CFM56-5B TRAINING MANUAL BASIC ENGINE

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ENGINE GENERAL CONCEPT

The CFM56-5B engine consists of two independent
rotating systems :
- The low pressure system rotational speed is
designated N1.
- The high pressure system rotational speed is
designated N2.
The engine rotors are supported by 5 bearings, identified
in manuals as numbers 1 thru 5, where No. 1 is the most
forward and No. 5 the most aft. These bearings are
housed in 2 dry sump cavities provided by the fan and
turbine frames.
Engine structural rigidity is obtained with short lengths
between two main structures (frames).
The accessory drive system uses energy from the high
pressure compressor rotor to drive the engine and
aircraft accessories. It also plays a major role in starting.

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on condition monitoring

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ENGINE GENERAL CONCEPT

The CFM56-5B engine uses a maintenance concept
called ‘On Condition Maintenance’. This means that the
engine has no periodic overhaul schedules and can
remain installed under the wing until something important
occurs, or when lifetime limits of parts are reached.
For this reason, to monitor and maintain the health of the
engine, different tools are available, which are :
- Engine performance trend monitoring
- Borescope inspection
- Lubrication particles analysis
- Spectrometric Oil Analysis Program (S.O.A.P)
- Engine vibration monitoring system

 

borescope  管道镜

spectrometric 光谱测定的,度谱的,分光仪的,光谱仪的

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design and operation

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aircraft pylon
飞机外挂架

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ENGINE GENERAL CONCEPT
The CFM56-5B engine is a high by-pass, dual rotor, axial
flow turbofan. It is supported by the wing pylon and
streamlined by cowlings.
Air is sucked into the intake by the fan blades and split
into two flow paths, the Primary and the Secondary.
The primary airflow passes through the inner portion of
the fan blades and is directed into a booster (LPC).
The airflow then enters a High Pressure Compressor
(HPC) and goes to a combustor. Mixed with fuel and
ignited, the gas flow provides energy to a High Pressure
Turbine (HPT) and a Low Pressure Turbine (LPT).
The secondary airflow passes through the outer portion
of the fan blades, the Outlet Guide Vanes (OGV’s) and
exits through the nacelle discharge duct, producing
approximately 80 % of the total thrust. It also plays a role
in the thrust reverser system.

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CFM-56-5B

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CFM56-5B MAIN CHARACTERISTICS

Type of engine Turbo fan
Arrangement Two spool axial flow
Rotation Clockwise (ALF)
Compressors
- Low Pressure:
Fan Stage 1
Booster Stages 2 to 5
- High Pressure:
HP Compressor Stages 1 to 9
Combustion chamber Annular SAC (option DAC)
Turbines
- HP Turbine Single stage
- LP Turbine Four stages
Weight 2381 kg (5249 lbs)
Overall dimensions
- Length 2.94m (115.86 ins)
- Height 2.14m (83.65 ins)
- Width 1.97m (77.88 ins)

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Engine Applications
The following chart shows the various engine models for
the Airbus A319-A320-A321 aircraft.
The engine used on these aircraft is the CFM56-5B,
which has several different thrust ratings ranging from
22000 to 33000 lbs.

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CFM INTERNATIONAL ORGANIZATION