pp2 pointers

Question 1

combustion chamber

Answer 1

where the fuel-air mixture is burned in a gas turbine engine

Question 2

primary air

Answer 2

used for combustion

Question 3

primary airflow

Answer 3

this is the larger portion of the incoming airflow

responsible for the majority of the fuel combustion

Question 4

primary combustion zone

Answer 4

where the majority of the combustion process takes place

Question 5

secondary airflow

Answer 5

The smaller portion of the incoming airflow is directed into the secondary
combustion zone.

This airflow is used to provide additional oxygen for further combustion and to
help cool the combustor walls.

Question 6

can-annular combustion chamber

Answer 6

multiple tubes house separate fuel-air mixtures.

Question 7

Multi - Can combustion chambers

Answer 7

sequential cans with individual fuel-air mixtures attached to a central chamber.

Question 8

Multi-can combustion chamber

Answer 8

utilizes a series of individual combustor cans that function as individual burner units.

Question 9

in american built engines

Answer 9

the multi-cans are numbered in clockwised

Question 10

Annular combustion chambers

Answer 10

are ring-shaped and have fuel injectors surrounding the gas
turbine.

Question 11

annular combustion chamber

Answer 11

typically used for both small and large modern engines, this is due to its efficiency and light weight.

Question 12

combustion chamber

Answer 12

facilitates efficient energy exchange from the burning fuel-air mixture
to the gas turbine.

Question 13

multiple can
combustors.

Answer 13

Older centrifugal compressor engines and very old axial compressor engines have

Question 13

Interconnector tube

Answer 13

that connects different sections or components within a gas
turbine engine

Question 14

Flame Tubes

Answer 14

Flame propagation in a multiple-can type and a can-annular type combustion chamber is made
possible

Question 14

Kerosene-based fuels

Answer 14

have a slow propagation rate

Question 15

turbine blades

Answer 15

typically made from high-strength, heat-resistant materials such as nickel-based superalloys or cobalt-based superalloys.

Question 16

Fuel Drainage System

Answer 16

drain unburned fuel after engine shutdown

Question 17

diffuser in an axial flow compressor

Answer 17

to slow down the air from the compressor
before it reaches the combustion chamber.

Question 18

Compressor spool

Answer 18

refers to the rotating assembly that includes the compressor stages of the
engine

Question 19

Turbine spool

Answer 19

refers to the rotating assembly that includes the turbine stages of the engine

Question 19

turbofan engine, N2

Answer 19

refers to the rotational speed of the high-pressure spool or core
engine components

Question 19

turbofan engine, N1

Answer 19

refers to the rotational speed of the low-pressure spool or fan
section

Question 20

single spool

Answer 20

a single rotating assembly that includes both the compressor and the turbine stages.

driven by a single shaft

Question 20

dual spool

Answer 20

there are two separate rotating assemblies or spools: the lowpressure spool (LP spool) and the high-pressure spool (HP spool).

Question 21

multi-spool

Answer 21

there are three or more separate rotating assemblies or spools.