US Patent 10030539 Gas turbine engine inner case including non-symmetrical bleed slots

A compressor of a gas turbine engine includes a plurality of rotors rotatable about a central longitudinal axis, a plurality of stators, and a circumferential inner case wall located outwardly of the plurality of rotors and the plurality of stators. The inner case wall includes a plurality of first slots located in a first section of the circumferential inner case wall and a plurality of second slots located in at least one second section of the circumferential inner case wall. A first area of each of the first slots is greater than a second area of each of the second slots. A circumferential manifold is located outwardly of the inner case wall including a port. At least one of the plurality of second slots is located proximate to the port.