Quiz about 1801-1900

Question 1

1801. If the airflow is constant and you decrease the diameter of the jet nozzle (Level 1)

Accepted Answer

c) The outlet velocity increase

Answer

a) The outlet velocity does not change

Answer

b) The outlet velocity decrease

Question 2

1802. The thrust is generated by (Level 1)

Accepted Answer

b) Acceleration of airflow

Answer

a) Pushing against the atmosphere

Answer

c) Acceleration of airflow and pushing against the atmosphere

Question 3

1803. With increasing altitudes (Level 1)

Accepted Answer

a) The ambient pressure decreases and the temperature decreases

Answer

b) The ambient pressure decreases and the temperature increases

Answer

c) The ambient pressure increases and the temperature decreases

Question 4

1804. There was no engine compressor before 1937 due to (Level 2)

Accepted Answer

b) There was no material that was heat-resistant enough for continuous combustion.

Answer

a) There was no one can invent it

Answer

c) The engine without compressor has better performance

Question 5

1805. Turboprop engines do not use on large A/C due to (Level 2)

Accepted Answer

c) It's hard to manage the rotation speed of propeller

Answer

a) This engine is very loud

Answer

b) This engine is not efficient

Question 6

1807. If the velocity of the air at the engine inlet increases, thrust force would be (Level 2)

Accepted Answer

c) Decreased

Answer

a) Stay the same

Answer

b) Increased

Question 7

1809. The reduction gear is used on turboprop engine for what purpose? (Level 2)

Accepted Answer

a) Reduce speed of propeller

Answer

b) Increase speed of propeller

Answer

c) Maintain speed of propeller

Question 8

1810. The fans of turbofan engine are always driven by (Level 2)

Accepted Answer

c) A turbine via a drive shaft

Answer

a) A turbine via two drive shafts

Answer

b) A compressor via a drive shaft

Question 9

1811. Which engine has the greatest bypass ratio? (Level 2)

Accepted Answer

b) Propfans engine

Answer

a) Turbofan engine

Answer

c) Turbojet engine

Question 10

1812. Bernoulli's Theorem states that at any point in a flow of gas. (Level 1)

Accepted Answer

c) The total energy remains constant.

Answer

a) The static pressure and dynamic pressure are equal.

Answer

b) The static pressure is less than the dynamic pressure.

Question 11

1813. Which factors are NOT important for the combustion process? (Level 1)

Accepted Answer

c) Minimum decrease fuel consumption

Answer

a) Minimum decrease in pressure

Answer

b) Maximum increase of energy

Question 12

1814. The primary function of the turbine (Level 1)

Accepted Answer

a) Supply the torque which is necessary to drive the compressor

Answer

b) Increases the pressure of the incoming air

Answer

c) Increases the velocity of the incoming air

Question 13

1815. The fuel air mixture is burned in the combustion chamber (Level 1)

Accepted Answer

a) The temperature, the volume of the air increases and the air pressure stays almost constant.

Answer

b) The pressure, the volume and the temperature of the air increases

Answer

c) The temperature, the pressure of the air increases and the volume stays almost constant.

Question 14

1816. The term Pt5 means. (Level 1)

Accepted Answer

b) Pressure and temperature at station No.5.

Answer

a) The total pressure at station No.5.

Answer

c) The total inlet pressure outlet No.5

Question 15

1817. The external efficiency of engine mainly depends on (Level 2)

Accepted Answer

b) The aircraft speed and the exhaust gas velocity

Answer

a) The aircraft speed and the exhaust gas pressure

Answer

c) The aircraft speed and the exhaust gas temperature

Question 16

1818. A flat rated engine gives a constant thrust at (Level 2)

Accepted Answer

a) All ambient conditions below this flat rate temperature.

Answer

b) All ambient conditions above this flat rate temperature.

