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庞巴迪环球5000公务机机组操作手册 Bombardier Global-动力装置(3)

时间:2011-11-11 09:42来源:蓝天飞行翻译 作者:公务机 点击:
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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.
Rev 3, Apr 25, 2005 Flight Crew Operating Manual Volume 2
POWER PLANT
 
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.
HP COMPRESSOR LP  TURBINE
LP COMPRESSOR (FAN)
HP TURBINE
ACCESSORY GEARBOX
GF1810_001
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.
HP TURBINE
HP COMPRESSOR  COMBUSTION ANNULAR  LP TURBINE 
CHAMBER 
LP COMPRESSOR  FORCED MIXER 

COLD STREAM (BYPASS AIR)
AIR INLET
HOT STREAM
(CORE GAS)
EXHAUST NOZZLE
INTAKE COWL BYPASS DUCT EXHAUST CONE
ACCESSORY
GEARBOX

Volume 2 Flight Crew Operating Manual
GF1810_002
Rev 2A, Apr 11, 2005
POWER PLANT
 
ENGINE MODULES
 
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