包 CFM56-5B TRAINING MANUAL
H
CFM56-5B5 (22,000 lbs) CFM56-5B5/2 (22,000 lbs) CFM56-5B5/P (22,000 lbs) CFM56-5B5/2P (22,000 lbs) CFM56-5B6 (23,500 lbs) CFM56-5B6/2 (23,500 lbs) CFM56-5B6/P (23,500 lbs) CFM56-5B6/2P (23,500 lbs) CFM56-5B7/P (27,000 lbs)
CFM56-5B4 (27,000 lbs) CFM56-5B4/2 (27,000 lbs) CFM56-5B4/P (27,000 lbs) CFM56-5B4/2P (27,000 lbs)
CFM56-5B1 (30,000 lbs) CFM56-5B1/2 (30,000 lbs) CFM56-5B1/P (30,000 lbs) CFM56-5B1/2P (30,000 lbs) CFM56-5B2 (31,000 lbs) CFM56-5B2/2 (31,000 lbs) CFM56-5B2/P (31,000 lbs) CFM56-5B2/2P (31,000 lbs) CFM56-5B3/P (33,000 lbs) CFM56-5B3/2P (33,000 lbs)
CFM56-5B FOR AIRBUS APPLICATIONS
CTC-063-002-02
Page 5
EFFECTIVITY
INTRO
Dec 00
BASIC ENGINE
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
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)
INTRO
Page 6Dec 00
BASIC ENGINE
EFFECTIVITYALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
CFM56-5B包H TRAINING MANUAL
CFM56-5B
CTC-063-003-01
Page 7
EFFECTIVITY
INTRO
Dec 00
BASIC ENGINE
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
THIS PAGE INTENTIONALLY LEFT BLANK
Page 8
EFFECTIVITY
INTRO
Dec 00
BASIC ENGINE
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
包 CFM56-5B TRAINING MANUAL
H
ENGINE GENERAL
Page 1
EFFECTIVITY
72-00-00
Dec 00
BASIC ENGINE
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
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).
中國航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：TRAINING MANUAL CFM56-5B BASIC ENGINE(7)
