737-300 400 500 AMM 飞机维护手册 ENGINE 发动机 2(71)

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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
HIGH PRESSURE COMPRESSOR REAR STATOR -
____________________________________ DESCRIPTION AND OPERATION
_________________________
 1.  General_______
 A.  The compressor rear stator is a bolted quadrant design consisting of four casing quarters, three stages of fixed vane segments, and vane shrouds (Fig. 1). The rear stator is located inside of the front stator assembly extension and is cantilever-mounted to the rear stator support. The rear stator support outer flange is mounted between the compressor front stator extension and the combustion case.
 2.  Casing Quarters_______________
 A.  The rear casing quarters are a matched set machined from inconel castings. The upper and lower halves are permanently bolted together at the 12 o'oclock and 6 o'clock positions. The casings have internally machined circumferential slots that retain 6th- thru 8th-stage stator vane segments. Between each stage of vanes, machined-in lands are coated with METCO 450 to provide a rub surface for the rotor blades.
 3.  Vanes_____
 A.  The vanes in the 6th- thru 8th-stages are fabricated into segments consisting of several vanes each. These segments are installed in circumferential slots in the casing quarters. Each stage of vanes is shrouded, having removable honeycomb shroud segments attached to their inner ends.
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 72-36-00
 ALL  ú ú C02 Page 1 ú Jun 25/86
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////

G-M56-MM-0143(1)-00-B
High Pressure Compressor Rear Stator Location Figure 1
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 72-36-00
 ALL  ú ú C02 Page 2 ú Jun 25/86
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
COMBUSTION CASE - DESCRIPTION AND OPERATION
___________________________________________
 1.  General
_______
 A.  The combustion case is a fabricated structural weldment located between the high pressure compressor (HPC) and the low pressure turbine (LPT) (Fig. 1). It provides the structural interface, transmits the engine axial load, and provides gas flow path between the compressor and LPT. The case incorporates the HPC outlet guide vanes (OGV) and a diffuser for the reduction of combustion chamber sensitivity to the compressor air velocity profile.
 B.  The combustion case encloses the combustion chamber and high pressure turbine (HPT) components. The combustion chamber, compressor rear stationary (CDP) seal, HPT nozzle assembly, and HPT shroud/1st-stage LPT nozzle assembly are mounted in and structurally supported by the combustion case. The case mounts and positions the 20 fuel nozzles, two igniter plugs, and fuel manifold.
 C.  There are six borescope ports: four for inspection of the combustion chamber and HPT nozzles, and two for inspection of the HPT blades, HPT shrouds, and the 1st-stage LPT blades. The case has four ports for extraction of compressor discharge air for airplane system's use, four ports for introduction of 5th-stage compressor air for LPT cooling, and three ports for HPT shroud cooling air (one for source air and two for introduction of air to the shrouds). There is also one port for the CDP (PS3C) sensing tube which connects to the main engine control (MEC), two ports for spark igniters, and 20 ports for fuel nozzles.
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 72-41-00
 ALL  ú ú C01 Page 1 ú Oct 25/84
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
HPT SHROUD 
COOLING AIR 
AFT FLANGE 
　
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