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· Fuel metering through the FMU for:
− Automatic start and relight.
− Idle Speed Control.
− Acceleration and deceleration.
− Engine power setting.
− Limit protection for N1 and N2 speeds.
− Limit protection for temperature.
− Independent overspeed protection of N1 and N2.
· Compressor airflow control via the VSV and HP compressor bleed valves, to ensure:
− Surge free acceleration and deceleration.
− Surge recovery.
− Stable operation.
· Control of oil and fuel temperature.
· Control of the ignitors and start air valve.
· Partial control of the thrust reverser system functions.
· Control of the engine power in reverse thrust.
· Control of system electrical supply, either 28VDC or dedicated generator output to the EEC
and through to the FADEC.
GF1810_019
THROTTLE
MODULE
EEC
28 VDC
DEDICATED GEN
FMU
HP 5 & 8 BLEED VALVES
STATOR VANE SYSTEM
STARTER AIR VALVE
IGNITION SYSTEM
FUEL COOLED OIL COOLER
THRUST REVERSER
OTHER AVIONICS SYSTEMS
ENGINE INPUTS
DAU 1
DAU 2
DAU 3
IAC 1
IAC 2
IAC 3
ADC 1
ADC 2
ADC 3
POWER PLANT
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
18−10−12
ENGINE ELECTRONIC CONTROLLER (EEC)
The EEC is the controlling unit of the FADEC system and is located on the top of the engine in a
fireproof trough.
GF1810_020
ENGINE ELECTRONIC
CONTROLLER(EEC)
The EEC is an electronic control unit containing two channels A and B. Each channel is comprised of
a Central Processor Unit (CPU), Power Supply Unit (PSU) and two Independent Overspeed
Protection (IOP) units.
The PSU controls the power supplies to the FADEC system and to the EECs, CPU and IOP.
The PSU will control the switch over from the airplane 28VDC supply to power supplied by the
Dedicated Generator (DG). Normally the FADEC is powered by the DG when the engine is
operating. If DG power fails, the PSU will revert to the airplane power supply, to continue operation of
the engine. The DG is mounted on the front of the accessory gearbox.
GF1810_021
DEDICATED GENERATOR AIR STARTER
HYDRAULIC PUMP
DRY DRAINS OUTLET
VARIABLE FREQUENCY
GENERATOR No.1
FRONT VIEW OIL TANK
POWER PLANT
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
18−10−13
ENGINE ELECTRONIC CONTROLLER (EEC) (CONT'D)
The CPU receives and processes all input signals and calculates the output signals. Control of the
engine automatically alternates between channel A and channel B. If channel A is in control, channel
B is the backup for the duration of that flight. On the next engine start channel B is in control and
channel A is backup. The change command is triggered by the engine shut down on the ground. An
interlock prevents both channels from being in control at the same time. Each CPU operation is
monitored by a “watchdog timer”. If the watchdog timer senses a CPU malfunction within a set time
scale, then it will momentarily pass control to the other channel, while the faulty CPU resets. After
four CPU resets the watchdog will impose a freeze and control will pass to the other channel for the
remainder of the flight.
GF1810_022
CPU CPU VALIDATION
PROCESSING
OUTPUT SIGNAL
CALCULATION
VALIDATION
PROCESSING
OUTPUT SIGNAL
CALCULATION
OUTPUT DRIVER OUTPUT DRIVER
LANE CHANGE RELAY LANE CHANGE RELAY
SYSTEM CONTROLLER
SYSTEM
ACTUATOR
POSITION
ACTUATOR
ENGINE
TIMER
WATCHDOG
WATCHDOG
TIMER
OUTPUTS INPUTS INPUTS INPUTS INPUTS OUTPUTS
AIRFRAME SIGNALS ENGINE ENGINE AIRFRAME SIGNALS
SYSTEM FEEDBACK TO CHANNEL A & B
OF EEC AS "ENGINE INPUTS"
ENGINE PARAMETER FEEDBACK TO BOTH
CHANNELS OF THE EEC (AS ABOVE) AND DIRECT
TO AIRFRAME SYSTEMS, IE: VIBRATION.
CROSS
LINK
The IOP will automatically shut off fuel in the event of N1 or N2 reaching the overspeed trigger
values. When either N1 or N2 speed signal has exceeded a preset value, one of the IOPs will “vote”
to close the HPSOV, located in the FMU and indicate this to the other channel via the cross link. The
engine will not shut down unless both IOPs detect an overspeed. The overspeed function is checked
during normal engine shut down, by resetting the overspeed trip points to a subidle
value. When the
speed drops below the reset values, the IOP overspeed detection trip points logic resets.
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