72-52-00
ALL ú ú C01 Page 2 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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.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 ////////////////////////
HIGH PRESSURE TURBINE SHROUD AND 1ST-STAGE LOW PRESSURE
_______________________________________________________ TURBINE NOZZLE - DESCRIPTION AND OPERATION
__________________________________________
1. General_______
A. The high pressure turbine (HPT) shroud and 1st-stage low pressure turbine (LPT) nozzle assembly is located inside the aft end of the combustion case (Fig. 1). It forms the interface between the engine core module and the LPT module. The forward flange of the assembly is rabbetted and bolted to the inner surfaces of the combustion case. The aft flange is bolted between the combustion case aft flange and the LPT stator forward flange.
B. The shroud/nozzle support has a thermal response matched to the rotor to provide tip clearance control and structural stability. An air cavity between the shroud/nozzle support and the combustion case directs mixed 5th- and 9th-stage high pressure compressor bleed air onto the support and the outer surface (backside) of the shrouds. This cooling air maintains closer clearances between the shrouds and the rotor blades. For more detailed information on the HPT clearance control system, refer to 75-24-00.
C. The 1st-stage LPT nozzles direct the core engine exhaust gas onto the 1st-stage LPT blades. An air cavity between the 1st-stage nozzle support and the combustion case directs 5th-stage high pressure compressor (HPC) bleed air through the nozzle vanes for cooling. After passing through the vanes, the air pressurizes and cools the cavity between the aft side of the HPT rotor and the forward side of the LPT rotor.
D. The HPT shroud and 1st-stage LPT nozzle assembly consists of the shroud/nozzle support, HPT shrouds, the 1st-stage nozzles, inner air seal, and stationary air seal.
2. Shroud/Nozzle Support_____________________
A. The shroud/nozzle support forms the outer shell of the assembly and provides an air space or manifold area between the outer shell and the combustion case. HPC bleed air is introduced into the manifold area to provide cooling for the HPT shrouds and the LPT nozzles.
3. HPT Shrouds___________
A. The HPT shrouds have a smooth abrasive rub surface. The shrouds are held in place on the support by retainers and are individually replaceable.
4. 1st-Stage Nozzle and Seals__________________________
A. There are 28 LPT nozzle segments, each having three vanes. The nozzle segments are installed in the shroud/nozzle support and joined to the inner air seal by the stationary air seal which is bolted on the aft face of the inner air seal. The assembly is bolted between the LPT case forward flange and the combustion case aft flange. Borescope ports at
5:30 and 8:30 o'clock positions are provided in the support to allow inspection of the nozzle area.
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72-53-00
ALL ú ú C01 Page 1 ú Jun 25/85
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
SUPPORT SHROUD/NOZZLE AIR SHIELD SPACER
HPT SHROUD CLIP RETAINER 1ST-STAGE LPT NOZZLE
AIR SEAL INNER AIR SEAL STATIONARY
G-M56-SM-1214(1)-01-B
HPT Shroud and 1st-Stage Low Pressure Turbine Nozzle Location Figure 1
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
72-53-00
ALL ú ú C01 Page 2 ú Oct 25/85
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
LOW PRESSURE TURBINE - DESCRIPTION AND OPERATION
________________________________________________
1. General
_______
A. The low pressure turbine (LPT) module (Fig. 1) is a four stage axial type turbine. It is mounted between the core engine and the turbine frame.
B. The module consists of the following major components:
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