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Engine and its Parts:
1) The inlet section
2) The compressor section
3) The combustion section
4) The exhaust section.
The systems often found associated with the operation of the engine are:
1) The accessory drive gearbox
2) The fuel system
3) The lubrication system
4) The ignition system
5) The bleed system
6) The start system
7) The anti-ice system.
In addition, there are airplane systems that are powered or driven by the engine. These systems may include:
1) The electrical system
2) The pneumatic system
3) The hydraulic system
4) The air conditioning system
purpose:
The FADEC (Full Authority Digital Engine Control) is a total system for the control of an engine. It controls all aspects of aircraft engine performance.
FADEC’s main purpose is to provide optimum engine efficiency for a given flight condition. FADEC controls the aircraft’s engine and propeller in order to perform at a maximum efficiency. It does this by controlling the power of the reciprocating engine and by adjusting the amount of fuel injection during the combustion process.
protection against engine exceeding limits - protection against N1 and N2 overspeed.
outputs:
It controls and regulates the fuel pump, providing to the engine the necessary amount of fuel for safe and controlled operation. The FADEC system also continuously monitors and controls ignition timing, fuel injection timing, and fuel-to-air ratio mixture.
The status of the FADEC system is conveyed to the pilot by the HSA. Discrete lamps in the HSA will illuminate upon detection of system faults and during some normal control actions.
inputs:
Sensor input to each control channel includes engine speed, crank position, fuel pressure, intake manifold air pressure, intake manifold air temperature and Wide Open Throttle (WOT) position. In addition, each control channel also receives exclusive signals for measuring its cylinder's head temperature and exhaust gas temperature.
airspeed, altitude from ADS.
The FADEC system includes the following components that will be installed on the engine or the airframe:
Two Master Power Control Units("MPC-1" And "MPC-2")
Sensors For Manifold Temperature And Pressure
Cylinder Head Temperature (CHT) Sensor
Exhaust Gas Temperature (EGT) Sensor
Speed Sensors
Speed Sensor Assembly
Fuel Pressure Sensors
Low Voltage Harness - aircraft power sources, the Ignition Switch, Speed Sensor Assembly (SSA), Health Status Annunciator (HSA), temperature and pressure sensors
High Voltage Harness - fuel injector coils and all sensors, except the speed sensor assembly, fuel pressure, and manifold pressure sensors
Throttle Body Assembly
Health Status Annunciator (HSA)
Fuel Injection System
FADEC Architecture:
EICAS: Engine instrumentation in the flight deck
Engine Pressure Ratio or EPR - engine thrust
Rotor RPM - N1, N2
Exhaust Gas Temperature or EGT
Fuel Flow
fuel quanity
fuel pressure
Oil Pressure
Oil Temperature.
Oil Quantity
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