1. Blade is an angle formed by a
line perpendicular to the propeller shaft and line formed by the
(a)
Relative wind
(b)
Apparent wind
(c)
Chord of the blade
(d)
Blade face
2. Thrust produced by a rotating
propeller is a result of
(a)
Propeller slippage
(b)
An area of low pressure behind the propeller
(c)
An area of decreased pressure immediately in front of
the pressure blades
(d)
The angle of relative wind and rotational velocity wind
and rotational velocity of the propeller
3. Propeller blade station number
increase from
(a)
Huh to tip
(b)
Tip to hule
(c)
Leading edge to aft edge
(d)
Aft edge of leading edge
4. It should have high specific
gravity
(a)
Low pan point
5. Velocity index should be high.
High freezing point – at a cold atm the water contents in the fuel in having
tendency to form in a ice crystal
6. It should be filtered to jet
engine
(a)
It should have low carbon content after burning the
fuel
7. In twin spool engine, with
constant N2,
compressor inlet temperature is decreasing then
(a)
N2
changes
(b)
Fuel flow increases
(c)
N1 decreases
(d)
The ratio N1 is maintained constant
N2
8. The thrust developed by high
bypass ratio engine is
(a)
Indicated by EGT
(b)
Indicated by N2
(c)
Proportional fan speed
(d)
Not affected by ambient conditions
9. Perceived noise decibel (PNDB)
level is low in case of
(a)
Pure jets without noise suppressor
(b)
Straight jet with noise suppressor
(c)
Low by pass jets
(d)
High by pass jets with acoustic panel
10. Ignitor plug spark is due to
(a)
High frequency
(b)
High input current
(c)
Discharge (storage) capacitor
(d)
DC voltage
11. In a ‘hot tank’ oil system
(a)
Oil cooler is not provided
(b)
Oil is stored in a separate tank
(c)
Oil is at high temp in the tank
(d)
De-aerator effect is very slow
12. If jet velocity and mass flow
is constant for a jet engine then thrust
(a)
Is maximum when aircraft speed is minimum
(b)
Is maximum when aircraft speed is maximum
(c)
Is more when jet velocity and inlet velocity are equal
(d)
Is always constant
13. Water injection systems are provides for the
jet engine for the thrust augmentation the thrust augmentation for water
injection can be caused and by two methods.
(a)
By adding or injecting water at the compressor inlet
(b)
By adding or injecting water at the differ section
Fig shown that
a water tank made up of aluminum or sheet metal allows the water flow a
regulating
It then panes
to the pressure regulating V/o of the diffuse and compressor inlet thought
which water injection in done by providing two manifolds at the diffuse and
compressor manifold.
A water heater
is provided for the water to not formed ice in cold atm or cold weather
condition
A drain a/v
provided to drain full water tank after are it is generally use of after
getting sufficient thrust by water injection
Water injection
system used when aircraft an going to take off
14. In a compressor space between
surge line and working lines called
(a)
Safety margin on surge margin
(b)
Stable zone unstable zone
(c)
Unstable zone
(d)
Stagger zone
15. Hottest zone in turbine
engine is
(a)
Compressor outlet
(b)
Turbine
(c)
1st stage NGV
(d)
Exhaust nozzle
16. In a high by pass engine
NGV’s are eliminated
(a)
To reduced noise
(b)
To reduce weight
(c)
To increase efficiency
(d)
To satisfy 1 and 2 above
For maximum thrust
The
thrust augmentation is achieved a the compressor inlet by injecting water at
the compressor inlet which increases mass airflow and their by thrust
Thrust
augmentation is achieved a the diffuser section by injecting water at the
diffuser section and which als the diffuser section and decreases the
temperature of the diffuser section which gives high deme man airflow high
affect to maximum
17. Brayton cycle is
(a)
Constant temperature cycle
(b)
Constant volume cycle
(c)
Constant pressure and constant temperature cycle
18. NGV’s of turbine are usually
(a)
Hollow
(b)
Solid
(c)
Air cooled
(d)
As per (1) & (2) above
19. Most common defects in
combustion chamber is
(a)
Crack and burning
(b)
Scoring
(c)
Pitting
(d)
