A compressor for a gas turbine engine, comprising: a rotor platform; a rotor blade extending radially outwardly from the rotor platform, the rotor blade including a pressure sidewall and a circumferentially opposing suction sidewall extending in a radial direction between a root and a tip and in an axial direction between a leading edge and a trailing edge; a casing having an inner surface surrounding the tip and spaced radially outwardly from the tip to define a gap between the casing and the tip, the casing and the rotor platform defining a primary air flow path between the casing and the rotor platform to direct a primary air flow in a direct air in a downstream direction; a secondary air flow system comprising a bleed inlet disposed in the inner surface of the casing downstream of the rotor blade and configured to remove secondary air flow from the primary air flow; an injection opening disposed in the inner surface of the casing upstream of the bleed inlet; an accessory conduit configured to be fluidly coupled to an accessory system of the gas turbine engine; and a plenum fluidly coupled to the bleed inlet, the injection opening, and the accessory conduit, characterized in that the bleed inlet and plenum at least partially define a secondary air flow path for the secondary air flow such that a first portion of the secondary air flow is directed in through the bleed inlet, through the plenum, and out through the injection opening and a second portion of the secondary air flow is directed in through the bleed inlet, through the plenum, and out through the accessory conduit. a rotor platform; a rotor blade extending radially outwardly from the rotor platform, the rotor blade including a pressure sidewall and a circumferentially opposing suction sidewall extending in a radial direction between a root and a tip and in an axial direction between a leading edge and a trailing edge; a casing having an inner surface surrounding the tip and spaced radially outwardly from the tip to define a gap between the casing and the tip, the casing and the rotor platform defining a primary air flow path between the casing and the rotor platform to direct a primary air flow in a direct air in a downstream direction; a secondary air flow system comprising a bleed inlet disposed in the inner surface of the casing downstream of the rotor blade and configured to remove secondary air flow from the primary air flow; an injection opening disposed in the inner surface of the casing upstream of the bleed inlet; an accessory conduit configured to be fluidly coupled to an accessory system of the gas turbine engine; and a plenum fluidly coupled to the bleed inlet, the injection opening, and the accessory conduit, characterized in that the bleed inlet and plenum at least partially define a secondary air flow path for the secondary air flow such that a first portion of the secondary air flow is directed in through the bleed inlet, through the plenum, and out through the injection opening and a second portion of the secondary air flow is directed in through the bleed inlet, through the plenum, and out through the accessory conduit. a bleed inlet disposed in the inner surface of the casing downstream of the rotor blade and configured to remove secondary air flow from the primary air flow; an injection opening disposed in the inner surface of the casing upstream of the bleed inlet; an accessory conduit configured to be fluidly coupled to an accessory system of the gas turbine engine; and a plenum fluidly coupled to the bleed inlet, the injection opening, and the accessory conduit, characterized in that the bleed inlet and plenum at least partially define a secondary air flow path for the secondary air flow such that a first portion of the secondary air flow is directed in through the bleed inlet, through the plenum, and out through the injection opening and a second portion of the secondary air flow is directed in through the bleed inlet, through the plenum, and out through the accessory conduit.