CRJ200发动机介绍

nmbobo · 发表于 2012-5-6 23:23:17

庞巴迪的英文原版介绍，对试车人员很有用噢

Canadair Regional Jet 100/200 - Power Plant
1. INTRODUCTION
The aircraft is equipped with two General Electric CF34--3A1 high bypass ratio turbofan engines which have a normal take-off thrust rating of 8,729 pounds flat rated at 21C (70F).In the event of an engine failure during takeoff, an automatic power reserve (APR) system,will increase the thrust on the remaining engine to 9,220 pounds.
The aircraft is equipped with two General Electric CF34--3B1 high bypass ratio turbofan engines which have a normal take-off thrust rating of 8,729 pounds flat rated at 30C (86F).In the event of an engine failure during takeoff, an automatic power reserve (APR) system, will increase the thrust on the remaining engine to 9,220 pounds.<0005>
The engine is a dual rotor assembly consisting of a fan rotor (N1) and a compressor rotor  (N2). The N1 rotor consists of a single-stage fan connected through a shaft to a 4-stage low pressure turbine. The N2 rotor is a 14-stage axial flow compressor connected through a shaft to a 2-stage high pressure turbine.
For normal engine function, intake airflow is accelerated through the single-stage N1 fan and is divided into two airflow paths:
Bypass air -- Air that is ducted around the engine to produce approximately 85% of the engine thrust. On landing, thrust reversers are used to direct the bypass air forward to assist in braking.
Core air -- Air that enters the engine core section is compressed, mixed with fuel and ignited. The expanding hot gases pass through the high pressure turbine which drives the compressor. Air from the high pressure turbine passes through the low pressure turbine which drives the N1 fan. The exhaust gases are then accelerated through the exhaust nozzle to produce a portion of engine thrust.
A variable geometry (VG) system regulates airflow through the compressor by changing the position of the compressor inlet guide vane and the variable geometry stator vanes on the first five stages of the compressor. This is done to prevent compressor stall and surge by optimizing the angle of attack of the vanes. The VG system is controlled by the fuel control unit (FCU) which uses high pressure fuel to hydraulically move two actuators which are mechanically linked to the VG system.
The engine fuel control system consists of a hydromechanical core engine speed (N2) governing system and an electrical fan speed (N1) governing system. The engine is on N2 governing at low power settings and on N1 governing at high power settings.
An accessory gearbox, mounted on the engine, is driven by the N2 rotor. The following components are mounted on and driven by accessory gearbox:
● Engine lubrication pump and integral oil reservoir
●  Alternator (provides N2 speed indication and powers the fuel electronic control unit)
●  Hydraulic pump
●  Engine fuel pump assembly
●  Integrated drive AC generator (IDG)
●  Air turbine starter.
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