Stainless steel inserts are mounted between the stator vane
rows of stages two through five to reduce compressor housing erosion
from sand and foreign objects. At the rear of the axial compressor
housings, a series of machined passages are provided to allow
bleeding of compressor air. This bleeding of air is controlled by an
interstage airbleed system. The centrifugal impeller housings have a
hollow core which allows compressor bleed air to flow through them to
the customer bleed air and antiicing systems.
Externally the housing provides mounting points for limited
engine and airframe accessories. Because of the structural support
provided by the compressor housing, only one half may be removed at a
time.
The dual compressor rotor assembly, figure 4.13, consists of
five axial compressor rotor disks and one centrifugal impeller. The
axial compressor blades are mounted in dovetail slots, machined into
the rotor disks. Roll pins and lock plates, which act as shims,
secure the blades to the disk. The centrifugal impeller is
constructed of titanium for a high strengthtoweight ratio. The
compressor rotor assembly is attached to the rear shaft and connects
to the gas
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