DOC AIRBUS | AMM A320FHPC ROTOR ASSEMBLY - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
1. General
The compressor rotor (C/R) is a 9-stage, high-speed, unitized spool-disk structure. The rotor consists of 5 major parts : front shaft, stages 1-2 spool, stage 3 disk, stages 4-9 spool, and C/R rear (compressor discharge pressure (CDP)) rotating air seal. Spools are assembled by inertia welding.
The front shaft, disk, and spools are joined at a single bolted joint to form a smooth, rigid unit. Interfering rabbeted diameters are used for proper positioning of parts and for rotor stability.
** ON A/C NOT FOR ALL The compressor rotor (C/R) is a 9-stage, high-speed, unitized spool-disk structure. The rotor consists of 5 major parts : front shaft, stages 1-2 spool, stage 3 disk, stages 4-9 spool, and C/R rear (compressor discharge pressure (CDP)) rotating air seal. Spools are assembled by inertia welding.
Compressor Rotor AssemblyThe front shaft, disk, and spools are joined at a single bolted joint to form a smooth, rigid unit. Interfering rabbeted diameters are used for proper positioning of parts and for rotor stability.
2. Description
A. Front Shaft
The front shaft is bolted between stages 1-2 spool and stage 3 disk, and is the forward support for the rotor. The shaft is splined to and secured to the inlet gearbox (IGB) horizontal bevel gear by a coupling nut. The IGB contains the thrust bearing for the core engine. The front shaft is made of titanium alloy.
The front shaft is bolted between stages 1-2 spool and stage 3 disk, and is the forward support for the rotor. The shaft is splined to and secured to the inlet gearbox (IGB) horizontal bevel gear by a coupling nut. The IGB contains the thrust bearing for the core engine. The front shaft is made of titanium alloy.
B. Disk and Spools
The stages 1-2 spool and stage 3 disk are made of titanium alloy forgings and retain the stages 1, 2, and 3 blades in axial slots. The stages 4-9 spool is made of a nickel alloy and retains stages 4 through 9 blades in circumferential grooves. The disk and stages 4-9 spool are internally cooled by low pressure compressor (booster) discharge air which enters the rotor through holes in the front shaft. Abrasive coated seals between the rotor blade stages improve compressor performance.
The stages 1-2 spool and stage 3 disk are made of titanium alloy forgings and retain the stages 1, 2, and 3 blades in axial slots. The stages 4-9 spool is made of a nickel alloy and retains stages 4 through 9 blades in circumferential grooves. The disk and stages 4-9 spool are internally cooled by low pressure compressor (booster) discharge air which enters the rotor through holes in the front shaft. Abrasive coated seals between the rotor blade stages improve compressor performance.
C. Blades
Blades in stages 1, 2 and 3 are made of a titanium alloy. Blades in stages 4 through 9 are made of a nickel alloy. The first 3 stages of blades are secured in the disk and spool axial slots by retaining rings ; blades in the stages 4-9 spool are secured in the circumferential grooves by locking lugs. All blades are replaceable without disassembling the rotor.
Blades in stages 1, 2 and 3 are made of a titanium alloy. Blades in stages 4 through 9 are made of a nickel alloy. The first 3 stages of blades are secured in the disk and spool axial slots by retaining rings ; blades in the stages 4-9 spool are secured in the circumferential grooves by locking lugs. All blades are replaceable without disassembling the rotor.
D. Rear Seal
The compressor rotor rear rotating (CDP) air seal is a one-piece nickel alloy forged part with abrasive, protective-coated sealing teeth. The seal is mounted to the aft flange of the stages 4-9 spool by a tight fitting rabbet diameter and is axially clamped by the bolts and nuts securing the forward flange of the high pressure turbine rotor to the compressor.
The compressor rotor rear rotating (CDP) air seal is a one-piece nickel alloy forged part with abrasive, protective-coated sealing teeth. The seal is mounted to the aft flange of the stages 4-9 spool by a tight fitting rabbet diameter and is axially clamped by the bolts and nuts securing the forward flange of the high pressure turbine rotor to the compressor.