STATOR CASE HORIZONTAL LEFT FLANGE
LEFT SIDE
K J HGF EDCB A
UT SR
PNM L
STATOR CASE
HORIZONTAL
RIGHT FLANGE
RIGHT SIDE
NACELLE STATIONS OF FLANGES
A = 165.2 D = 174.3 G = 182.3 K = 199.1 N = 216.2 S = 239.9
B = 169.2 E = 176.5 H = 186.0 L = 200.1 P = 221.82 T = 250.4
C = 171.5 F = ----- J = 191.9 M = ----- R = 233.8 U = -----
Engine Flange Locations
Figure 5
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(4) The fan frame, 72-33-00, provides the front handling mounts and is the main forward support for mounting the engine to the strut. Its purpose is to support the fan inlet case and fan, booster and HPC rotors, and to provide ducting for primary and secondary airflows. The fan frame houses the 11 variable bleed valve (VBV) ballscrew actuators and the VBV master ballscrew actuator. The structure rear face supports the HPC casing, the VBV hydraulic fuel gear motor and has provisions for engine mounting. It also supports the accessory drive system and houses the inlet gearbox (IGB) and radial drive shaft. The fan frame is lined with acoustical panels.
3. Core Major Module Assembly (Fig. 3)
__________________________
A. The core major module consists of 8 maintenance modules as follows: high pressure compressor (HPC) rotor, HPC front stator, HPC rear stator, combustion case, combustion chamber, high pressure turbine (HPT) nozzle, HPT rotor, and HPT shroud and 1st-stage LPT nozzle.
(1)
The HPC rotor, 72-34-00, is a 9-stage, high-speed, unitized spool-disk structure. The rotor consists of 5 major parts: the front shaft, the 1st-and 2nd-stage spool, the 3rd-stage disk, the 4th-thru 9th-stage spool and the compressor rear seal. The front shaft, disk and spools are joined at a single bolted joint to form a smooth, rigid unit.
(2)
The HPC front stator, 72-35-00, consists of: front casing halves, extension casing halves, inlet guide vanes (IGV's) and the first 5 stages of stator vanes. The IGV's and the 1st-thru 3rd-stage vanes are variable, the 4th-and 5th-stage vanes are fixed. Actuation of the variable vanes is accomplished with hydraulically actuated bellcrank assemblies mounted on the front compressor stator at the
1:30 and 7:30 o'clock positions.
(3)
The HPC rear stator, 72-36-00, consists of: rear casing halves, liners, 3 stages of fixed vanes, and vane shrouds. The rear stator is located inside the front stator 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.
(4)
The combustion case, 72-41-00, is a fabricated structural weldment located between the HPC and the LPT. It provides structural interface, transmits engine axial load, and provides gas flow path between the compressor and the LPT. The case incorporates compressor outlet guide vanes (OGV's) and a diffuser for the reduction of combustion chamber sensitivity to compressor air velocity profile. It incorporates 6 borescope ports: 4 for inspection of the combustion chamber and 2 for inspection of the HPT nozzle.
(5)
The combustion chamber, 72-42-00, contained in the combustion case, consists of outer and inner cowls, 20 primary and 20 secondary swirl nozzles, dome, and outer and inner liners.
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72-00-00
ALL ú ú C01 Page 8 ú Feb 25/85
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
(6)
The HPT nozzle, 72-51-00, is a single-stage, air-cooled assembly that mounts in the combustion case and directs the gas flow from the combustion chamber onto the blades of the HPT rotor at the optimal angle. Major parts of the nozzle are the 23 nozzle segments, the outer support, the inner support, the aft support and seal assembly, and the stator aft seals.
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