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mounted on a pylon on either side of the rear fuselage.
The engine is an axial flow, dual shaft turbofan, with a 4.0:1 bypass ratio, rated at 14,750 lbs of thrust
at sea level to ISA +20.
The BR 700−710A2−20 engine contains two main rotating assemblies (spools), a single stage low
pressure (LP) fan driven by a two stage turbine and a ten stage high pressure (HP) compressor,
driven by a two stage turbine. The HP spool provides an external drive for the accessories mounted
on the accessory gearbox.
The engine is made up of eight modules as follows:
· Fan assembly.
· Fan case.
· Intermediate case.
· HP Compressor.
· HP Turbine and combustion chamber.
· LP Turbine and shaft.
· Accessory Gearbox (AGB).
· Bypass duct.
Each engine provides bleed air extraction, from either the 5th stage or the 8th stage of compression,
for Air Conditioning and Pressurization, Cowl and Wing antiicing
and/or engine starts.
The engine oil system consists of a lubrication system, a heat management system and an oil
replenishment system.
The fuel system consists of a low pressure system and a high pressure system. Fuel is supplied from
the airplane fuel system via AC and/or DC fuel pumps and engine driven fuel pumps.
Thrust management is controlled throughout all phases of operation by the Full Authority Digital
Electronic Control (FADEC). An Electronic Engine Controller (EEC) is the major part of the FADEC,
interfacing between the airplane and the engine.
Primary engine indications are displayed on EICAS and secondary indications on the STATUS page.
Autothrottle is controlled by the autothrottle computer, located in the IAC and sends signals to
FADEC via the throttle, for thrust commands.
Starting is initiated through the FADEC, to provide normal ground/air starts, alternate ground/air
starts, wet and dry motoring and continuous ignition. Starting can also be performed manually.
The thrust reverser system is operated by the airplane hydraulic system and is controlled by the
EEC.
Vibration monitoring system provides signals indicating N1 (Fan) and N2 (HP compressor) vibration
levels on each engine.
Fire detection is provided by dual element sensor assemblies connected in series to provide two
independent sensing loops. Two fire bottles are located at the rear of the airplane.
POWER PLANT
Rev 3, Apr 25, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
18−10−1
ENGINE ASSEMBLY AND AIRFLOW
The BR 700−710A2−20 engine contains two main rotating assemblies (spools), a single stage low
pressure (LP) fan driven by a two stage turbine and a ten stage high pressure (HP) compressor,
driven by a two stage turbine. The HP spool provides an external drive for the accessories mounted
on the accessory gearbox.
GF1810_001
HP TURBINE
LP COMPRESSOR (FAN) HP COMPRESSOR LP TURBINE
ACCESSORY GEARBOX
All air entering the engine air intake passes through the LP compressor and is divided into two main
flows, the bypass and core airflows. The core airflow passes through the HP compressor to the
annular combustion chamber, which supplies the engine with its fuel requirements. The core airflow
then flows through two stages of HP turbines and two stages of LP turbines into the forced mixer to
mix with bypass air.
The Bypass air passes through the fan outlet guide vanes along the bypass duct to meet with the
core airflow. The combined airstream is exhausted to atmosphere.
GF1810_002
LP COMPRESSOR
HP COMPRESSOR
INTAKE COWL
ACCESSORY
BYPASS DUCT
EXHAUST CONE
EXHAUST NOZZLE
HOT STREAM
(CORE GAS)
COLD STREAM
(BYPASS AIR)
FORCED MIXER
LP TURBINE
HP TURBINE
COMBUSTION
CHAMBER
AIR INLET
ANNULAR
GEARBOX
POWER PLANT
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
18−10−2
ENGINE MODULES
The engine is made up of eight modules as follows:
FAN CASE
INTERMEDIATE CASE
HP COMPRESSOR
HP TURBINE AND COMBUSTOR
FAN ASSEMBLY
ACCESSORY GEARBOX
BYPASS DUCT LP TURBINE
AND SHAFT
GF1810_003
· Fan assembly − Compresses the air entering the engine inlet cowl and feeds a percentage of it
to the core, while the bypass air provides a major portion of the engine’s thrust.
· Fan case − Provides containment in the event of fan blade failure and noise attenuation.
· Intermediate case − Provides a fixed structure for rotating systems and houses the drive for
　
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