F 『
E C F M E
E E
E 56-5B E
E E
______________________________________________
1. General
_______ (Ref. Fig. 001, 002, 003) The fan frame module provides front handling mounts and is the main forward support for mounting the engine to the aircraft. Its purpose is to support the fan, booster and high pressure compressor (HPC) rotors, and to provide ducting for primary and secondary airflows. The fan frame module consists of the following major assemblies:
- Fan frame assembly.
- Fan Inlet Case assembly.
2. Fonctions
_________
The Fan Frame and Fan Inlet Case perform the following primary functions:
A. Fan Frame.
(1) An inlet airflow path to the core engine.
(2) A support for loads of the fan stator, fan rotor and fan reverser.
(3) Containment of accessory drive power take off gears (inlet gearbox) and radial drive shaft arrangement.
(4) A variable bypass bleed valve system.
(5) Housing for the oil pressure, scavenge, drain lines and venting/pressurisation/sealing system associated with the bearings and gears located in the engine forward sump.
B. Fan Inlet Case.
(1) Provides for attachment of the engine inlet cowl and the support and transmission of attachment loads from this point to the fan frame.
(2) Provides fan blade containment.
(3) Provides attachment points for acoustical panels, and fan OGV.
(4) Provides an abradable lining for fan blade tips.
F 『 EEFF : ALL E Page 172-23-00
E E Feb 01/98 E E ECES E F 『 E C F M E E E E 56-5B E
Fan Frame Assembly
Figure 001
F 『 EEFF : ALL E Page 272-23-00
E E Feb 01/98 E E ECES E F 『 E C F M E E E E 56-5B E
Fan Frame Assembly
Figure 002
F 『 EEFF : ALL E Page 372-23-00
E E Feb 01/98 E E ECES E F 『 E C F M E E E E 56-5B E
Fan Frame Assembly Figure 003 (SHEET 1)
F 『 EEFF : ALL E Page 472-23-00
E E Feb 01/98 E E ECES E F 『 E C F M E E E E 56-5B E
Fan Frame Assembly Figure 003 (SHEET 2)
F 『 EEFF : ALL E Page 572-23-00
E E Feb 01/98 E E ECES E 3. Description
F 『
E C F M E
E E
E 56-5B E
E E
___________ (Ref. Fig. 002, 003)
A. Fan Frame Assembly The fan frame assembly is a fabricated structural weldment made of concentric rings connected by radial struts. It consists of the basic fan frame structure and the fan inlet case assembly.
(1) The basic fan frame structure is made of steel alloy. It consists of a hub, mid box structure and outer casing interconnected through 4 thick and 8 thin radial struts.
(a) Structural strength for the fan frame is obtained from the 12 struts. The struts are hollow and provide passage for the following equipment :
(b) The hub front face supports the No. 1 and No. 2 bearing support. The rear face supports, from front to rear, the IGB and No. 3 bearing module and the rear stationary air/oil seal together with its pressurization air supply ring. The hub outer surface, which is also the inner wall of the primary airflow annulus, has orifices for bleed air requirements.
(c) The mid box structure is located radially between the primary and secondary airflows. It houses the 11 variable bleed valve (VBV) ballscrew actuators and the VBV master ballscrew actuator , and air scoops for the LPT active clearance control system (LPTACC). The front flange of the structure supports the rear outer flanges of the stage 5 booster vane assembly, and the fan OGV inner shroud. The structure rear flange supports the HPC forward case, the VBV hydraulic fuel gear motor and provides for engine mounting.
(d) The outercasing makes up the outer wall of the secondary airflow. Located on the outer surface of the casing are the 2 ground handling mounts and the TGB mounting pad. The fan inlet case mounts to the outer casing front flange, and the fan discharge duct mounts to the outer casing rear face.
1_ No. 1 bearing vibration sensor cable (No. 4 strut).
2_ N1 speed sensor and drain cavity (No. 6 strut).
3_ Transfer gearbox (TGB) radial drive shaft and scavenge tube
(No. 7 strut).
4_ Forward sump oil supply tube (No. 10 strut).
F 『 EEFF : ALL E Page 672-23-00
E E Feb 01/98 E E ECES E
F 『 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 1(117)
