曝光臺 注意防騙
網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者
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A. The engine air system regulates air throughout the engine for cooling and for control purposes.
B. The air system includes the Engine Bearing Cooling System (AMM 75-22-00), Engine External Accessories Cooling (AMM 75-23-00), Turbine Cooling System (AMM 75-24-00), Compressor Stator Vane Control System (AMM 75-31-00), Compressor Bleed Control System (AMM 75-32-00), and HPC Secondary Flow Control System (AMM 75-33-00).
C. The engine bearing cooling system pressurizes bearing carbon seals with different stages of compressor bleed air, and decreases the temperature of the No. 3 bearing compartment with 12th-stage compressor bleed air which is cooled by fan air.
D. Engine external accessories cooling is done by fan air which is put into the nacelle zone and specific engine components. Such components include the exciter-to-ingiter plug cables, starter, start valve, intergrated drive generator (IDG), electronic engine control (EEC) alternator (N2 transducer), secondary flow control valves, and the oil quantity transmitter.
E. The turbine cooling system includes the turbine case cooling system, which uses fan air for cooling, and the turbine vane and blade cooling system, which uses 12th-stage compressor bleed air for cooling, to decrease the turbine blade tip clearances and to increase engine efficiency.
F. The compressor stator vane control system controls the inlet guide vanes and the 5th-, 6th-, and 7th-stage variable stator vanes of the high pressure compressor (HPC) to increase the stall margin and compressor efficiency.
G. The compressor bleed control system uses 2.5 and 2.9 bleed valves to bleed compressor air overboard during the engine start. The bleed valves are also open for higher compressor stability during engine surge and reverse thrust conditions.
H. The HPC secondary flow control system controls 9th-stage compressor bleed airflow to the HPC inner cavity. This controls HPC blade tip clearance for improved compressor efficiency.
2. Operation
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A. Functional Description
(1) Operation of the different air systems is automatic. The compressor bleed and control systems and the different cooling systems are in normal operation during engine operation and no operator actions are necessary.
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75-00-00
ALL ú ú N01 Page 1 ú Jun 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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A / PW4000 SERIES /
747-400 / ENGINES /FAULT ISOLATION/MAINT MANUAL ////////////////////////
AIR
COMPONENT FIG. 102 SHT QTY ACCESS/AREA REFERENCE
ENG 1 ACTUATOR - TURBINE CASE COOLING AIR VALVE, 5 1 HPC CASE416, RIGHT THRUST REVERSER HALF, 75-24-05
ACTUATOR - TURBINE CASE COOLING AIR VALVE, ENG 2 5 1 HPC CASE426, RIGHT THRUST REVERSER HALF, 75-24-05
ACTUATOR - TURBINE CASE COOLING AIR VALVE, ENG 3 5 1 HPC CASE436, RIGHT THRUST REVERSER HALF, 75-24-05
ACTUATOR - TURBINE CASE COOLING AIR VALVE, ENG 4 5 1 HPC CASE 446, RIGHT THRUST REVERSER HALF, 75-24-05
ACTUATOR - VARIABLE STATOR VANE, ENG 1 6 1 HPC CASE416, RIGHT THRUST REVERSER HALF, 75-31-02
ACTUATOR - VARIABLE STATOR VANE, ENG 2 6 1 HPC CASE426, RIGHT THRUST REVERSER HALF, 75-31-02
ACTUATOR - VARIABLE STATOR VANE, ENG 3 6 1 HPC CASE436, RIGHT THRUST REVERSER HALF, 75-31-02
ACTUATOR - VARIABLE STATOR VANE, ENG 4 6 1 HPC CASE 446, RIGHT THRUST REVERSER HALF, 75-31-02
ACTUATOR - 2.5 BLEED VALVE, ENG 1 4 1 415, LEFT THRUST REVERSER HALF, INTERMEDIATE CASE 75-32-01
ACTUATOR - 2.5 BLEED VALVE, ENG 2 4 1 INTERMEDIATE CASE 425, LEFT THRUST REVERSER HALF, 75-32-01
ACTUATOR - 2.5 BLEED VALVE, ENG 3 4 1 INTERMEDIATE CASE435, LEFT THRUST REVERSER HALF, 75-32-01
ACTUATOR - 2.5 BLEED VALVE, ENG 4 4 1 INTERMEDIATE CASE 445, LEFT THRUST REVERSER HALF, 75-32-01
CONTROL, ENG 1CABLE - TURBINE CASE COOLING AIR VALVE 3 1 HPC TO HPT CASE416, RIGHT THRUST REVERSER HALF, 75-24-11
CABLE - TURBINE CASE COOLING AIR VALVE CONTROL, ENG 2 3 1 HPC TO HPT CASE426, RIGHT THRUST REVERSER HALF, 75-24-11
CABLE - TURBINE CASE COOLING AIR VALVE CONTROL, ENG 3 3 1 HPC TO HPT CASE436, RIGHT THRUST REVERSER HALF, 75-24-11
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747-400 AMM 飛機維護手冊 大氣 AIR 1(3)
