Installation
QAD Ring - Fuel Pump, Removal 216
Seal - Magnetic, Installation 206
Seal - Magnetic, Removal 201
Seal - Sealol, Installation 212
Seal - Sealol, Removal 210
INLET GEARBOX 72-61-00
Description and Operation 1 ALL General 1 Bearing - Thrust (No. 3 Ball) 1 Gear - Horizontal Bevel 1 Gear - Radial Bevel 1
TRANSFER GEARBOX 72-62-00
Description and Operation 1 ALL General 1 Gearbox - Transfer 1 Shaft - Horizontal Drive 5 Shaft - Radial Drive 1
GEARBOX - TRANSFER 72-62-01 Removal/Installation 401 ALL Inspection/Check 601 ALL
HOUSING - RADIAL DRIVE SHAFT, 72-62-02
INNER HOUSING AND OUTER Removal/Installation 401 ALL Inspection/Check 601 ALL
SHAFT - HORIZONTAL DRIVE 72-62-03
Maintenance Practices 201 ALL
ACCESSORY GEARBOX 72-63-00
Description and Operation 1 ALL General 1 Housing - Accessory Gearbox 1 Train - Gear 1
Adjustment/Test 501 ALL Inspection/Check 601 ALL Approved Repairs 801 ALL
72-CONTENTS
CBEJ Page 7 Mar 12/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
ENGINE - DESCRIPTION AND OPERATION
__________________________________
1. General
_______
A. The CFM56-3 is a high bypass, dual-rotor, axial flow turbofan engine. Basic engine specifications are provided in Fig. 1 and 2.
B. The integrated fan and booster (low pressure compressor - LPC) is driven by a 4 stage low pressure turbine (LPT) (Fig. 4). A single-stage high pressure turbine (HPT) drives the 9 stage high pressure compressor (HPC). The two rotors are mechanically independent of each other. Air entering the engine is divided into a primary (inner) airstream and a secondary (outer) airstream (Fig. 4). After the primary airstream has been compressed by the LPC and HPC, combustion of fuel in the annular combustion chamber increases the HPC discharge air velocity to drive the high and low pressure turbines. An accessory drive system off the N2 rotor drives engine and airplane accessory components.
C. The engine consists of 4 major sections: fan major module, core engine major module, LPT major module and accessory drive system (Fig. 4). It also includes the following components which are not included in any section: spinner front cone, LPT shaft plug and coupling nut, aft rotating air/oil separator, and oil inlet cover. Nacelle stations are provided in Fig. 5.
2. Fan Major Module (Fig. 3)
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A. The fan major module consists of 4 maintenance modules: fan and booster, No. 1 and No. 2 bearing support, inlet gearbox and No. 3 bearing, and fan frame.
(1)
The fan and booster module, 72-31-00, consists of a single-stage fan rotor and a 3-stage axial booster, cantilever-mounted at the rear of the fan disk. The module is comprised of the following major parts: spinner rear cone, fan disk, fan blades, booster rotor, and booster stator.
(2)
The No. 1 and No. 2 bearing support module, 72-32-00, supports both the fan and booster rotor assemblies and is bolted to the fan frame front face. The module is comprised of the following major parts: No. 1 bearing support, No. 1 ball bearing, No. 2 bearing support, No. 2 bearing roller bearing, oil manifold assembly, external piping, and fan shaft.
(3)
The inlet gearbox (IGB), 72-61-00, is located in the fan frame sump and is bolted to the forward side of the fan frame aft flange. The gearbox contains a horizontal bevel gear, a radial bevel gear, and the core engine thrust bearing (No. 3 ball bearing).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
72-00-00
ALL ú ú C01 Page 1 ú Feb 25/85
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
ENGINE GENERALType Thrust Class Number of Combustion Chambers Type of Combustion Chamber Type of Compressor
Direction of Rotation (Both Rotors)
Type of Turbine
Engine Weight Bare Engine Engine (with QEC) Engine Length
Axial-flow, gas turbine turbofan
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