A gas turbine engine includes a primary flow path fluidly connecting a compressor section, a combustor section and a turbine section. A cooling air flowpath is positioned radially outward of the primary flowpath. A first seal spans from an inner diameter of the cooling air flowpath to an outer diameter of the cooling air flowpath. The first seal includes at least one axial convolution and a plurality of pass through features. A bifurcation feature is positioned downstream of the first seal. The bifurcation feature is configured to direct a portion of an airflow through the first seal into a cooling air passage. A second seal contacts the bifurcation and the first seal, such that fluid radially inward of the bifurcation feature.