1) In a turbojet engine, combustion occurs at Report

constant velocity

constant volume

constant pressure

2) Tubo-annular gas turbine combustion system consists of Report

A number of flame tubes in an annular air casing.

A number of flame tubes each with its own air casing

An annular flame tube in an annular air casing

3) In which type of turbine engine combustion chamber is the case and liner removed and installed as one unit during routine maintenance?. Report

Cannular

Annular

Can

4) In a turboprop engine, combustion takes place at constant Report

pressure

density

volume

5) The air passing through the combustion chamber is Report

entirely combined with fuel and burned

used to support combustion and to cool the engine

speeded up and heated by the action of the turbines

6) The air used for combustion is Report

Primary

Secondary

Primary and secondary

7) Combustion chamber flame temperature is in the order of Report

2000^oCentigrade

2000^oFahrenheit

2000 K

8) Hot spots in the combustion section of a turbojet engine are possible Report

dirty compressor blades

malfunctioning fuel nozzles

faulty igniter plugs

9) The approximate percentage of the mass airflow taken in by the flame tube snout is Report

8 %

18 %

82 %

10) What component creates a vortex in a gas turbine flame tube? Report

Tertiary hole

Swirl vanes

Cascade vanes

11) In the combustion chamber Report

static pressure and volume remains constant

static pressure decreases slightly and volume increases

static pressure and volume decreases

12) Which of the following types of combustion sections are used in aircraft turbine engines? Report

Annular, variable, and cascade vane

Multiple can, annular, and can-annular

Can, multiple can, and variable

13) Secondary air in the combustion chamber is used for Report

increasing axial velocity of gases

combustion

cooling

14) Duplex burners have Report

two calibrated outlets

variable orifices

a spring

15) The overall air/fuel ratio of a combustion chamber can vary between Report

45:1 and 130:1

130:1 and 200:1

10:1 and 45:1

16) When light-up takes place Report

the nozzle guide vanes spread the heat to adjacent flame tubes

interconnectors spread the heat to adjacent flame tubes

each flame tube is isolated from its neighbours

17) Why do the holes in the body of the duple burner provide air to the shroud around the burner head? Report

To assist atomisation of the fuel at slow running

To reduce burner temperature

To minimise carbon formation on the burner face

18) The air passing through the combustion chamber of a jet engine is Report

entirely combined with fuel and burned

used to support combustion and to cool the engine

speeded up and heated by the action of the turbines

19) A toroidal vortex is Report

a vapour trail visible in moist air conditions

a region in the combustion chamber of low velocity re-circulation

a bull-nosed cowling for deflecting air from the static

20) Why is it necessary to have a combustion drain system? Report

To prevent pressure build up in the combustion chamber

To prevent initial over-fuelling on start up or hot start

To allow water in the combustor to drain away

EASA Questions Mod 15: Gas Turbine Engine Set 5: Combustion Section

Set 1: Fundamentals

Set 2: Engine Performance

Set 3: Engine Inlet

Set 4: Eng. compressors

Set 5: Combustion Section

Set 6: Turbine Section

Set 7: Engine Exhaust

Set 8: Bearing and Seals

Set 9: Lubricants and Fuel

Set 10: Lubrication system

Set 11: Fuel Systems

Set 12: Air Systems

Set 13: Ignition Systems

Set 14: Engine Indication

Set 15: Power Augmentation

Set 16:Turboprop engines

Set 17: Turboshaft

Set 18: APU

Set 19:Powerplant Installation

Set 20: Fire Protection

Set 21:Engine Monitoring

Set 22: Engine Storage