(3)
Turbine discharge temperature (at rated combination load) maximum 632 DEG.C (1170 DEG.F) approximately.
(4)
Engine shaft speed
(Ref. Fig. 002)
B. Fuel and Fuel Control System
NOTE : This is for general reference only. All fuel types approved in
____ your Flight Crew Operation Manual (FCOM) can be used in the APU.
----------------------------------------------------------------Fuel Specifications
----------------------------------------------------------------Jet A/Jet A1 ASTM D 1655 JP4 Mil-T-5624 Jet B ASTM D 1655 JP5 Mil-T-5624
-----------------------------------------------------------------
(1)
Fuel inlet pressure from 0.34 bar (5 psi) (min) above true vapour pressure to 3.8 bar (55 psi) (max).
(2)
Fuel inlet temperature from - 40 DEG.C (-40 DEG.F) to 57 DEG.C. (135 DEG.F).
C. Engine Starter Motor-Duty Cycle Three consecutive start attempts are permitted without cooldown. After the third start attempt the starter motor must cool down for at least 60 minutes.
R EFF : 001-049, 101-105, 107-107, 151-199, 49-20-00Page 5 201-210, Config-2 Aug 01/05
CES
IDLE/MES and ECS Engine Speed Schedule
Figure 002
CES D. Lubrication System
(1)
Oil specification - approved lubricants of vendor.
(2)
Oil reservoir capacity 6.26 l (1.6537 USgal) approx.
(3)
Oil consumption - should not exceed 93cc (0.099qt/hr) per operating hour.
E. Electrical System:
(1)
The ECB (59KD) is supplied with 28VDC by the busbar 301PP.
(2)
The Starter Motor is supplied with 28VDC by the busbar 3PP.
F. Bleed-Air Control System
(1)
Inlet Guide-Vane Actuator - Nonoperating - Closed.
(2)
Surge Control Valve - Nonoperating - Open.
(3)
Bleed Load Valve - Normal position - Closed.
R EFF : 001-049, 101-105, 107-107, 151-199, 49-20-00Page 7 201-210, Config-2 Aug 01/05
CES ENGINE - DESCRIPTION AND OPERATION
__________________________________
1. General
_______
The APU supplies:
-
pneumatic power for 'Main Engine Start (MES)',
-
pneumatic power for the environmental control system (ECS),
-mechanical shaft power to drive an AC generator and a fan. The fan, an integral part of the APU, cools its lubrication system and the APU compartment.
2. System Description
__________________
(Ref. Fig. 001)
The power unit has three basic modules:
-
a power section,
-
a load compressor,
-
an accessory gearbox.
A.
Power Section The power section supplies shaft power to drive a load compressor, a gearbox with accessories and an electrical generator. It is a single-shaft assembly with a single-stage, machined-titanium centrifugal-compressor with a 8:1 pressure ratio. It also includes a reverse-flow annular-combustion chamber and a two-stage axial-flow turbine (Ref. 49-21-00).
B.
Load Compressor The load compressor is a direct-drive modular assembly, installed between the power section and the accessory gearbox. It is a single-stage centrifugal compressor. Inlet Guide Vanes (IGVs) are installed at the entrance of the compressor housing to control the compressor output to the aircraft system (Ref. 49-23-00).
C.
Accessory Gearbox
The accessory gearbox is installed on the front face of the load
compressor casing and is driven by the power section.
The accessory gearbox (Ref. 49-26-00) has drive pads for:
-an AC generator,
-a starter motor,
-two oil pumps (pressure and scavenge pump),
-
a fuel pump,
-
a cool air fan and PMG.
Auxilliary Power Unit
Figure 001
CES
3. Operation/Control and Operation_______________________________ The MASTER SW pushbutton switch 14KD and the APU START pushbutton switch 2KA are installed on the panel 25VU in the cockpit. They both control the engine start.
When the MASTER SW 14KD is set to ON, the Electronic Control Box (ECB) 59KD
is energized. This causes the ECB to transmit signals that:
- open the APU air-intake flap,
- open the FUEL LP VALVE 3QF,
-energize the APU fuel-feed pump 4QC. When the APU START switch 2KA is set to the ON position, a signal is transmitted to the ECB 59KD. This signal is used to start the APU. The starter motor 8KA does not engage unless the air intake flap is open. This is indicated to the ECB via the open position switch of the air intake flap-actuator. After 100 ms. the backup start contactor is energised. 1.5 sec. later the gearbox de-oiling valve, the main start contactor and the exciter are energised. Manifold fill algorithm and open loop fuel schedule begin. Acceleration control to 100% is initiated when delta EGT is greater than 50 deg F and speed is greater than 15 per cent. The starter motor accelerates the engine to 55%. 中國航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320飛機維護(hù)手冊 AMM 機載輔助動力 AIRBORNE AUXILIARY POWER3(69)
