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The engine is made up of eight modules as follows:
HP TURBINE AND COMBUSTOR
INTERMEDIATE CASE
HP COMPRESSOR
FAN CASE LP TURBINEBYPASS DUCTFAN ASSEMBLY AND SHAFT
ACCESSORY GEARBOX
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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.
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Fan case . Provides containment in the event of fan blade failure and noise attenuation.
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Intermediate case . Provides a fixed structure for rotating systems and houses the drive for the AGB.
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HP Compressor . Provides a pressurized airflow to the combustion chamber for combustion and cooling purposes and pressurized air for ECS and Wing and Cowl anti-icing.
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HP Turbine and combustion chamber . The two stage HP turbine drives the HP compressor . The combustion chamber mixes fuel and air, for an optimum mixture, for maximum efficiency.
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LP Turbine and shaft . Provides the LP turbine shaft which drives a two stage LP turbine that drives the LP compressor (fan).
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Accessory Gearbox (AGB) . Transmits the motoring force from the engine to the accessories mounted on the AGB. The AGB also transmits motoring from the air starter to the engine during start/crank procedures. The AGB also houses the integral oil tank.
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Bypass duct . Provides a streamlined path for the fan bypass airflow and supports the thrust reverser unit.
GF1810_003
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
The pneumatic system supplies compressed air for Air Conditioning and Pressurization, Ice and Rain Protection and Engine starting. The pneumatic air supply normally comes from the engines (inflight) and the APU or a high pressure ground air supply unit (on the ground).
The engine bleed air system is controlled during all phases of operation by two Bleed Management Controllers (BMC).
The BMC selects air from either the low pressure port (5th stage) or the high pressure port (8th stage) depending on the demand. Under normal operation (inflight), the air is selected from the 5th stage of compression. When the airflow is insufficient, the BMC will select the 8th stage of compression.
L and R ENG BLEED AIR selection, AUTO or ON, is accomplished via the BLEED/AIR COND/ANTI-ICE panel on the overhead panel. A crossbleed valve (CBV) is installed between the left and right pneumatic ducts, which can be opened, automatically by the BMC or manually, to provide bleed air for engine starting. The APU is normal source of bleed air used for engine starting.
GF1810_005
For more information on ECS, see Chapter 2 AIR CONDITIONING AND PRESSURIZATION. For more information on cowl and wing anti-icing, see Chapter 14 ICE AND RAIN PROTECTION.
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005 18.10.4 CSP 700.5000.6
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