HP Compressor Section
Figure 001
F 『 EEFF : ALL E Page 272-30-00
E E Feb 01/98 E E ECES E HP COMPRESSOR SECTION - REMOVAL/INSTALLATION
F 『
E C F M E
E E
E 56-5B E
E E
____________________________________________
TASK 72-30-00-920-001
Discard Life Limited HP Compressor rotating parts
1. Reason for the Job
__________________
Refer to the MPD TASK: 723000-C1
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
71-00-00-000-042 Removal of the Power Plant
71-00-00-400-042 Installation of the Power Plant
ESM 051102
ESM 723104
ESM 723105
ESM 723106
ESM 723107
ESM 723108
3. Job Set-up
__________
Subtask 72-30-00-010-052
A. Remove the engine (Ref. TASK 71-00-00-000-042).
4. Procedure
_________
Subtask 72-30-00-020-052
A. Remove and discard life limited parts of the high pressure compressor:
- (Ref. ESM 723104) for the HPC Stage 1-2 Spool
- (Ref. ESM 723105) for the HPC Stage 3 Disk
- (Ref. ESM 723106) for the HPC Stage 4-9 Spool
- (Ref. ESM 723107) for the HPC rotor Shaft
- (Ref. ESM 723108) for the HPC CDP Seal
NOTE : (Ref. ESM 051102) for time limits.
____
F 『 EEFF : ALL E Page 40172-30-00
E E Feb 01/04 E E ECES E 5. Close-up
F 『
E C F M E
E E
E 56-5B E
E E
________ Subtask 72-30-00-410-052
A. Install the engine (Ref. TASK 71-00-00-400-042).
F 『 EEFF : ALL E Page 40272-30-00
E E Feb 01/04 E E ECES E HPC ROTOR ASSEMBLY - DESCRIPTION AND OPERATION
F 『
E C F M E
E E
E 56-5B E
E E
______________________________________________
1. General
_______ (Ref. Fig. 001) 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.
2. Description
___________
(Ref. Fig. 001, 002)
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.
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.
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.
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.
F 『 EEFF : ALL E Page 172-31-00
E E Feb 01/98 E E ECES E F 『 E C F M E E E E 56-5B E
Compressor Rotor Assembly
Figure 001
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機維護手冊 AMM ENGINE 發動機 2(16)
