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 4.  Blades
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 A.  The 1st-through 3rd-stage blades are made of a titanium alloy. The 4th-through 9th-stage blades are made of a nickel alloy. The first three stages of blades are secured in the disk and spool axial slots by retaining rings; the blades in the 4th-thru 9th-stages are secured in the circumferential grooves by locking lugs. All blades are replaceable without disassembling the rotor.
 5.  Rear Seal
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 A.  The compressor rotor rear rotating (CDP) air seal is a one-piece nickel alloy forging with abrasive, protective-coated sealing teeth. The seal is mounted to the aft flange of the 4th-through 9th-stage spool by a tight fitting rabbet diameter and is axially clamped by the bolts and nuts securing the forward flange of the high pressure turbine rotor to the compressor.
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 ALL  ú ú C01 Page 1 ú Oct 20/83
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
1ST-STAGE 
BLADES  AIR SEAL
1ST-AND 2ND-
STAGE SPOOL 
FRONT 
SHAFT  9TH-STAGE 
BLADES 

G-M56-MM-0069(1)-01-C
High Pressure Compressor Rotor Location Figure 1
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 ALL  ú ú C01 Page 2 ú Feb 20/84
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
HIGH PRESSURE COMPRESSOR FRONT STATOR - DESCRIPTION AND OPERATION
_________________________________________________________________
 1.  General
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 A.  The high pressure compressor front stator consists of the front casing halves, the extension casing halves, the inlet guide vane (IGV), and the first five stages of stator vanes (Fig. 1).
 2.  Front Stator Casing
___________________
 A.  The front casing halves are a matched set machined from a titanium forging. The extension casing halves are also a matched set and are machined from an Inco 706 stainless steel forging. The extension case attaches to the front case with bolts and nuts, nine of which are welded in place forming an inseparable assembly. The lower halves of the front casing and the extension casing contain ports for borescope inspection of internal areas. The front stator forms the load carrying structure between the fan frame and the combustion case. Bleed air is extracted from pads on the front case and extension for airplane systems' use, and for high pressure turbine (HPT) and low pressure turbine (LPT) cooling.
 3.  Stator Vanes
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 A.  The IGV and 1st- through 3rd-stage vanes are variable; the 4th- and 5th-stage vanes are fixed. All stages of variable vanes are shrouded. The IGV shrouds are made of epoxy resins and are in two 180 degree sections. Shrouds for 1st- through 3rd-stages are made of aluminum and are in 12 segments. The fixed vanes in the 4th- and 5th-stages are fabricated into segments consisting of several vanes each. The fixed vanes have honeycomb shroud segments attached to their inner ends.
 4.  Variable Vane Actuation
_______________________
 A.  Actuation of the variable vanes is accomplished by hydraulically actuated bellcrank assemblies mounted on the front compressor stator at the 1:30 and 7:30 o'clock positions. Adjustable linkages connect the bellcranks to actuation rings. Lever arms attached to the variable vanes connect to the actuation rings. Fuel from the main engine control (MEC) operates the hydraulic actuators.
 5.  Liners
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 A.  Liners are installed between each stage of vanes to provide a rubbing surface for the rotor blades.
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 ALL  ú ú C02 Page 1 ú Oct 25/86
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
　
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