Patent ID: 7249929

Claim:
A gas turbine engine comprising: a fan; a compressor along a core flow path and having: a plurality of rows of blades; a plurality of rows of vanes; and a plurality of shroud rings, at least a bleed one of which defines a plurality of bleed ports; a structural hub downstream of the shroud rings and secured relative to the shroud rings; a structural case extending from an aft joint with the structural hub to a fore joint with a joined one of the shroud rings and having a plurality of valve ports, at least a portion of the structural case extending structurally between the fore and aft joints, wherein: a bleed flowpath through the bleed ports and the valve ports further extends through the structural hub to join a fan bypass flow; a valve element shiftable between: a first condition in which the valve element blocks communication through the valve ports; and a second condition in which the valve element does not block said communication.