(0.64 and 0.71 m.daN).
(3) Wirelock the plugs with lockwire 0.032 in. (0.8mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8mm) dia (Material No. CP8002).
(4) If necessary, install the fuel drain tube to the fuel nozzle adjacent to the 6 o'clock borescope plug. TORQUE the coupling nuts on the fuel drain tube to between 120 and 135 lbf.in (1.35 and 1.52 m.daN) and safety with lockwire 0.032 in. (0.8mm) dia (Material No. CP8001) or lockwire 0.032 in. (0.8mm) dia (Material No. CP8002)
(5) Install the spark igniters (Ref. TASK 74-21-30-400-002).
Subtask 72-51-00-790-051
F. Do a fuel nozzle leak check.
(1) If you removed the drain tube from the fuel nozzle adjacent to the o'clock borescope plug, do a fuel nozzle leak check (Ref. TASK 73-11-40-790-002)
F 『 EEFF : ALL E Page 61972-51-00
E E Feb 01/02 E E ECES E 5. Close-up
F 『
E C F M E
E E
E 56-5B E
E E
________ Subtask 72-51-00-410-056
A. Close Access
(1) Make sure that the work area is clean and clear of tool(s) and other items.
(2) Close the thrust reverser doors: (Ref. TASK 78-36-00-410-040). FOR 1000EM1 451AL, 452AR FOR 1000EM2 461AL, 462AR
(3) Remove the access platform(s). Subtask 72-51-00-440-052
B. Make the thrust reverser serviceable (Ref. TASK 78-30-00-081-041). Subtask 72-51-00-410-057
C. Close Access
(1) Close the fan cowl doors: (Ref. TASK 71-13-00-410-040)
FOR 1000EM1
437AL, 438AR
FOR 1000EM2
447AL, 448AR
(2) Remove the warning notice(s).
F 『 EEFF : ALL E Page 62072-51-00
E E Feb 01/98 E E ECES E
F 『
E C F M E
E E
E 56-5B E
E E
HPT ROTOR ASSEMBLY - DESCRIPTION AND OPERATION
______________________________________________
1. General
_______ (Ref. Fig. 001) 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.
2. 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.
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.
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.
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.
E. Blades
(Ref. Fig. 002) R The 80 HPT blades are made of a high temperature nickel alloy that has a R high strength to weight ratio and are made in a single-crystal. Each R 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
R ceramic that has a thickness of 0.006 in. (0.15 mm).
F 『 EEFF : ALL E Page 172-52-00
E E Nov 01/04 E E ECES E F 『 E C F M E E E E 56-5B E
High Pressure Turbine Rotor
Figure 001
F 『 EEFF : ALL E Page 272-52-00
E E Feb 01/98 E E ECES E F 『 E C F M E E E E 56-5B E
HP Turbine Blade Cooling Airflow
Figure 002
F 『 EEFF : ALL E Page 372-52-00
E E Feb 01/98 E E ECES E
F 『
E C F M E
E E
E 56-5B E
E E
HPT ROTOR ASSEMBLY - INSPECTION/CHECK
_____________________________________
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：A320飞机维护手册 AMM ENGINE 发动机 2(57)
