Compressor bleed offtake

A gas turbine engine having an engine axial centerline, comprising:

• a compressor section having a plurality of rotor stages and stator vane stages, each rotor stage having a plurality of rotor blades, and each rotor blade having a blade tip, each stator vane stage having a plurality of stator vanes;
• a combustor section;
• and
• a turbine section;
• wherein the compressor further includes an annular compressor shroud, the compressor shroud including:
• an inner radial panel, an outer radial panel, a forward panel, and an aft panel that collectively defining an annular interior region, wherein the inner radial panel is disposed radially inside of the outer radial panel, and the forward panel extends between the inner radial panel and the outer radial panel and is disposed at a forward end of the compressor shroud, and the aft panel extends between the inner radial panel and the outer radial panel and is disposed at an aft end of the compressor shroud;
• an airflow exit opening disposed within the outer radial panel;
• and
• an offtake disposed in the inner radial panel, the offtake defined in part by a segment of the inner radial panel, the inner radial panel segment extending a distance into the interior region, wherein the offtake includes an offtake passage that is in part defined by the inner radial panel segment;
• wherein the inner radial panel segment has an interior surface contiguous with the interior region and an exterior surface that is opposite the interior surface, the exterior surface contiguous with the offtake passage, and a plurality of apertures is defined in the inner radial panel segment, and is configured to permit airflow between the interior region and the offtake passage.