FADEC system Presentation

Welcome Aboard

FADEC-Full Authority Digital Engine Control 1

Topic

FADEC (Full Authority Digital Engine Control) System


Members:

1) Dipayan Swarnaker (ID-201222014)

2) Md. Nurul Huda (ID-201222037)

3) Masum Bellah (ID-201222019)


Outline

• Jet engine control

• History of FADEC system

• FADEC system

• Advantage

• Limitation


Flow of presentation

Jet Eng. Cntrl. & Intro to FADEC (Masum)

Historical Development of FADEC (Toyon)

FADEC System (Dipayan)

Advantage & Limitation (Masum)


Jet Engine Control by

Masum Bellah (201222019)


What will I need to control jet?

Control Electrical system

Control Fuel Injection system

Control Ignition system


How does a jet engine works ?


FADEC

ᴭ Means Full Authority Digital Engine Control

ᴭ A system consisting of digital computer called EEC

ᴭ Can be used both for jet and piston engine

ᴭ Consists of HMU, sensors, EEC

ᴭ Can be installed only on a fuel-injected engine that eliminating carburetors


FADEC

ᴭ Engine is controlled based on temperature and pressure

ᴭ Maintains the fuel/air ratio

ᴭ Commercial and military engines, missiles, UAV


Historical Background by

Nurul Huda Toyon (201222037)


Historical Background

Digital electronic controls on aircraft engines began in the late 1960's

In 1968 Rolls-Royce and Elliott Brothers introduced first digital engine controlled engine that is JT9D engine applied on B767, A300 and A310 airplanes.

1970's Pratt & Whitney began to develop electronic controls for commercial engines




FADEC Operations & Controls by

Dipayan Swarnaker (201222014)


Operations of a FADEC system

• Controls the ignition spark

• Controls the fuel to air mixture of the engine

• Engine acceleration to idle speed during start

• Acceleration and deceleration limiting

• Minimum approach idle speeds during descents

• Selection of alternative power modes

• Monitors cylinder head, manifold and exhaust gas temperatures.


Parts of FADEC system

• Two Master Power Control Units

• Cylinder Head Temperature (CHT) Sensor

• Exhaust Gas Temperature (EGT) Sensor

• Fuel Pressure Sensors

• Health Status Annunciator(HSA)

• Fuel Injection System


Electronic Control Unit (ECU)

• Brain of the Engine Control System

• ECU divided into two part. – Lower portion

– Upper portion

• Lower portion contains the Electronic Circuit Board that processes all data

• Upper portion contains the ignition coils for the spark plugs


ECU (cont.)

• Lower portion contains two independent microprocessor controllers which serve as control channels


Purpose of ECU

• receive the sensor inputs and monitor any changes

• precisely trim the fuel/air ratio

• control fuel injection and ignition timing


Master Power control


• Centralize the primary electrical controls for general aviation aircraft

Manifold Temperature And Pressure sensor


CHT Sensor

EGT Sensors


Fuel pressure sensor (FPS)


Low Voltage Harness

• Connects all essential components of FADEC

• Fuel Injector Coils and all sensors (except Speed Sensors Assembly, Fuel Pressure, Manifold Pressure) are hardwired to the low voltage harness

• All information from sensors will flow to the Electronic Control Units for data processing and analysis



Health Status Annunciator (HSA)

HSA lights

• Consists of (5) lights on panel and WOT

• HSA will not give you a warning or caution light for OIL temp/pressure or ALT FAIL

• FADEC WARN: Engine Failure may be imminent, more than one cylinder is affected

• FADEC CAUTION: 99.99% of installed components are working


HSA Lights (contd.)

• PPWR FAIL: Primary Battery is not being charged, will be accompanied by EBAT FAIL…you will start draining both batteries and have at least 60 minutes to land. Your secondary battery will only power FADEC

• EBAT FAIL: Backup Battery not being charged, everything can run from Primary Power Source/Battery


HSA Lights (contd.)

• FUEL PUMP: illuminates when Fuel Boost Pump Mode Switch is in ON or OFF

• WOT: below HSA panel. Illuminates when Throttle Position Switch is contacted (full throttle), signal sent to ECU that max power is required which causes FADEC to set fuel to air ratio for Best Power


FADEC Sensors

These sensors are used to maintain a stable engine performance. Here I have shown Airbus A-320 engine sensors.


Control of Ignition system

• FADEC system schedules the spark timing and the intensity using two MPC units

• Two high voltage terminals on each spark transformer

• Spark transformers are controlled by microproccessor.



Control of Fuel Injection System

• FADEC schedules the amount of fuel and the injection timing for the multi-port fuel injectors

• The Fuel Injection System is composed of:

– An engine-driven Fuel Pump

– Fuel Distribution Block and fuel lines

– Solenoid-controlled Fuel Injection Nozzles



Control of Electrical System

• FADEC system requires two independent power sources.

• FADEC connections supply operating data to HSA panel and the optional Engine Performance Display




Advantage & Limitation by

Masum Bellah (201222019)


Advantages

• Run the engine in optimal condition for less fuel consumption

• Single lever control - less pilot workload

• Easier and cleaner installation

• Extra safety features


Advantages (contd.)

• Engine-related issues during takeoff

– MEASTO


Limitation

• FADEC doesn’t provide any manual override since it takes over the engine completely

• In case of emergency, the system becomes highly unreliable


Accident

• On 2 June 1994 at about 18:00 hours Scotland RAF Chinook (CH-47) crash occurred

• There was FADEC malfunction.

• Rotors got over speed (one rotor got more fuel than other one)

• Controls are jammed


This accident caused 25 passengers & 4 crews



THANK YOU


Any

Question ??

FADEC system Presentation

Documents