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 1.  General
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 A.  The combustion chamber is a short, annular, fabricated structure (Fig. 1). The design of the chamber, along with the low pressure fuel injectors and high intensity air, produces a more complete fuel-air mixture to provide a uniform combustion pattern and low thermal stresses. The combustion chamber, contained in the combustion case, consists of outer and inner cowls, 20 primary and secondary swirl nozzles, dome, and outer and inner liners. The outer liner and outer cowl are welded to the dome. The inner liner and inner cowl are bolted to the dome at a common joint.
 2.  Dome
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 A.  The dome is a fabricated part consisting of both cast and fabricated components. Twenty primary swirl nozzles and 20 secondary swirl nozzles with venturies and sleeves are used to provide flame stabilization and mixing of air and fuel. The entire surface of the dome is swept by a film of cooling air.
 3.  Cowls
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 A.  The inner and outer cowls are designed to provide uniform and predictable air flow profiles to the combustion chamber.
 4.  Liners
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 A.  The outer and inner liners are of an integral design with panel overhangs which contain closely spaced cooling holes that provide film cooling. Dilution holes are employed in the liners to provide additional mixing and cooling air which lowers the gas temperature at the turbine inlet. The outer liner contains two ports for the spark igniters.
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 72-42-00
 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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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 ////////////////////////
SECONDARY 
SWIRL NOZZLE 
DOME 
OUTER 
LINER  VENTURI 
COOLING 
HOLES 

DOME 
COWL INNER  LINER INNER 
INNER 
SUPPORT 
FLANGE 

COWL OUTER  (2 LOCATIONS) IGNITER FERRULE 
G-M56-MM-0065(1)-02-B
Figure 1 Combustion Chamber Location 

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 72-42-00
 ALL  ú ú C01 Page 2 ú Feb 25/85
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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 TURBINE NOZZLE - DESCRIPTION AND OPERATION
________________________________________________________
 1.  General
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 A.  The high pressure turbine (HPT) nozzle 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 optimum angle (Fig. 1). The major components of the nozzle are the 23 nozzle segments, outer support, and inner support. The aft support and seal assembly, and the aft stator seals, while not integral components of the HPT nozzle module, are included since they attach to the HPT stator.
 2.  Nozzle Segments
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 A.  Each HPT nozzle segment is made up of two vanes brazed into inner and outer platforms. Each vane is a cast shell divided into forward and aft compartments by an inner rib. The vanes and bands are cooled by compressor discharge air entering the vane compartments through inserts in the inner and outer ends of vanes and exiting through the vane leading and trailing edges. The vanes and platforms are made of high strength cobalt base alloy with a protective coating on vane airfoils and platform flowpath surfaces.
 3.  Inner and Outer Supports
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 A.  The nozzle inner and outer supports are both one-piece, nickle base alloy rings. The major portion of the nozzle axial load is carried by the inner support through the bolted flanges of the support and nozzle inner platforms. The outer support carries a minor portion of the load.
 4.  Aft Outer Support and Seal
__________________________
 A.  The aft outer support is a one-piece, nickel base alloy ring that provides support for the four step honecomb seal. The honeycomb seal mates with the HPT rotor inducer seal to help maintain the proper amount of cooling air flow and rotor thrust.
　
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