Operation - BOMBARDIER Challenger 601-3A CL-600-2B16 Pilot Training Manual

Combustor
The combustor includes a straight-flow an-
nular combustion chamber, a liner, and the
first-stage turbine inlet nozzle.
Eighteen swirl injectors are installed in the
combustion chamber to atomize the fuel.
Initial ignitions supplied by two high-energy
ignitor plugs. The combustor system ensures
proper mixing of the air-fuel mixture, air di-
lution, and flame containment.
Turbine
The turbine section consists of a HP and
LP turbine.
The two-stage HP turbine is rigidly connected
to the HP compressor by the main rotor shaft.
The turbine extracts sufficient energy from
the expanding gases to drive the HP com-
pressor and the accessory gearbox.
The HP compressor and HP turbine assem-
blies form the HP spool of the engine. The rpm
of the HP spool is designated N
The four-stage LP turbine located behind the HP
turbine is rigidly connected to the single-stage
forward fan by a shaft that passes through the
main rotor shaft. The energy extracted by the
LP turbine is used to drive the fan. The remain-
ing energy in the combustion gases is accelerated
rearward to the atmosphere as the core engine's
contribution to the total engine thrust.
The fan and LP turbine combination constitute
the LP spool. The rpm of the LP spool is des-
ignated N .
1
Exhaust
The exhaust frame is located aft of the LP turbine
and consists of an exhaust duct and cone assem-
bly. The exhaust system directs the combustion
gases from the core engine to the atmosphere.
7-4 CL 601-3A
CL-600-2B16 PILOT TRAINING MANUAL
Accessory Gearbox
The accessory gearbox is attached to the lower
side of the front frame. The gearbox is driven
by a tower shaft and bevel gear assembly from
the main (HP spool rotor shaft. The following
accessories are driven by the accessory gearbox:
In addition to these accessories, an air turbine
starter is mounted on the accessory gearbox to
provide engine cranking through a clutch.

OPERATION

Air entering the nacelle inlet (Figure 7-1) is
accelerated rearward by the fan. A large por-
. tion of this air is accelerated to a moderate ve-
2
locity through the fan bypass duct to contribute
the major portion of the thrust. Some of the air
passing through the fan enters the core en-
gine inlet duct and is progressively increased
in pressure as it passes through the 14 stages
of the HP compressor. The compressor outlet
air is directed rearward to the straight-flow an-
nular combustor. A precise amount of the air
enters the combustion chamber where fuel is
added in the proper proportion by the 18 fuel
injectors. Ignition is provided by two high-en-
ergy ignitor plugs until the engine rpm be-
comes self-sufficient. A large portion of the
air provides dilution and insulation for the
combustion liner. The expanding combustion
gases are directed rearward to the turbine sec-
tion. The two-stage HP turbine extracts enough
energy to drive the HP compressor and the
accessory gear system. The expanding gases
continue rearward to the four-stage LP turbine
which extracts sufficient energy to drive the
fan. The remaining core energy is directed to
the atmosphere by the exhaust duct to con-
tribute to the total engine thrust.
FOR TRAINING PURPOSES ONLY
FlightSafety Canada
• N speed control alternator
1
• Integrated-drive generator
• Oil pump
• Fuel pumps and FCU
• Hydraulic pump
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