Answer

c) All ambient conditions

Question 17

1819. Which parameters are the engines used to measure the thrust? (Level 2)

Accepted Answer

a) The engine pressure ratio or the RPM

Answer

b) The engine pressure ratio or the engine burn temperature

Answer

c) The engine fuel flow or the RPM

Question 18

1820. The term thrust specific fuel consumption (TSFC) is (Level 2)

Accepted Answer

c) The amount of fuel which an engine needs to make 1kN of thrust for 1hour.

Answer

a) The amount of fuel which an engine used at 100% speed for 1hour.

Answer

b) The amount of fuel which an engine used at idle speed for 1hour.

Question 19

1821. The equation shows that 1lb of thrust equals 1 thrust horsepower (THP) at a speed of (Level 2)

Accepted Answer

c) At a speed of 375mph

Answer

a) At a speed of 175mph

Answer

b) At a speed of 275mph

Question 20

1822. The engine air intake has: (Level 1)

Accepted Answer

a) The shape divergent

Answer

b) The shape convergent

Answer

c) The shape constant.

Question 21

1823. This design employs an external oblique shock wave in supersonic engine inlet for (Level 1)

Accepted Answer

b) Slow the supersonic airflow before the normal shock occurs.

Answer

a) Increase the supersonic airflow before the normal shock occurs.

Answer

c) Prevent the shock occurs.

Question 22

1828. Which two elements make up the axial flow compressor assembly? (Level 1)

Accepted Answer

a) Rotor and stator.

Answer

b) Stator and diffuser.

Answer

c) Compressor and manifold.

Question 23

1829. What is meant by a compressor stage? (Level 1)

Accepted Answer

a) One rotor and one stator assembly.

Answer

b) All rotors and stators.

Answer

c) One rotor and one guide vane assembly.

Question 24

1830. The ring of fixed blades at the intake of an axial flow compressor are called. (Level 1)

Accepted Answer

a) Inlet guide vanes.

Answer

b) First stage stator blades.

Answer

c) First stage diffuser blades.

Question 25

1831. The main components of a centrifugal flow compressor are: (Level 1)

Accepted Answer

c) The impeller, the diffuser and the compressor manifold.

Answer

a) The rotor, the stator and the guide vane assembly.

Answer

b) The rotor, the stator and the compressor manifold.

Question 26

1832. The velocity of the airflow through the compressor will be? (Level 1)

Accepted Answer

c) Kept constantly

Answer

a) increased

Answer

b) Decreased

Question 27

1833. Axial flow and centrifugal flow compressors have their own specific advantages and disadvantages. Which following statement is NOT correct? (Level 2)

Accepted Answer

b) Axial flow compressors have a good efficiency over a wide speed range.

Answer

a) Centrifugal flow compressors have a very high pressure rise per stage.

Answer

c) Engines with axial flow compressors cause less drag than engines with centrifugal flow compressors

Question 28

1834. The compression ratio of an axial flow compressor is a function of the. (Level 1)

Accepted Answer

a) Number of compressor stages.

Answer

b) Air inlet velocity.

Answer

c) Rotor diameter.

Question 29

1835. The used of bleed valves to avoid engine stall and surge. (Level 2)

Accepted Answer

a) In the mid section and sometimes in the aft section of the engine compressor

Answer

b) In the mid section and sometimes in the aft section of the engine turbine

Answer

c) In the mid section and sometimes in the forward section of the engine compressor

Question 30

1836. The advantage of the variable stator vanes (Level 2)

Accepted Answer

b) Optimum angle of attack on the following rotor blades

Answer

a) Optimum velocity of airflow on the following rotor blades

Answer

c) Optimum pressure of airflow on the following rotor blades

Question 31

1837. For basic compressor control the main engine control (MEC) uses (Level 2)

Accepted Answer

c) The core engine speed N2 and the compressor inlet temperature CIT.

Answer

a) The core engine speed N2 and the compressor inlet pressure.

Answer

b) The compressor outlet temperature COT and the compressor inlet temperature CIT.

Question 32

1838. The variable stator vane actuators operate by (Level 1)

Accepted Answer

b) Engine fuel pressure power.

Answer

a) Aircraft hydraulic power.

Answer

c) Electrical motor power.

