15.12 air system

Question 1

The large volume of air cools the hot sections of the engine and maintains the temperature to an acceptable range from

Answer 1

800 to 1150 °C.

Question 2

Turbine engines are usually divided into primary zones that isolate each other by a fireproof bulkhead or seals, what are the zones

Answer 2

The fan case compartment
The intermediate compressor case compartment
The core engine compartment

Question 3

what comes under zone 1

Answer 3

Zone 1 is the area around the fan case that contains the accessory case and the Electronic Engine Control (EEC).

Question 4

what comes under zone 2

Answer 4

Zone 2 is cooled by fan air from the upper part of the fan duct and is exhausted at the lower end back into the fan air stream.

Question 5

what is done to prevent the formation of ice on the engine inlet cowls

Answer 5

they are typically fitted with an anti-ice system

Question 6

is the engine anti-ice function manual or automatic

Answer 6

manual

Question 7

where is compressor cooling provide from

Answer 7

an intermediate compressor stage, which is relatively colder.

Question 8

what percentage range of the incoming air (primary) is directed inside the liner.

Answer 8

Approximately 20% - 30%

Question 9

what is One of the major limiting factors of a gas turbine engine

Answer 9

the temperature of the turbine section

Question 10

what is the most common method of cooling the turbine vanes and blades

Answer 10

to use engine bleed air.

Question 11

how is overheating of the turbine disc prevented

Answer 11

cooling air is directed over each side of the disc

Question 12

what is used for the sealing of the engine bearing chambers

Answer 12

The LP compressor bleed air

Question 13

what is the secondary function of the compressor

Answer 13

to supply air to the various systems on the aircraft

Question 14

what does the exact location of the bleed ports depend on

Answer 14

the pressure or temperature required for that particular system.