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HONEYWELL AS907 ENGINE SECTIONS
FAN INLET
FAN ROTOR ASSEMBLY HOUSING FRONT FRAME ASSEMBLY HIGH PRESSURE BLEED PORTS
TURBINE ASSEMBLY
SPINNER
CENTER BODY COVER RING ASSEMBLY
INNER RING
ASSEMBLY
EXHAUST
HIGH PRESSURE LOW PRESSURE MIXER
FAN STATOR VANE ASSEMBLY ACCESSORY GEABOX COMPRESSOR ASSEMBLY TURBINE ASSEMBLY NOZZLE
ASSEMBLY
CFO1801002_001
Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6
18-01-01 ENGINE CONSTRUCTION
DESCRIPTION
The AS907 powerplant has two independent major assemblies. The N1 section consists of a fan rotor that is driven through a shaft by a three stage low-pressure turbine. The N2 section is comprised of four axial flow and one centrifugal compressor, combustor, accessory gearbox and a two stage high pressure turbine. The high pressure turbine drives the compressor.
AIRFLOW PATHS
Inlet air is initially accelerated and compressed by the fan and is split into two streams. A large percentage of the fan air exits into the bypass duct. The remainder is directed into the core of the engine. This core airflow passes through a four stage axial compressor and a single stage centrifugal compressor. Exiting the high pressure compressor diffuser the airflow is directed into the in line annular combustor where fuel is injected. The fuel/air mixture is ignited and a continuos com-bustion is maintained. The expanding gases are then directed through the two stage high pressure and three stage interme-diate turbine assembly, driving both rotating groups, and exiting the engine through the mixer nozzle.
AIR INLET COMPRESSOR COMBUSTION TURBINE
SECTION SECTION SECTION SECTION
ACCESSORY DRIVES BY-PASS SECTION LEGEND EXHAUST SECTION
COLD BYPASS AIRFLOW
FWD HOT EXHAUST GASES
CFO1801002_019
V 2
Volume 2 Flight Crew Operating Manual May 06/2005 CSP 100-6 REV 2
18-01-02 ENGINE CONSTRUCTION (CONT)
MAJOR POWERPLANT COMPONENTS
N1 FAN
N1 fan consists of twenty two titanium inserted blades. the fan containment system uses an aluminum honeycomb material surrounded by an aramid fiber wrap.
N1 fan speed is indicated on the EICAS.
N2 COMPRESSOR
The N2 compressor is a variable geometry (VG) axial flow compressor that is mechanically driven by the high-pressure turbine assembly.
The variable geometry (VG) system regulates airflow across the N2 compressor by changing the position of the inlet guide vanes and the stator vane for the inlet and first stage of the compressor. The VG system optimizes the angle of attack of the airflow at the compressor blades and provides compressor stall and surge protection.
The VG inlet guide vanes and stators are programmed by FADEC and positioned by actuators and mechanical linkage. High-pressure fuel from the engine fuel metering unit is used to hydraulically move the actuators.
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