Question 33

1839. The variable stator vanes (VSV) schedule open or close applies for (Level 2)

Accepted Answer

a) Air inlet temperature only

Answer

b) Air inlet pressure only

Answer

c) Air inlet temperature and pressure.

Question 34

1840. The FADEC calculates a variable stator vane (VSV) demand signal based on (Level 2)

Accepted Answer

a) The actual engine speed and compressor inlet temperature.

Answer

b) The actual engine speed and compressor inlet pressure.

Answer

c) The compressor inlet temperature and pressure.

Question 35

1841. The fan speed of a twin spool axial compressor engine is the same as the. (Level 1)

Accepted Answer

a) Low pressure compressor.

Answer

b) Forward turbine wheel.

Answer

c) High pressure compressor.

Question 36

1842. The non-rotating axial-flow compressor airfoils in an aircraft gas turbine are known as. (Level 2)

Accepted Answer

a) Stator vanes.

Answer

b) Bleed vanes.

Answer

c) Pressurization vanes.

Question 37

1843. What is used to aid in stabilization of high compressor airflow? (Level 2)

Accepted Answer

a) Variable stator vanes and/or compressor bleed valves.

Answer

b) Pressurization and dump valves.

Answer

c) Stator vanes and rotor vanes.

Question 38

1845. The flame tube of annular combustion chamber has major parts: (Level 2)

Accepted Answer

c) The dome, the inner liner and the outer liner.

Answer

a) The air supply duct, the inner liner and the outer liner.

Answer

b) The casing, the inner liner and the outer liner.

Question 39

1846. What is a can-annular combustion system? (Level 2)

Accepted Answer

c) A set of flame tubes, enclosed in a common air casing.

Answer

a) One common flame tube closed in a common air casing.

Answer

b) A set of flame tubes, each mounted in a separate air casing.

Question 40

1847. The primary conditions are necessary for correct and safe combustion are: (Level 2)

Accepted Answer

b) The ratio of air and fuel, the airflow velocity.

Answer

a) The ratio of air and fuel, the airflow pressure.

Answer

c) The ratio of air and fuel. the airflow temperature.

Question 41

1848. The mainly airflow which comes from the compressor to combustion is (Level 1)

Accepted Answer

b) The secondary airflow.

Answer

a) The primary airflow,

Answer

c) The burned airflow.

Question 42

1849. The airflow that comes from the compressor is decreased by: (Level 2)

Accepted Answer

a) The diffuser, the restrictors and by swirl vanes

Answer

b) The diffuser, the restrictors and by guide vanes

Answer

c) The diffuser, the restrictors and by supply ducts.

Question 43

1850. An air fuel mixture burns best at (Level 1)

Accepted Answer

a) A ratio of 15:1

Answer

b) A ratio of 7.5:1

Answer

c) A ratio of 24:1

Question 44

1851. The flame tube is cooled by: (Level 1)

Accepted Answer

b) The secondary airflow

Answer

a) The primary airflow

Answer

c) Cooling air system.

Question 45

1852. A thin coating of ceramic material on the inner surface of the flame tube for (Level 1)

Accepted Answer

c) Protect the inner line
against heat.

Answer

a) Strengthen the inner liner.

Answer

b) Seal air from the inner liner.

Question 46

1853. The combustion case has: (Level 2)

Accepted Answer

a) An outer wall, an inner wall and a diffuser.

Answer

b) A inner liner, a outer liner and a diffuser.

Answer

c) An outer wall, an inner wall and a guide vane.

Question 47

1854. What are the two main basic components of the turbine section in a gas turbine engine? (Level 1)

Accepted Answer

a) Stator and rotor.

Answer

b) Hot and cold.

Answer

c) Impeller and diffuser.

Question 48

1855. The turbine blades are prevented from corrosion of sulfuric acid by (Level 2)

Accepted Answer

a) Using the correct kind of jet fuel.

Answer

b) Using the correct ratio of air fuel mix.

Answer

c) Using the ceramic coating.

