TAKEOFF POWER - 9TH-STAGE AIR
FUEL (PF) CLIMB POWER - 5TH-AND 9TH-STAGE
BLEED VALVE AND
CORE ENGINE
MASTER
AIR MIXTURE
SPEED (N2)
OVERBOARD
FAN FRAME
TC2
BALLSCREEN CRUISE POWER - 5TH-STAGE AIR
DRAIN
MID BOX
ACTUATOR
STRUCTURE
HIGH
PRESSURE
AIR DISCHARGEFUEL MAIN PCR
TO HIGH PRESSURE(PF) ENGINE
TURBINE SHROUDMANIFOLD
CONTROL
TC1
HIGH PRESSUREVBV FEEDBACK
TURBINE CLEARANCEREVERSER ARM
FUEL RETURN AIR VALVE
HIGH PRESSURETURBINE CLEARANCEOVERBOARD
5TH-STAGEVARIABLE BLEED
VBV ACTUATOR VALVE
MAIN DRAIN COMPRESSOR
HPT-LPT COOLINGVALVE (VBV) FEEDBACK
FLEXIBLE INLET TEMPERATURE
CABLE 5TH- STAGEFEEDBACK ROD
SHAFT (CIT)
AIR INLET HIGH PRESSURETURBINE (HPT)VARIABLE
CLEARANCEBLEED VALVE
CONTROL LOW PRESSURETURBINE (LPT) CASECOOLING MANIFOLDFWD
FLEXIBLE
SYNCHRONIZING
SHAFT
(11 UNITS)
CORE COMPARTMENT VENTILATION
PRIMARY FLOW
SUMP VENT AIR
FAN MID-SHAFT AIR CAVITY
SECONDARY FLOW
5TH-STAGE AIR
9TH-STAGE AIR
VARIABLE STATOR5TH AND 9TH-STAGE AIR MIXTURE
VANE ACTUATOR
Engine Air System Schematic
Figure 1
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
ENGINE AIR - TROUBLE SHOOTING
_____________________________
1. Trouble Shoot the Engine Air System
___________________________________
A. Procedure
(1) To trouble-shoot the Engine Air system, refer to the trouble-shooting diagrams in Chapter 71 (AMM 71-00-40/101).
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////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
ACCESSORY COOLING - DESCRIPTION AND OPERATION
_____________________________________________
1. General
_______
A. Accessory cooling consists of engine internal cooling, turbine case cooling, engine external accessories cooling and the high pressure turbine clearance control system.
2. Engine Internal Cooling
_______________________
A. Cooling air for the 3rd-stage disk and 4th-through 9th-stage spool of the high pressure compressor (HPC) rotor is bled from booster discharge.
B. Cooling air for the inner part of the high pressure turbine (HPT) disk is provided by booster discharge air. The outer part of the disk is cooled by HPC discharge air.
C. Cooling air for the HPT blades is bled from the final stage of the HPC.
D. Cooling air for the HPT nozzle vanes is provided by compressor discharge air from the combustion chamber.
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