POWERPLANT
AIRPLANE
OPERATIONS
MANUAL
2-10-05
Page
2
Code
01
DECEMBER 20, 2002
MAIN ASSEMBLIES
FAN MODULE
Air enters the engine through the fan case inlet and is compressed by
a 24-blade, single-stage fan. The compressed air is split into a bypass
stream, which bypasses the core through the outer bypass duct, and a
core stream that enters the high-pressure compressor.
HIGH-PRESSURE COMPRESSOR
The compressor rotor consists of 14 stages of individual wheel
assemblies, compressor shaft, compressor-to-turbine shaft, and
compressor tiebolt. Compressor Variable Geometry (CVG) stators are
provided for stages 1 through 5 and for the inlet guide vanes. These
stators are driven by servo actuators controlled by the FADECs. High-
pressure compressor bleed air tappings are available at the 9
th
and
14
th
stages (compressor discharge).
A combustion liner assembly mixes air and fuel to support combustion,
and delivers a uniform, high-temperature gas flow to the turbine.
HIGH-PRESSURE TURBINE (HPT)
The High Pressure Turbine converts the gas flow coming from the
combustion liner into usable mechanical energy to drive the
compressor.
LOW-PRESSURE TURBINE (LPT)
The Low-Pressure Turbine is located downstream of the High-
Pressure Turbine and extracts energy from the gas path to drive the
fan. The LPT is connected to the fan by means of a shaft extending
through the entire high-pressure spool and the compressor assembly.
Air exiting the LPT mixes with the bypass air and provides thrust.
EXHAUST CONE AND MIXER
The forced air mixer provides the mixing for the engine bypass and
core gas-flow streams and sets the fan operating line for all operating
envelope conditions. The Thrust Reversers deflect the exhaust
providing reverse thrust.
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