Hawker Beechcraft Hawker 800XP, Руководство по эксплуатации для пилотов

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Page 2-6
Pilot’s Operating Manual
Original Issue: Feb, 2002
Sub-section 2
ENGINES
Hawker 800XP Pro Line 21
Section III - SYSTEMS DESCRIPTION
DESCRIPTION
The engine is a two-spool-transonic-stage-compressor, front fan jet engine. It is a light weight modular
design for ease of maintenance. The simplicity of the design eliminates the need for variable geometry
inlet guide vanes. This minimizes the weight of the engine, 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.
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 bypass 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 and
continues on to the LP compressor where it is compressed and forced through the interstage diffuser
assembly to the HP compressor where it is further compressed and discharged into the combustion
chamber.
Figure 1
Engine Cutaway View