Abstract: A bleed duct is configured for bleeding fan air from the fan bypass duct in a turbofan aircraft engine. The bleed duct includes a tubular conduit having an inlet and outlet at opposite ends. The conduit is configured in flow area for recovering pressure from speeding fan air bled therethrough. A shroud extends forwardly from the duct inlet for suppressing dynamic pressure oscillations inside the conduit without degrading the pressure recovery.

Abstract: A gas turbine engine rotor disk has a number of annular hubs circumscribed about a centerline and each of the hubs is connected to a disk rim by a web. A plurality of circumferentially spaced apart circular arc dovetail slots are disposed through the rim. Circumferentially extending annular burst slots extend radially through the rim into the dovetail slots between each adjacent pair of the webs. The fan blades have circular arc dovetail roots disposed within the circumferentially spaced apart circular arc dovetail slots. A one piece spinner attached to a forward extension of the disk at a location between a tip and an axially aft spinner end of the spinner. Non-integral platforms circumferentially disposed between the fan blades. A booster spool is connected to the rotor disk by a mounting plate therebetween and the platforms are radially retained to the disk and mounting plates by pins through holes in mounting lugs depending radially inwardly from the platforms.