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CT FEB 2013 1) a) b) c) d)
Engine rumbles during starting and at low powercruise conditions. Pressurizing & drain valve malfunction. Cracked air duct. Fuelcontrol malfunction. All of the above. (ref/12A/491)
2)
a)
Pressurerelief valve of bearing chamber does not operate , the flow rate of oil will???? Increase
b) c)
Decrease Remain same
3) a) b) c) d)
Fuel additive used in GTE. Fungicide Anti-oxidizing agent, de-metal anticorrosiveagent De-additive All of the above
4) a)
Dissolved Water in fuel is detected by Aqua-disk capsule
b)
Globus of water
c) d)
Hazy look of fuel Both a & c
5) a) b) c)
Types of vibration indicator Velocity pick-up Piezo-electric type Both a & b
6) a) b)
Methods of cooling turbine blade in GTE Leading & trailing holes Film cooling
7) a)
Single crystal blade Turbine blade
8) a)
Igniter plug Wide gap at low pressure
9) Compressor bleed air a)middle & rear, increase air flow infront of inlet
10) RPM hung up during turbine start. 11) Propeller slip 12) droop 13) engine trimming a)on FCU change
14) Before shut down it is essential to run the engine atidle for few minutes. A) To avoid seizure of turbine blades & turbine case 15) Propeller tracking a) Constant pitch & controllable pitch at lower pitch. 16) Speed governor 17) Magnetic chip detector (MCD) a) Bridge gap 18) Dual ball bearing?> 19) Cartridge filter at low pressure &screen filter atoutlet of pump at high pressure. 20) API number liquid lighter then water value a) Greater than 10 b) Lower then 10 c) Remains up to 10 21) A flow of fluid metered by keeping the pressure drop ordifferential across the metering valve constant while varying the orifice valve. 22) FADEC power supply a) Dedicated EDG 23) High by pass engine use a) T/R uses secondary & primary air separately 24) Use of T/R should not cause Re-ingestion of hot gases 25) Thrust rating up to 31c 26) High viscosity index of oil
27) OIL marked written on filter 28) Lubrication oil to bearings is provided through vane isidentified by a) Thickest staticvane from lower position to bearing 29) Beta range a) Propeller lever blocked 30) TSS a) Auto feathering feature 31) Safety coupling a) For NTS if it fails 32) Fire extinguisher in engine is distributed by a) Spray nozzles & perforated tubes 33) Thermocouple used for a) Rate of temp rise detector 34) Turbojet engine largest take-off roll & less weight 35) EGT indication 36) Continues fire detection system 37) fin-wall type eutic salt bed 38) Thrust indication a) EPR 39) Tail wind on trimming a) Low trim 40) Auto ignition a) In flight start possible 41) Modern type ignition system uses a) Capacitor type 42) Igniter plug in jet engine a) High intense spark ignition
43) Centrifugal force tends to decrease blade angle 44) Annular inlet a) At nose of fuselage b) Just before start of fuselage c) Both a & b 45) Nozzle distortion by can type combustion chamber 46) Advantages of annular combustion chamber &disadvantage of can type combustion chamber 47) Disadvantages of shrouded blades a) Aero dynamic disadvantage due to thinner blade at tip 48) Full flow oil system 49) Functions of reverse flow combustion chamber 50) Wet thrust a) period of water injected in jet engine for thrust 51) Roller bearing takes only a) Radial load 52) Rise in temperature of compressor stages is equal todecrease of temp at turbine stages 53) Squeeze film bearing 54) Flat rated engine a) Part throttle b) More thrust by forward movement of the lever c) all of the above 55) Variation of speed in convergent divergent exhaust ductobtained 56) Bell mouth duct to increase inlet pressure then ambientpressure at the i nlet of compressor 57) In starter if carbon brushes is worn out a) Engine will not start 58)boro-scope inspection 59) In impulse turbine inlet & outlet area of blades issame
60) Impulse turbine blade diagram 61) Input of FCU 62) Mostly used fuel nozzle a) 2 stage b) Duplex style c) Both a & b 63) Which type of fuel nozzle atomizer is used a) Swirl type 64) Equation for universal gas law 65) TSFC is directly proportional to efficiency 66) Efficiency of dual impeller is more than single impeller& dual impeller size is smaller than single 67) Maximum pressure at outlet of compressor 68) Centrifugal impeller takes air in from center & cause to moves outward at diffusion 69) Propfan Otis pg 2-7 70) Calorific value 71) Tip speed Ts=(pie*diam* RPM)/60
( Otis pg 2-36)
72) Centrifugal compressor material a) Aluminum alloy b) Titanium wrought c) Casting 73) tip speed in compressor blade a) Mach 1 ( Otis pg 3-14) 74) Shroud aerodynamic drag reduces efficiency (pg 3-17)
75) In succeeding turbine stage pressure, velocity &temp a) Increase b) Decrease c) Remain same 76) GTE is a open cycle (Trg pg155)
77) Temp datum valve location 78) In combustion burner a) Pressure remain constant & volume increase 79) TSFC calculation 700*6.5=9100/475=0.5 80) Water wash after use of fire extinguisher methyl bromide 81) Exhaust duct a) Straighten the airflow & increase velocity b) Increase temp anda)
