Description and Operation 1 ALL General 1 Light - Filter Bypass Warning 1 Switch - Fuel Filter 1
Differential Pressure
Operation 1 Adjustment/Test 501 ALL SWITCH - FUEL FILTER 73-34-01
DIFFERENTIAL PRESSURE Removal/Installation 401 ALL
73-CONTENTS
CBEJ Page 4 Nov 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
ENGINE FUEL AND CONTROL - DESCRIPTION AND OPERATION
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1. General
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A. Engine Fuel and Control includes these systems:
(1)
Fuel Distribution System, AMM 73-11-00.
(2)
Fuel Control System, AMM 73-21-00.
(3)
Fuel Flow Indicating System, AMM 73-31-00.
(4)
Fuel Filter Bypass Warning System, AMM 73-34-00.
B. The fuel distribution system is a hydromechanical system which provides and controls fuel flow to the engine combustor. The system also powers and schedules variable stator vane and variable bleed valve positions to maintain maximum engine performance within stall margin, rotor speed, compressor discharge pressure and turbine temperature limits. High pressure rotor speed (N2) is controlled and limited by the main engine control (MEC) by metering fuel to the engine fuel nozzles. Fan and low pressure rotor (N1) rotation is obtained from low pressure turbine energy extraction and is mechanically independent of N2 rotation. N1 speed is controlled indirectly by controlling N2 speed, which is achieved by the MEC by integrating inputs of thrust lever [power lever angle (PLA)], core compressor inlet temperature (T25), fan inlet temperature (T2), fan inlet pressure (PS12) and N2 rotor speed.
C. The fuel control system includes the MEC and sensors mentioned above and the components that follow:
(1)
Engine driven fuel pump, which receives fuel from the airplane fuel system and pressurizes it for use by the engine fuel and control system components.
(2)
Oil/fuel heat exchanger, which cools the engine lubricating oil (AMM 79-21-02).
(3)
Power Management Control (PMC), which provides an electronic adjustment of the MEC to obtain optimum power settings for take-off, climb and cruise flight conditions without constant adjustment of the thrust lever by the flight crew. The PMC is equipped with automatic and manual disabling controls.
(4)
Fuel filter, which ensures clean fuel is provided to the MEC.
(5)
Servo fuel heater, which maintains fuel temperatures at a high enough level to prevent ice from entering and damaging the MEC servos.
(6)
Fuel plumbing, which provides the means to route fuel between the MEC and fuel manifold.
(7)
Fuel manifold, which distributes fuel to the 20 fuel nozzles.
(8)
Fuel nozzles, which spray fuel into the combustion section of the engine core.
D. The fuel flow indicating system monitors fuel flow rate and total fuel quantity used. This information is provided by a fuel flow transmitter located in the fuel plumbing between the MEC and fuel manifold.
E. The fuel filter bypass warning system is provided to warn the flight crew of impending fuel filter bypass resulting from a clogged fuel filter.
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本文鏈接地址：737-300 400 500 AMM 飛機維護手冊 發動機燃油和控制(2)
