Registration > lift > off : Which of these statements about compressor stall are correct or incorrect.i a ?
Question 34-1 : I is correct ii is correct i is correct ii is incorrect i is incorrect ii is correct i is incorrect ii is incorrect

In a compressor stage if the axial air velocity increases more than the rotor ?
Question 34-2 : Stall margin increases stall margin decreases pressure ratio will be too high relative air velocity becomes supersonic

Which of these statements about compressor stall are correct or incorrect.i a ?
Question 34-3 : I is incorrect ii is correct i is correct ii is incorrect i is incorrect ii is incorrect i is correct ii is correct

With regard to a twin spool turbofan an abortive start hung start will result in ?
Question 34-4 : N2 speed stabilising at a lower than normal rpm and a subsequent increase in egt n2 speed stabilising at a higher than normal rpm and a subsequent increase in egt n2 speed stabilising at a lower than normal rpm and a subsequent decrease in egt n2 speed stabilising at a higher than normal rpm and a subsequent decrease in egt

Which of the following statements is correct about the flow in a divergent ?
Question 34-5 : I is incorrect ii is correct i is correct ii is incorrect i is correct ii is correct i is incorrect ii is incorrect

One of the functions of a gas turbine engine subsonic intake is to ?
Question 34-6 : Decrease airflow velocity increase total pressure increase airflow velocity decrease static temperature

One of the advantages of multiple spool jet engine designs is that ?
Question 34-7 : A smaller air starter driving only a single spool can be used if one spool seizes the remaining spool s will continue to operate normally a compressor stall cannot occur under any condition engine length can be reduced

Which of these statements about compressor stall are correct or incorrect.i a ?
Question 34-8 : I is incorrect ii is incorrect i is correct ii is incorrect i is incorrect ii is correct i is correct ii is correct

After a successful start of a high bypass turbofan engine the air starter ?
Question 34-9 : Is disengaged by the coupling between engine n2 spool and starter by the use of centrifugal forces is disengaged by using a clutch that is controlled by the main engine control is disengaged by the coupling between engine n1 spool and starter by the use of centrifugal forces remains engaged and rotates continuously with the n2 spool

Both gas turbine and piston engines use a cycle made up of induction ?
Question 34-10 : I is correct ii is incorrect i is incorrect ii is incorrect i is incorrect ii is correct i is correct ii is correct

Which of these statements about compressor stall are correct or incorrect.i a ?
Question 34-11 : I is correct ii is incorrect i is incorrect ii is incorrect i is incorrect ii is correct i is correct ii is correct

The following problems may occur when starting a twin spool turbofan engine ?
Question 34-12 : No n1 rotation although n2 may accelerate normally no n2 rotation although n1 may accelerate normally a hung abortive start with no light up indication after 'fuel on' selection a hung abortive start with fuel flow indication zero after 'fuel on' selection

Both gas turbine and piston engines use a cycle made up of induction ?
Question 34-13 : I is incorrect ii is correct i is incorrect ii is incorrect i is correct ii is correct i is correct ii is incorrect
The most unfavourable conditions for adequate inlet air flow of a turbofan ?
Question 34-14 : Maximum take off thrust zero forward speed and strong crosswind conditions maximum thrust during climb out with strong crosswind idle thrust zero forward speed with no wind maximum thrust at rotation speed on the ground during take off

If a twin spool gas turbine engine is controlled by a conventional n2 control ?
Question 34-15 : Overspeed of the lp turbine n2 and epr increase n1 and n2 increase n1 decrease and epr increase
The rotor blades of an axial compressor of a gas turbine engine are often ?
Question 34-16 : Limits damage to the blades due to vibration limits fod damage limits damage due to creep facilitates easy assembly and removal

For a turbine engine the self sustaining speed relates to the minimum rpm at ?
Question 34-17 : Will continue to operate without any starter motor assistance is designed to idle after starting operates most efficiently in the cruise will enable the generators to supply bus bar voltage

The primary function of the diffuser located between the compressor and the ?
Question 34-18 : Decrease the flow velocity increase total pressure convert kinetic energy into mechanical energy increase the temperature of the compressed air

A fadec on a gas turbine engine ?
Question 34-19 : Is single fault tolerant is a single channel system is a three channel system consists of two identical channels cross linked through an non engine related aircraft computer

When a turbo prop aeroplane decelerates during the intial part of the landing ?
Question 34-20 : Produces negative thrust produces zero thrust is feathered produces positive thrust

