Lesson 1 Flashcards
The thrust of a turbo jet is controlled by varying the [?] that is burnt in the [?] and in order to operate the safe temperature limits, the amount of fuel that is burnt must be governed by the [?] that is available at the time.
1.amount of fuel
2. combustion system
3. amount of air
The air supply is dependent upon the RPM of the compressor and the density of the air at its inlet, so under a constant set of atmospheric conditions, the RPM of the compressor is an indication of the [?].
engine thrust
The pilot has control of the fuel flow to the combustion system and ts able to select any compressor RPM, between ground idling and the maximum permissible which is required for [?] conditions, by the operation of a cockpit lever.
take-off
In the normal operational environment of an aircraft engine, atmospheric conditions can vary over a wide range of air temperatures and pressures resulting in [?] at the compressor inlet.
changes of air density
A [?] will cause a reduction in the amount of air delivered to the combustion system at a selected RPM, with a consequent increase in the combustion chamber temperature.
reduction in air density
If the fuel flow is not reduced, a [?] will occur accompanied with overheating of the combustion and turbine assemblies.
rise in compressor RPM
An [?] will result in an increase in the amount of air delivered to the combustion system at a selected RPM
increase in air density
Fuel flow is increased, a [?] in RPM will occur .
reduction
The density of the air gets progressively less as the altitude is increased, therefore less fuel will be required in order to maintain the
selected RPM.
ALTITUDE
The faster the aircraft flies then the faster the air is forced into the aircraft intake.
FORWARD SPEED
(?) plays an important part in the performance of a turbo-jet. Within certain limits the greater the ram
effect, the greater the air mass flow and more fuel can be burnt at the selected RPM, producing more thrust.
Ram Effect
(?) is to deliver to the combustion system, in a readily combustible form, the correct amount of fuel over
the whole operating range of the engine, as required by the pilot.
Purpose of the engine fuel system
2 TYPES OF FUEL TANK
A. Gravity feed fuel system
B. Booster Pump feed fuel system/ Pressure Type
Stores sufficient fuel for the aircraft’s designed flight duration.
Fuel Tanks
(?) the fuel passes through a main system strainer. This often has a drain function to remove sediment and water.
Shutoff Valve or Selector Valve
(?) also supplies fuel pressure while starting and is used to prevent vapor lock during flight at high altitude.
Electric Pump
Some high-wing, high-performance, single-engine general aviation aircraft are equipped with a fuel system that features (?) rather than a carburetor.
fuel injection
It combines gravity flow with the use of a fuel pump(s).
Teledyne Continental system
Fuel pressurized by an (?) is metered as a function of engine rpm on the Teledyne-Continental system.
Engine-Driven Pump
draws fuel through the selector valve. It forces the fuel through the strainer, making it available for the primer pump and the engine-driven fuel pump.
Electric Auxiliary Fuel Pump
This pump is typically used for starting and as a backup should the engine-driven pump fail.
Electric Auxiliary Fuel Pump
It is controlled by a switch in the cockpit and does not need to be operating to allow the engine-driven fuel pump access to the fuel.
Electric Auxiliary Fuel Pump
Fuel injection systems spray (?) into the engine intake or directly into the cylinders.
pressurized fuel
(?) intakes the pressurized fuel from the electrically driven pump or from the reservoir tanks if the electric pump is not operating.
Engine-Driven Fuel Pump/ EDP
