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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
Figure 1
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CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
HIGH PRESSURE TURBINE ROTOR - DESCRIPTION AND OPERATION
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1. General
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A. The high pressure turbine (HPT) rotor is a single-stage, air-cooled turbine. Structurally, the rotor consists of the front shaft, the forward air seal, the disk, blades, and the rear shaft (Fig. 1).
2. Front Shaft
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A. The front shaft forms the structural connection between the high pressure compressor (HPC) rotor and the HPT rotor, and supports the aft end of the compressor rotor.
3. Disk
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A. The HPT disk is a forged and machined part that retains the turbine blades in axial dovetail slots. The inner part of the disk is cooled by booster discharge air. The outer part of the disk is cooled by HPC discharge air.
4. Rear Shaft
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A. The rear shaft is bolted to the aft side of the disk at a rabbetted flange and forms the aft support for the HPT rotor. The shaft is supported by the No. 4 roller bearing which rides on the low pressure shaft. Repairable abrasive-coated seals are machined as an integral part of the rear shaft.
5. Front Outer Seal
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A. The front outer seal is bolted between the disk and the front shaft of the rotor. It forms a cavity between itself and the disk to direct HPC discharge air against the disk web and out through the turbine blades. The seal is a labyrinth inclined tooth form that reduces leakage past the seals. The seal teeth are abrasive coated and repairable.
6. Blades
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A. The blades are made of a high temperature nickel alloy. They are of a single-shank design and are individually replaceable. The blades are internally cooled by HPC discharge air that enters through the blade dovetail and exits through holes in the front, sides, and trailing edges. The blades are secured in the disk dovetail slots by front and rear retainer rings bolted to the disk. Seals are inserted under the blade dovetails.
7. Operation
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A. The HPT rotor drives the high pressure compressor rotor and is directly connected to it by a bolted flange to form what is essentially a single core rotor. The rotor is internally cooled by low pressure compressor (booster) discharge air. It has interference rabbetted flanges for rigidity and stability.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / /
CFM56 ENGINES
737-300/400/500/ /MAINTENANCE MANUAL ////////////////////////
BLADES
FRONT BLADE REAR BLADE
RETAINER RETAINER
DISK
FRONT ROTATING
AIR SEAL
REAR SHAFT DAMPER SLEEVE
BALANCE WEIGHT
REAR SHAFT
BALANCE WEIGHT
SHAFT FRONT DAMPER SLEEVE FRONT SHAFT
Figure 1 High Pressure Turbine Rotor Location G-M56-MM-0063(1)-01-B
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