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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 上的動力裝置提供飛機飛行所需的推力及飛機停止
時的反推力，同時為空調(diào)、增壓系統(tǒng)及防冰系統(tǒng)提供引氣，并驅(qū)動一
個電源及液壓系統(tǒng)使用的齒輪箱。B737 飛機的動力來自于安裝于機
翼上的兩臺CFM56-3 型高函道比的渦扇發(fā)動機，左右發(fā)動機的結(jié)構(gòu)
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.
發(fā)動機是一個有兩個轉(zhuǎn)子和不同的定子葉片的軸流式渦輪風(fēng)扇發(fā)動
機。單級風(fēng)扇和三級低壓壓氣機被驅(qū)動，經(jīng)由N1 低速軸，通過一個
四級低壓渦輪。九級高壓壓氣機被驅(qū)動，經(jīng)由N2 高速軸，通過一個
單級高壓渦輪。兩個轉(zhuǎn)子是彼此獨立的機械結(jié)構(gòu)。進(jìn)入發(fā)動機的空氣
被分成主（內(nèi)）次（外）兩個氣流。當(dāng)主氣流被低壓壓氣機和高壓壓
氣機壓縮后，環(huán)形燃燒室內(nèi)的燃油開始燃燒，增加了高壓壓氣機的排
氣速度以驅(qū)動高、低壓渦輪。發(fā)動機能夠產(chǎn)生在海平面條件下大約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.
發(fā)動機包含四個組要組件：風(fēng)扇、主體、低壓渦輪及附件齒輪箱。風(fēng)
扇又包含四個主要的維護部件，它們是：風(fēng)扇和助推器、1#、2#軸承
支架，入口齒輪箱、3#軸承及風(fēng)扇骨架。發(fā)動機主體主要組件包括8
個維護組件，它們是高壓壓氣機轉(zhuǎn)子、高壓壓氣機前定子、高壓壓氣
機后端定子、燃燒室外殼、燃燒室、高壓渦輪噴嘴、高壓渦輪轉(zhuǎn)子、
高壓渦輪保護罩及第一級高壓渦輪噴嘴。低壓渦輪組件包括3 個維護
組件，它們是低壓渦輪、低壓渦輪軸及渦輪支架。附件驅(qū)動組件包括
2 個維護組件，它們是傳動齒輪箱和附件齒輪箱。
(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.
風(fēng)扇及助推器提供兩個隔離的氣流，主氣流通過風(fēng)扇轉(zhuǎn)子內(nèi)部，接著
穿過助推器、發(fā)動機主體及低壓壓氣機，從排放噴嘴核心排出。次級
氣流通過風(fēng)扇外部從風(fēng)扇排氣管道噴出。風(fēng)扇安裝于發(fā)動機前端，其
主要功能是給氣流加速引導(dǎo)氣流到發(fā)動機次級氣流噴嘴。這樣產(chǎn)生的
動力占發(fā)動機總推力的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.
燃油根據(jù)發(fā)動機推力的需求在壓力作用下流到燃油噴嘴。燃油在油箱
中用泵抽出并流過燃油關(guān)斷活門。發(fā)動機燃油關(guān)斷活門由發(fā)動機起動
手柄和發(fā)動機火警開關(guān)控制。當(dāng)發(fā)動機燃油關(guān)斷活門關(guān)閉時，位于前
頂置面板上的“FUELVALVE CLOSED”燈燃亮。
(6) Fuel passes from the first stage of the engine driven fuel pump through a
　
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