Swash Plate Pump Operations

Swash Plate Pump

• If the swash plate is perpendicular to the axis of the pump, the flow will be zero
• The swash plate angle is controlled by servo pressure, which is obtained from pump delivery pressure through variable restrictions
• A spring moves the swash plate away from the minimum stroke position

Fuel System

• The burner fuel flow is at maximum at sea level (ISA)
• Fuel flow responds to mass airflow rate through the engine during aircraft acceleration
• Fuel flow is increased at a controlled rate during acceleration to prevent surge and the risk of flame-out
• The barometric pressure controller (BPC) controls fuel pump output in relation to the pressure variation at the intake

Fuel Pump

• The high-pressure fuel pump is fitted in a gas turbine engine aircraft to provide the majority of the fuel pressure to the engine
• The low-pressure pump prevents cavitation of the high-pressure fuel pump
• The fuel pump plungers are lubricated by the fuel itself

Governor

• The hydromechanical governor is fitted to a gas turbine engine fuel pump to enable the engine to operate over a wide range of fuel specific gravities
• The governor controls the maximum RPM of the engine by reducing the fuel pump stroke when maximum RPM is reached

Fuel Control Unit (FCU)

• The FCU is trimmed to obtain maximum thrust output when desired
• The FCU is adjusted to set idle RPM and maximum speed or EPR
• Trimming is most accurate in no wind and low moisture conditions

Electronic Engine Control (EEC)

• The EEC receives engine operating information and adjusts a standard hydromechanical fuel control unit to obtain the most effective engine operation
• The EEC is a system that controls engine operation according to ambient temperature, pressure, and humidity

FADEC System

• FADEC (Full Authority Digital Engine Control) system has electronic control of the hydro-mechanical fuel control unit in all modes
• Active control switchover occurs on engine start-up only
• Channel reset selects standby, which becomes active on the next start

Fuel Nozzle

• The duplex fuel nozzle provides better atomization and uniform flow pattern
• The flow divider in a turbine engine duplex fuel nozzle creates the primary and secondary fuel supplies
• The valve on a vane type fuel flow measuring device becomes stuck, and a differential pressure bypass valve is the safety backup available for the engine fuel flow### Engine Fuel Shutoff Valve
• Located downstream of the engine driven fuel pump

FADEC System

• Consists of H.M.U, sensors, and an E.E.C
• Primary purpose is to save fuel, reduce crew workload, and reduce maintenance costs
• Receives primary power from a separate permanent magnet alternator
• E.E.C measures pressure and temperature along with RPM
• Can change digital inputs into analogue format to provide glass cockpit information and reduce flight crew workload
• Has an automatic starting capability
• Does not have automatic control of engine fire bottles

Throttle and Fuel Control

• Throttle position is controlled by the crew or autothrottle
• Fuel flow is controlled by the E.E.C in flight
• Trimming is adjusting idle speed and maximum thrust
• Fuel trimmer unit is adjusted automatically at altitude

FADEC Channels

• Both channels are operating, but either one can be in command if they are both healthy
• If a channel fails to receive information from a sensor, it will take the information from the other channel
• If all air data input fails, the E.C.U reverts to an alternate (Fail-safe) mode

Engine Performance

• Optimized performance is the reason FADEC was introduced
• FADEC ensures efficiency is always maximum

Fuel System

• Engine fuel pump has a wire mesh filter
• Pressure drop across the Fuel Control Unit throttle orifice drops then increases due to increasing pump output
• Fuel boost pumps are cooled using fuel
• Main purpose of the fuel boost pumps is to provide fuel pressure to both engine pumps

Sensors and Valves

• Silver strip on a fuel filter detects sulphur in fuel
• Baffles in a rigid fuel tank prevent surge
• End fittings on a fuel non-return valve are different sizes to prevent incorrect installation

Swash Plate Pump

• If the swash plate is perpendicular to the axis of the pump, the flow will be zero
• The swash plate angle is controlled by servo pressure, which is obtained from pump delivery pressure through variable restrictions
• A spring moves the swash plate away from the minimum stroke position

Fuel System

• The burner fuel flow is at maximum at sea level (ISA)
• Fuel flow responds to mass airflow rate through the engine during aircraft acceleration
• Fuel flow is increased at a controlled rate during acceleration to prevent surge and the risk of flame-out
• The barometric pressure controller (BPC) controls fuel pump output in relation to the pressure variation at the intake

Fuel Pump

• The high-pressure fuel pump is fitted in a gas turbine engine aircraft to provide the majority of the fuel pressure to the engine
• The low-pressure pump prevents cavitation of the high-pressure fuel pump
• The fuel pump plungers are lubricated by the fuel itself

Governor

• The hydromechanical governor is fitted to a gas turbine engine fuel pump to enable the engine to operate over a wide range of fuel specific gravities
• The governor controls the maximum RPM of the engine by reducing the fuel pump stroke when maximum RPM is reached

Fuel Control Unit (FCU)

• The FCU is trimmed to obtain maximum thrust output when desired
• The FCU is adjusted to set idle RPM and maximum speed or EPR
• Trimming is most accurate in no wind and low moisture conditions

Electronic Engine Control (EEC)

• The EEC receives engine operating information and adjusts a standard hydromechanical fuel control unit to obtain the most effective engine operation
• The EEC is a system that controls engine operation according to ambient temperature, pressure, and humidity

FADEC System

• FADEC (Full Authority Digital Engine Control) system has electronic control of the hydro-mechanical fuel control unit in all modes
• Active control switchover occurs on engine start-up only
• Channel reset selects standby, which becomes active on the next start