Most high bypass unmixed turbofan engines are equipped with a cold exhaust ?
Question 34-21 : Save costs and mass at the expense of a reduction in available reverse thrust prevent disturbance of cold exhaust reversed airflow by the hot exhaust reversed gas flow reduce the risk of exhaust gas re ingestion prevent extra fuel consumption due to operation of the hot exhaust reverser turbine reverser

A booster or lp compressor in a twin spool turbofan ?
Question 34-22 : Rotates at the same rotor speed as the fan rotates at the same rotor speed as the hp turbine rotates at a rotor speed different from both fan hp compressor and hp turbine rotates at the same rotor speed as the hp compressor

The function of the swirl vanes round the fuel nozzles is to.1 increase air ?
Question 34-23 : 2 3 1 2 1 2 3 1 only

The take off of a jet aeroplane may be performed with 'reduced thrust' in order ?
Question 34-24 : Reduce maintenance costs save fuel reduce take off noise reduce the risk of engine failure during take off

In an ignition system during a normal start of a gas turbine engine igniter ?
Question 34-25 : Should commence prior to fuel entering the combustion chamber should commence after fuel has entered the combustion chamber should commence prior to starter motor engagement to prevent a hot start commences upon starter motor engagement and is deactivated at a rotor speed of approximately 15% below idle rpm

A gas turbine engine is run at ground idle for a period of time prior to ?
Question 34-26 : Prevent seizure of the rotor blades in their seals prevent vapour lock in the fuel control and/or fuel lines prevent seizure of the engine bearings allow the engine oil to cool

The purpose of variable by pass valves in a high bypass turbofan engine between ?
Question 34-27 : Prevent fan stall and lp compressor stall during engine start and low rotor speeds provide sufficient air to the hp compressor during engine start prevent fan surge at high rotor speeds high rpm prevent hp compressor stall during engine start

If a gas turbine engine fuel/oil heat exchanger is located downstream of the hp ?
Question 34-28 : Rise rise and the fuel nozzles eventually to become clogged fall fall and the oil jets eventually to become clogged
The compressor pressure ratio of an axial flow compressor is primarily ?
Question 34-29 : Number of stages rotor diameter compressor inlet temperature design value compressor inlet pressure design value

In a theoretical gas turbine cycle combustion takes place at constant ?
Question 34-30 : Pressure energy temperature volume

When a gas turbine engine accelerates from idle to take off thrust and the ?
Question 34-31 : A compressor stall stagnation supersonic airflow at the compressor blade trailing edges a compressor blade airflow angle of attack that is too small

Which of the following parameters remains constant in a divergent subsonic gas ?
Question 34-32 : Total temperature static pressure dynamic pressure static temperature

The most favourable conditions to apply the flexible take off procedure are .1 ?
Question 34-33 : 2 4 5 1 3 5 2 3 6 2 4 6

Assuming the jet pipe is not choked the equation to calculate jet engine thrust ?
Question 34-34 : T = m vj vv t = m vv vj t = m vv + vj t = mvj

Given . p0 = static ambient pressure .t0 = static ambient temperature.m = air ?
Question 34-35 : T = m vj vv + a pj p0 t = m vv vj + a t j t0 t = m vv vj + a pj p0 t = m vj vv + a tj t0

The axial compressor of a gas turbine engine usually has more stages than its ?
Question 34-36 : The power output of a turbine stage is higher than the power consumption of a compressor stage the compressor consumes much more power than the turbine bleed air is taken from the compressor turbine speed is much higher than compressor speed

On a fadec gas turbine engine during normal flight the power for the fadec's ?
Question 34-37 : The fadec power source s on the engine the aircraft battery the aircraft generator the apu generator

In a gas turbine combustion chamber ?
Question 34-38 : Secondary air is required for cooling of the inner casing the gas pressure increases in an axial downstream direction the axial velocity of the gas stream is greatest behind the swirl vanes the gas temperature is highest at the chamber outlet

If there is a single input data failure on a fadec gas turbine engine ?
Question 34-39 : The engine continues to operate normally the engine stops the engine is set at a fail safe thrust the electronic engine control unit uses a constant data value for computation

Concerning the fuel system high pressure shut off valve hpsov of a gas turbine ?
Question 34-40 : Ignition is activated before fuel is delivered by the hpsov to the fuel nozzles the hpsov is located between the hp fuel pump and the fuel control unit manual hpsov control from the cockpit is not possible with fadec equipped engines the hpsov is mounted in the wing front spar near the pylon

~
Exclusive rights reserved. Reproduction prohibited under penalty of prosecution.
1319 Free Training Exam Other source study: Ulm theorique examen 34