Compressor apparatus with bleed slot and supplemental flange

A gas turbine engine apparatus, comprising:

• a compressor, a combustor, and a turbine arranged in serial flow relationship, wherein the compressor includes:
• an annular compressor casing;
• a stator row disposed inside the compressor casing;
• a blade row mounted for rotation about a centerline axis inside the compressor casing;
• a bleed slot passing through a forward section of the compressor casing, wherein the bleed slot is bounded by inboard and outboard walls defined within the forward section of the compressor casing, the bleed slot having an inlet positioned axially between the stator row and the blade row, the bleed slot extending along a slot axis, at least a portion of the bleed slot lying within an axial extent of the blade row;
• and
• an annular supplemental flange extending radially outward from the forward section of the compressor casing, wherein at least a portion of the supplemental flange is axially positioned within an axial extent of the bleed slot, wherein the supplemental flange is cantilevered and has a freestanding end, and wherein the supplemental flange includes an enlarged portion at an outer periphery thereof, and a necked-down portion adjacent the forward section of the compressor casing, wherein the necked-down portion is positioned axially between the inlet of the bleed slot and an outlet of the bleed slot.