Fuel Nozzle

• The duplex fuel nozzle provides better atomization and uniform flow pattern
• The flow divider in a turbine engine duplex fuel nozzle creates the primary and secondary fuel supplies
• The valve on a vane type fuel flow measuring device becomes stuck, and a differential pressure bypass valve is the safety backup available for the engine fuel flow### Engine Fuel Shutoff Valve
• Located downstream of the engine driven fuel pump

FADEC System

• Consists of H.M.U, sensors, and an E.E.C
• Primary purpose is to save fuel, reduce crew workload, and reduce maintenance costs
• Receives primary power from a separate permanent magnet alternator
• E.E.C measures pressure and temperature along with RPM
• Can change digital inputs into analogue format to provide glass cockpit information and reduce flight crew workload
• Has an automatic starting capability
• Does not have automatic control of engine fire bottles

Throttle and Fuel Control

• Throttle position is controlled by the crew or autothrottle
• Fuel flow is controlled by the E.E.C in flight
• Trimming is adjusting idle speed and maximum thrust
• Fuel trimmer unit is adjusted automatically at altitude

FADEC Channels

• Both channels are operating, but either one can be in command if they are both healthy
• If a channel fails to receive information from a sensor, it will take the information from the other channel
• If all air data input fails, the E.C.U reverts to an alternate (Fail-safe) mode

Engine Performance

• Optimized performance is the reason FADEC was introduced
• FADEC ensures efficiency is always maximum

Fuel System

• Engine fuel pump has a wire mesh filter
• Pressure drop across the Fuel Control Unit throttle orifice drops then increases due to increasing pump output
• Fuel boost pumps are cooled using fuel
• Main purpose of the fuel boost pumps is to provide fuel pressure to both engine pumps

Sensors and Valves

• Silver strip on a fuel filter detects sulphur in fuel
• Baffles in a rigid fuel tank prevent surge
• End fittings on a fuel non-return valve are different sizes to prevent incorrect installation

Swash Plate Pump

• If the swash plate is perpendicular to the axis of the pump, the flow will be zero
• The swash plate angle is controlled by servo pressure, which is obtained from pump delivery pressure through variable restrictions
• A spring moves the swash plate away from the minimum stroke position

Fuel System

• The burner fuel flow is at maximum at sea level (ISA)
• Fuel flow responds to mass airflow rate through the engine during aircraft acceleration
• Fuel flow is increased at a controlled rate during acceleration to prevent surge and the risk of flame-out
• The barometric pressure controller (BPC) controls fuel pump output in relation to the pressure variation at the intake

Fuel Pump

• The high-pressure fuel pump is fitted in a gas turbine engine aircraft to provide the majority of the fuel pressure to the engine
• The low-pressure pump prevents cavitation of the high-pressure fuel pump
• The fuel pump plungers are lubricated by the fuel itself

Governor

• The hydromechanical governor is fitted to a gas turbine engine fuel pump to enable the engine to operate over a wide range of fuel specific gravities
• The governor controls the maximum RPM of the engine by reducing the fuel pump stroke when maximum RPM is reached

Fuel Control Unit (FCU)

• The FCU is trimmed to obtain maximum thrust output when desired
• The FCU is adjusted to set idle RPM and maximum speed or EPR
• Trimming is most accurate in no wind and low moisture conditions

Electronic Engine Control (EEC)

• The EEC receives engine operating information and adjusts a standard hydromechanical fuel control unit to obtain the most effective engine operation
• The EEC is a system that controls engine operation according to ambient temperature, pressure, and humidity

FADEC System

• FADEC (Full Authority Digital Engine Control) system has electronic control of the hydro-mechanical fuel control unit in all modes
• Active control switchover occurs on engine start-up only
• Channel reset selects standby, which becomes active on the next start

Fuel Nozzle

• The duplex fuel nozzle provides better atomization and uniform flow pattern
• The flow divider in a turbine engine duplex fuel nozzle creates the primary and secondary fuel supplies
• The valve on a vane type fuel flow measuring device becomes stuck, and a differential pressure bypass valve is the safety backup available for the engine fuel flow### Engine Fuel Shutoff Valve
• Located downstream of the engine driven fuel pump

FADEC System

• Consists of H.M.U, sensors, and an E.E.C
• Primary purpose is to save fuel, reduce crew workload, and reduce maintenance costs
• Receives primary power from a separate permanent magnet alternator
• E.E.C measures pressure and temperature along with RPM
• Can change digital inputs into analogue format to provide glass cockpit information and reduce flight crew workload
• Has an automatic starting capability
• Does not have automatic control of engine fire bottles

Throttle and Fuel Control

• Throttle position is controlled by the crew or autothrottle
• Fuel flow is controlled by the E.E.C in flight
• Trimming is adjusting idle speed and maximum thrust
• Fuel trimmer unit is adjusted automatically at altitude

FADEC Channels

• Both channels are operating, but either one can be in command if they are both healthy
• If a channel fails to receive information from a sensor, it will take the information from the other channel
• If all air data input fails, the E.C.U reverts to an alternate (Fail-safe) mode

Engine Performance

• Optimized performance is the reason FADEC was introduced
• FADEC ensures efficiency is always maximum

Fuel System

• Engine fuel pump has a wire mesh filter
• Pressure drop across the Fuel Control Unit throttle orifice drops then increases due to increasing pump output
• Fuel boost pumps are cooled using fuel
• Main purpose of the fuel boost pumps is to provide fuel pressure to both engine pumps

Sensors and Valves

• Silver strip on a fuel filter detects sulphur in fuel
• Baffles in a rigid fuel tank prevent surge
• End fittings on a fuel non-return valve are different sizes to prevent incorrect installation

Assess your knowledge of swash plate pump operations, including flow direction, swash plate movement, and burner fuel flow. Test your understanding of these mechanical systems.