unit 4

Question 1

Discharged air used for aircraft engine anti-icing to heat-critical areas is taken from which engine area?

Answer 1

Compressor

Question 2

What is one of the first indications of ice formation at aircraft engine inlets?

Answer 2

Compressor stall

Question 3

On an F110-GE-129 engine, the anti-icing system prevents detrimental formation and accumulation of ice on front frame struts, forward centerbody, and

Answer 3

fan inlet guide vane flaps

Question 4

On an F110-GE-129 engine, compressor bleed air is used for anti-icing, customer bleed, and

Answer 4

low-pressure turbine cooling functions

Question 5

What law does the C-D supersonic inlet use to slow down the airflow?

Answer 5

Bernoulli’s law

Question 6

The bleed air system is different from the variable vane system in that it

Answer 6

bleeds off air after it has entered the engine

Question 7

The compressor bleed system reduces the probability of compressor stall in a dual-rotor engine by

Answer 7

reducing the amount of air available to the N2 compressor

Question 8

The cooling air for turbine nozzle vanes come from

Answer 8

the last few stages of the compressor

Question 9

Once the cooling airflow has done its job of cooling the turbine section, where does it go?

Answer 9

Into the gas stream to exit the engine

Question 10

The F110-GE-129 engine controls airflow through the engine with the

Answer 10

IGVs and VSVs

Question 11

Below what percentage of core engine speed are the VSV fully closed (cambered) on an F110-GE-129 engine?

Answer 11

45 percent

Question 12

On an F110-GE-129 engine, the MEC schedules the variable vane positions by the

Answer 12

fan discharge temperature and core engine speed

Question 13

What is the function of the flexible feedback cable on the F110-GE-129 engine variable vane system?

Answer 13

Transmit a mechanical feedback signal to the main engine control