2. Description

___________
 A. Nozzle Segments The HPT nozzle segments are assemblies of 2 vane/platform castings that are brazed together. Each vane is a cast shell divided into forward and aft compartments by an inner rib. The vanes and platforms are cooled by compressor discharge air entering the vane compartments through inserts in the inner and outer ends of vanes and exiting through the vane leading and trailing edges. The vanes and platforms are made of high strength nickel base alloy with protective coating on vane airfoils and on platform flowpath surfaces.
 B. Inner Support The nozzle inner support is a one-piece nickel base alloy ring. The major portion of the nozzle axial load is carried by the inner support through the bolted flanges of the support and nozzle inner platforms. The nozzle inner platform and the inner support form a seal ring which controls the amount of cooling air leakage that passes between the seal and the HPT blades.
 C. Aft Outer Support and Seal The aft outer support is a one-piece nickel base alloy ring that provides support for the 4-step honeycomb seal that mates with the HPT rotor inducer seal to help maintain the proper amount of cooling air flow and rotor thrust.
 F 『 EEFF : ALL E Page 172-51-00
 E E Feb 01/98 E E ECES E F 『 E C F M E E E E 56-5B E

 High Pressure Turbine Nozzle
 Figure 001

 F 『 EEFF : ALL E Page 272-51-00
 E E Feb 01/98 E E ECES E F 『 E C F M E E E E 56-5B E

 Stage 1 HPT Nozzle Cooling Airflow
 Figure 002

 F 『 EEFF : ALL E Page 372-51-00
 E E Feb 01/98 E E ECES E

 F  『
 E  C F M  E
 E  E

 E 56-5B E
 E E
 HPT NOZZLE ASSEMBLY - INSPECTION/CHECK

______________________________________
 TASK 72-51-00-290-004
 Borescope Inspection of High-Pressure Turbine Nozzle Assembly
 1. Reason for the Job
__________________
 This TASK is applicable for NON/P engines.
 NOTE : Inspection of the high pressure turbine (HPT) nozzle assembly is
____ limited to the areas that can be seen with a rigid borescope at the 1, 3, 6, and 10 o'clock borescope ports, and at the 2 spark igniter ports. The borescope ports at the 1, 3, 6, and 10 o'clock position are located immediately in front of the fuel manifold. Special inspection of the HPT nozzle convex side can be accomplished, if required using with a flexible borescope.
 2. Job Set-up Information
______________________
 A. Fixtures, Tools, Test and Support Equipment
 -------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific warning notice
 No specific access platform 1 m (3 ft. 3 in.)
 No specific Torque Wrench : range 36.00 to 220.00 lbf.in

 (0.40 to 2.60 m.daN)
 856A1310 1 KIT, BORESCOPE GUIDE - HP TURBINE
 856A1320 1 BORESCOPE KIT
 856A1321 1 FIBERSCOPE SET
 856A1322 1 BORESCOPE - LIGHT SOURCE SET
 856A1323 1 MONITOR, RESOLUTION BORESCOPE
 856A1351 1 GUIDE TUBE ,BORESCOPE - HPT SHROUD

 B. Consumable Materials
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
Material No. CP2101 USA MIL-T-5544
 graphite grease (Ref. 70-30-00) R Material No. CP2619 * R Never Seez-Pure Nickel, Special (Ref. 70-30-00)
 Material No. CP8001 *
 lockwire 0.032 in. (0.8mm) dia (Ref. 70-30-00)
 Material No. CP8002 *
 lockwire 0.032 in. (0.8mm) dia (Ref. 70-30-00)

 F 『 EEFF : ALL E Page 60172-51-00
 E E Feb 01/02 E E ECES E

 F 『
 E C F M E
 E E
 E 56-5B E
 E E
 C. Referenced Information

 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
71-13-00-010-040 Opening of the Fan Cowl Doors 71-13-00-410-040 Closing of the Fan Cowl Doors 72-00-00-200-025 Over-Serviceable-Limit Extensions 73-11-40-790-002 Leak Check of the Fuel Nozzles 74-21-30-000-002 Removal of the Spark Igniter 74-21-30-400-002 Installation of the Spark Igniter 78-30-00-081-041 Make the Thrust Reverser Serviceable after
 Maintenance 78-30-00-481-041 Make the Thrust Reverser Unserviceable for
 Maintenance 78-36-00-010-040 Opening of the Thrust Reverser Doors 78-36-00-410-040 Closing of the Thrust Reverser Doors NDTM 720000 72-51-00-991-300 Fig. 601 72-51-00-991-301 Fig. 602
　
中國航空網 m.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(51)