DESCRIPTION
The engine is a two-spool-transonic-stage-
compressor, front fan jet engine. It is a light
weight modular design for ease of mainte-
nance. The simplicity of the design eliminates
the need for variable geometry inlet guide
vanes. This minimizes the weight of the en-
gine, the possibility of the inlet vanes icing up
is reduced and the noise is also reduced. Use
of a reverse flow combustion chamber reduces
the overall length of the engine and provides
a cool skin concept for the external surfaces
of the turbine section. (See Figure 7-3.)
FAN
The fan is an axial flow unit that moves large
quantities of air into the bypass and core
inlets. The bypass section consists of the
fan spinner support, fan rotor assembly, fan
bypass stator, fan duct assembly and the by-
pass fan support and shaft section. The fan
is driven by the low pressure (N
1
) spool
through the planetary gear section.
Compressor Section
Air enters the engine through the air inlet
section located immediately aft of the fan
bypass section.
From the air duct it enters the compressor sec-
tion at the LP compressor where it is com-
pressed and forced through the interstage
diffuser assembly to the HP compressor. Air
is further compressed by the high pressure
compressor and is discharged into the com-
bustion chamber.
7-3
FOR TRAINING PURPOSES ONLY
HAWKER 800 XP
PILOT TRAINING MANUAL
FlightSafety
international
Figure 7-3. Engine Cutaway
Summary of Contents for 800 XP
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