Question 49

1856. In convection cooling method, where does the cooling air escapes during cooling the turbine blades (Level 2)

Accepted Answer

c) At the trailing edges and at the blade tips

Answer

a) At the leading edges and at the blade tips

Answer

b) At the leading edges and a the trailing edges of blades.

Question 50

1857. On most modern gas turbine engines, a combination of all 3 cooling methods of convection, impingement and film cooling is used on? (Level 2)

Accepted Answer

a) The first stage nozzle guide vanes and the first stage rotor blades

Answer

b) The first stage nozzle guide vanes and The second stage nozzle guide vanes.

Answer

c) The second stage rotor blades and the second stage nozzle guide vanes.

Question 51

1858. Which does the engine use for the active clearance control of LP turbine? (Level 1)

Accepted Answer

b) The engine fan air.

Answer

a) Compressor bleed air

Answer

c) The ram air.

Question 52

1859. The clearance control valves are normally controlled by the engine control unit and actuated by (Level 1)

Accepted Answer

c) Fuel pressure from the engine fuel system

Answer

a) Electric motor control valves.

Answer

b) Pneumatic pressures from PS3 station.

Question 53

1860. In convergent exhaust nozzles, the maximum airflow at pressure ratios should be below of (Level 1)

Accepted Answer

a) Approximately 2:1

Answer

b) Approximately 3:1

Answer

c) Approximately 1:1

Question 54

1861. On a four engine aircraft the angle of the reverse stream can be matched by (Level 1)

Accepted Answer

b) The correct arrangement of the cascade vanes in the thrust reverser cowlings.

Answer

a) The correct arrangement of the thrust reverser actuators.

Answer

c) The correct troke of the thrust reverser actuators.

Question 55

1862. What indication does the pilot receive that thrust reversers have deployed? (Level 1)

Accepted Answer

b) A sequence of lights.

Answer

a) An audible warning.

Answer

c) A feeling of rapid deceleration.

Question 56

1865. Speed control of the pneumatic thrust reverse system is via (Level 2)

Accepted Answer

c) The cam mechanism on the feedback rod.

Answer

a) The speed sensor of the air motor.

Answer

b) The overspeed mechanism of the air motor.

Question 57

1866. How is the pneumatically operated reverser is latched in deploy position? (Level 2)

Accepted Answer

c) By the brake in the pneumatic drive unit.

Answer

a) By locking valve.

Answer

b) By cam lock mechanism.

Question 58

1867. The main components of the hydraulically operated thrust reverser system are: (Level 2)

Accepted Answer

a) The reverser control valve module and the hydraulic actuators to deploy or stow the reverser.

Answer

b) The reverser control valve module, gearboxes, ballscrew actuators.

Answer

c) The reverser control valve module, gearboxes and the hydraulic actuators to deploy or stow the reverser.

Question 59

1868. To avoid the jamming of the translating sleeve, the reverser system use: (Level 2)

Accepted Answer

c) The flexible drive shafts.

Answer

a) A directional control valve.

Answer

b) A the synchronize control valve.

Question 60

1870. The accessory gearbox of a high bypass engine is. (Level 1)

Accepted Answer

a) On the HP Compressor housing.

Answer

b) In the forward bearing housing.

Answer

c) Attached to the turbine casing.

Question 61

1872. What bearing is used to take axial loads on a main rotation shaft of a gas turbine engine? (Level 2)

Accepted Answer

c) Ball bearing.

Answer

a) Plain bearing.

Answer

b) Roller bearing.

Question 62

1873. A floating bearing is usually (Level 2)

Accepted Answer

b) Roller bearing.

Answer

a) Plain bearing.

Answer

c) Ball bearing.

Question 63

1874. The type of seal between the drive shaft and the gearbox is: (Level 1)

Accepted Answer

a) Carbon seals

Answer

b) Labyrinth seals.

Answer

c) Rubber seals.

Question 64

1875. How are bearings lubricated? (Level 1)

Accepted Answer

b) By engine oil system.

Answer

a) By greases.

Answer

c) By engine fuel system.

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