ATPL Bgt Quiz

At the face of the compressor

Leaving the diffuser

At the end of the exhaust nozzle

Lower pressure and lower temperature

Raise pressure and lower velocity

Raise velocity and lower temperature

Thrust increases as air temperature increases

Thrust decreases as air temperature increases

Thrust increases as humidity increases

In the jet pipe

At the end of the compressor

In the combustion chamber

In the diffuser

At the last stage of the turbine

At the inlet of the compressor

The fan

The compressor, combustion chambers, turbines and exhaust

The accessory drive shaft

A decrease in ambient air temperature

A decrease in ambient air pressure

A decrease in ambient air density

It will stall more readily

Discharge pressure will increase

RPM will increase

A bypass ratio less than 1:1

A bypass ratio more than 1:1

No bypass air

A convergent duct

A divergent duct

A helical duct

Lowers the efficiency of a jet engine as aircraft speed increases

Raises the thrust output of a jet engine as aircraft speed increases

Cools the air as it enters the engine intake

Gas pressure, velocity and temperature all decrease

Gas pressure increases, velocity falls and temperature increases

Gas pressure reduces, velocity increases and temperature decreases

Blade creep experienced on the test bench by the manufacturer

Normal blade creep over the life of the engine

Blade creep to the point where it would be detrimental to continue to run the engine

Prolonged ground running with the air intake guard screens fitted

An unserviceable igniter plug

An unstable airflow through the compressor

Within the combustion chamber

At the entry to the exhaust unit

At the compressor exit

At MSL under ISA conditions

At high altitudes

At MSL under ISA plus temperatures

The compressor ceases to rotate

The smooth flow of air over the blading breaks away and causes an interruption of airflow through the engine

The fuel flow burners will cease immediately

Prevent turbine blade stall at high engine RPM

Prevent compressor blade stall during operation off design RPM

Prevent excessive cooling due to large mass air flow through the engine

The decrease in mass airflow permits an increased fuel/air ratio

The higher ambient temperature results in a greater pressure rise through the engine

The engine can operate at design RPM to maintain an efficient wing angle of attack

An increase in the gas temperature, reduced thrust and an increase in SFC

An increase in thrust since less air will be mixed with fuel in the combustion chambers

An increase in RPM and a decrease in gas temperature

Between the final compressor stage and the inlet to the combustion chamber

In the exhaust unit

At the downstream end of the combustion chamber

To prevent overheating of the turbine

To prevent burning of the thermocouples

To prevent a thermal runaway

Raise the pressure and reduce the velocity of the gases

Increase the density and reduce the temperature of the gases

Increase the volume and velocity of the gases

Nozzles designed to increase velocity of the air

Divergent ducts which lower the velocity and raise the pressure of the air

Special passages which drop the pressure of the air before combustion occurs

Leave the fuel filler caps off

Keep the tanks as full as possible

Fill the tank airspace with carbon dioxide