曝光台 注意防骗
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anti-icing , and drives a gearbox used for electrical power and hydraulic
power. The 737 airplane are powered by two wing-mounted CFM 56-3
high bypass-ratio turbofan engine, the engine buildup is identical for left
or right engines.
B737-300/400/500 上的动力装置提供飞机飞行所需的推力及飞机停止
时的反推力，同时为空调、增压系统及防冰系统提供引气，并驱动一
个电源及液压系统使用的齿轮箱。B737 飞机的动力来自于安装于机
翼上的两台CFM56-3 型高函道比的涡扇发动机，左右发动机的结构
是相同的。
(2) The engine is an axial flow turbofan with two rotors and variable stator
vanes. The single-stage fan and three –stage low pressure
compressor(LPC) are driven, via the low –speed(N1) shaft, by a
four-stage low pressure turbine(LPT), the nine stage high pressure
compressor(HPC) is driven, via the high speed(N2) shaft, by a single
stage high pressure turbine(HPT). The two rotors are mechanically
independent of each other. Air entering the engine is divided into a
primary(inner) and a secondary (outer) airstream. After the primary
airstream has been compressed by the LPC and HPC , combustin of fuel
in the annular combustion chamber increases the HPC discharge air
velocity to drive the high and low pressure turbines. The engine is capable
of producing approximately 18,500 to 23,500 pounds of thrust at sea level
static condition.
发动机是一个有两个转子和不同的定子叶片的轴流式涡轮风扇发动
机。单级风扇和三级低压压气机被驱动，经由N1 低速轴，通过一个
四级低压涡轮。九级高压压气机被驱动，经由N2 高速轴，通过一个
单级高压涡轮。两个转子是彼此独立的机械结构。进入发动机的空气
被分成主（内）次（外）两个气流。当主气流被低压压气机和高压压
气机压缩后，环形燃烧室内的燃油开始燃烧，增加了高压压气机的排
气速度以驱动高、低压涡轮。发动机能够产生在海平面条件下大约18，
500 到23，500 磅的推力。
(3) The engine consist of 4 major modules; fan, core, low pressure turbine
and accessory gearbox. The fan major module consists of 4 maintenance
modules, they are fan and booster, No.1 and No.2 bearing support, inlet
gearbox. No.3 bearing and fan frame. The core major module consist of 8
maintenance modules, they are high pressure compressor (HPC) rotor,
HPC front stator, HPC rear stator, combustion outer case, combustion
chamber, high pressure turbine (HPT) nozzle, HPT rotor, HPT shroud and
1st – stage LPT nozzle. The low pressure turbine module consisis of 3
maintenance modules, they are low pressure turbine, low pressure turbine
shaft and turbine frame. The accessory drive module consists of 2
maintenance modules, they are the transfer gear box and the accessory
gearbox.
发动机包含四个组要组件：风扇、主体、低压涡轮及附件齿轮箱。风
扇又包含四个主要的维护部件，它们是：风扇和助推器、1#、2#轴承
支架，入口齿轮箱、3#轴承及风扇骨架。发动机主体主要组件包括8
个维护组件，它们是高压压气机转子、高压压气机前定子、高压压气
机后端定子、燃烧室外壳、燃烧室、高压涡轮喷嘴、高压涡轮转子、
高压涡轮保护罩及第一级高压涡轮喷嘴。低压涡轮组件包括3 个维护
组件，它们是低压涡轮、低压涡轮轴及涡轮支架。附件驱动组件包括
2 个维护组件，它们是传动齿轮箱和附件齿轮箱。
(4) The fan and booster provide two separate air stream, the primary airflow
passes through the inner portion of the fan rotor, then continues through
the booster, the core engine and the LPT, exiting through the core exhaust
nozzle. The secondary airflow passes through the fan outer portion and
exits through the fan discharge duct(fan air ). The fan is located on the
front of the engine, the main function of the fan is to accelerate the air
directed to the engine secondary airflow nozzle. This results in producing
approximately 78% of the total engine thrust.
风扇及助推器提供两个隔离的气流，主气流通过风扇转子内部，接着
穿过助推器、发动机主体及低压压气机，从排放喷嘴核心排出。次级
气流通过风扇外部从风扇排气管道喷出。风扇安装于发动机前端，其
主要功能是给气流加速引导气流到发动机次级气流喷嘴。这样产生的
动力占发动机总推力的78%。
(5) Fuel is delivered to the fuel nozzles at pressure and flow-rate required to
obtain the desired engine thrust. Fuel is pumped from the fuel tank and
enters through the engine fuel shutoff valve. The engine fuel shutoff valve
is controlled by the engine start lever and the engine fire warning switch.
When the engine fuel shutoff valve is closed ,the FUEL VALVE CLOSED
light located on the forward overhead panel illuminates dim.
燃油根据发动机推力的需求在压力作用下流到燃油喷嘴。燃油在油箱
中用泵抽出并流过燃油关断活门。发动机燃油关断活门由发动机起动
手柄和发动机火警开关控制。当发动机燃油关断活门关闭时，位于前
顶置面板上的“FUELVALVE CLOSED”灯燃亮。
(6) Fuel passes from the first stage of the engine driven fuel pump through a
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航空工程英语基础（中英文对照）(94)
