DOC AIRBUS | AMM A320FHPT ROTOR ASSEMBLY - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
1. General
The high pressure turbine (HPT) rotor is a single-stage, air-cooled, high-efficiency turbine. Structurally the rotor consists of the front shaft, the forward air seal, the disk, and the rear shaft.
** ON A/C NOT FOR ALL The high pressure turbine (HPT) rotor is a single-stage, air-cooled, high-efficiency turbine. Structurally the rotor consists of the front shaft, the forward air seal, the disk, and the rear shaft.
High Pressure Turbine Rotor2. Description
A. Front Shaft
The front shaft forms the structural connection between the compressor rotor and the HPT rotor, and supports the aft end of the compressor rotor.
The front shaft forms the structural connection between the compressor rotor and the HPT rotor, and supports the aft end of the compressor rotor.
B. Disk
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 compressor discharge air.
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 compressor discharge air.
C. Rear Shaft
The rear shaft is bolted to the aft side of the disk at a rabbeted 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.
The rear shaft is bolted to the aft side of the disk at a rabbeted 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.
D. Front Outer Seal
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 compressor 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.
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 compressor 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.
E. Blades
The 80 HPT blades are made of a high temperature nickel alloy that has a high strength to weight ratio and are made in a single-crystal. Each blade has its own shank and dovetail. Compressor discharge air flows through the blades to decrease the temperature of the metal. The air flows through the root entrance holes, through eight internal cavities and out the holes in the leading edge, airfoil, tip, and trailing edges. The blades have a Thermal Barrier Coating (TBC) on the airfoil and platform to decrease the temperature of the metal. The TBC is a white ceramic that has a thickness of 0.006 in. (0.15 mm).
POST SB CFM SB 72-0821
If the engine has incorporated the CFM56-5B/3 PIP (Performance Improvement Package), GE SB 72-0809 and 72-0810, the HPT rotor disk will have 76 HPT blades.
END OF POST SB CFM SB 72-0821
The 80 HPT blades are made of a high temperature nickel alloy that has a high strength to weight ratio and are made in a single-crystal. Each blade has its own shank and dovetail. Compressor discharge air flows through the blades to decrease the temperature of the metal. The air flows through the root entrance holes, through eight internal cavities and out the holes in the leading edge, airfoil, tip, and trailing edges. The blades have a Thermal Barrier Coating (TBC) on the airfoil and platform to decrease the temperature of the metal. The TBC is a white ceramic that has a thickness of 0.006 in. (0.15 mm).
POST SB CFM SB 72-0821
If the engine has incorporated the CFM56-5B/3 PIP (Performance Improvement Package), GE SB 72-0809 and 72-0810, the HPT rotor disk will have 76 HPT blades.
END OF POST SB CFM SB 72-0821