Blistering
20. Jet engine ignition system.
Jet engine
ignition system is a high intensity and dual capacitor discharge type are used
The
two system are used for the ignition system
(a)
Low voltage A.C or D.C type ignition system
(b)
High voltage capacitor discharge type ignition system
21. High voltage capacitor
discharge type ignition system
FIGURE SHOWN HIGH VOLTAGE
CAPACITOR DISHCARGE TYPE CUT (A.G)
A
115 A.C is provided bu E.S.I. but to the primary coil of the transformer A to
reduce the noise level a filter cut is provided at the primary
After
paning 115V at the primary a seen way coil induces a voltage of about 2000V
approximately which paner through solid rectifier A through resistance to the
dual capacitor or storage capacitor which store the electrically charger
In
the next cycle a 20000 is paned through rectifier B this resistance
22. Combustion chamber used in a
modern jet engines are
(a)
Can annular type
(b)
Annular type
(c)
Can type
(d)
As stated in 1 and 2
23. Exhaust nozzle is
(a)
No necessary for jet engines
(b)
Made up of titanium alloy
(c)
Made up of aluminum alloy
(d)
A must for jet engine
24. Internal energy of a perfect
gas is
(a)
A function of temperature only
(b)
A function of pressure only
(c)
Always constant
(d)
A function of temperature and pressure
25. The turbo jet engines
(a)
Can be used in thermal power stations as prime stations
as primer movers
(b)
Are more efficient at lower altitudes
(c)
Work on Newton ’s
third law of motion
(d)
(2) and (3) above are correct
26. Compression process in axial
compressor is
(a)
Isothermal
(b)
Adiabatic
(c)
Isobaric
(d)
Isometric
27. Compressor pressure ratio of
an engine compressor depends upon
(a)
Ambient pressure
(b)
Ambient temperature and ambient pressure
(c)
Speed and ambient pressure
(d)
Speed mass airflow and ambient temperature
The energy stored in a dual
capacitor and storage charger at a fule charge level and then tenses the tube
this caused charger when fully developed it induces in the primary winding of
the transformer (TRIGGER), which is of up to app 2000 V
This
induces a appx of 20,000V to the secondary of the tram former winding and which
gives high intensity current flow thr ignite plug which gives spark
A
bleeder resistance are provided for troiger capacitor to give protection for
excess voltage
Two
igniter plug are used for capacitor discharge type cht for alternate operations
28. The fuel nozzles used in
modern gas turbine engines
(a)
Are always of dual type
(b)
Are identical for engine with same power rating
(c)
Are welded to the combustion chamber
(d)
Is the last component in the fuel system
29. Anti – icing system used on
jet aircrafts
(a)
Is fully automatic
(b)
Is to be used only to melt the ice formed
(c)
Never makes use of electrical heaters
(d)
Need not be used thought the flight
30. How many igniters are usually
used on a turbine engine having nine burner cans?
(a)
One
(b)
Two
(c)
Three
(d)
Nine
31. The material used for jet
engine is following main fine types
(a)
Titanium
(b)
Aluminum or Aluminum alloy
(c)
Nickel bare alloy
(d)
Nickel chrome alloy
(e)
Steel or stainless steel
Titanium are high resistant to 1000 &
corrosion and are used for fan blades and sometime for compressor vanes
Aluminum or aluminum alloy are
used for jet engine for its light weight characteristics it is high resistant
to corrosion heat
Nickel- chrome alloy’s re used
fore turbine blades, which stands for high temperature
Steel or stainless steel alloy
are used for rota vane or staten vane in an axial flow type jet
32. In an axial flow turbine
engine, compressor bled air is sometimes used to aid in the cooling of
(a)
Oil
(b)
IGV
(c)
Fuel cooler
(d)
Turbine
33. Which of the following
turbine fuel filters has the greatest filtering action?
(a)
Micron
(b)
Wire mesh
(c)
Wafer screen
(d)
Stacked charcoal
34. For starting a turbine engine
(a)
D.C motor is never used
(b)
Very very low cranking speeds are required
(c)
Ignition is necessary
(d)
Statements 2 and 3 are correct
35. Mechanical integrity of the
turbine as well as engine operating conditions of the engine can be checked by
(a)
Engine oil pressure
(b)
Exhaust gas temperature
(c)
Engine oil temperature
(d)
Engine pressure ratio
36. Which parameter will
determine engine power?
(a)
EGT and vibration meter
(b)
RPM and oil pressure
(c)
RPM and fuel pressure
(d)
EPR OR RPM
37. Mark the correct statement
(a)
Thrust reverse reduces landing roll
(b)
Oil pressure for jet engine is always regulated
(c)
VSV’ are not provided on modern jet engine
(d)
By providing fire wall in the engine cowl compartment
engine fire detection element can be eliminated