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Posted By: gopal Member Level: Diamond Posted Date: 31 Aug 2008
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2005 Jawaharlal Nehru Technological University Aeronautical III B.Tech. I Semester Regular Examinations, November -2005,TURBO MACHINERY Question paper
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Code No: RR312003 Set No.4
III B.Tech. I Semester Regular Examinations, November -2005
TURBO MACHINERY
(Production Engineering)
Time: 3 hours Max Marks: 80
Answer any FIVE Questions
All Questions carry equal marks
? ? ? ? ?
1. Describe, with the help of simple sketches the working principle of impulse and
reaction turbines? [16]
2. (a) Draw the inlet and outlet velocity triangles of an axial flow compressor?
(b) An axial flow compressor of 50% reaction desig has blades with inlet and outlet
angles of 400 and 100. The compressor is to produce a pressure ratio of 5:1
with an overall isentropic efficiency of 87%. The mean blade speed and axial
velocity are constant through out the compressor. Assuming blade velocity of
180 m/s and work input factor 0.85, find the number of stages required.
[6+10]
3. The following data pertaining to a centrifugal compressor:
overall diameter of the impeller - 60cm
speed - 14000RPM
slip factor - 0.9
power input factor - 1.04
eye tip diameter - 35cm
eye root diameter - 20cm
total mass flow - 20kg/s
inlet total head temperature and pressure - 250C and 1.01bar
total head isentropic efficiency - 82%
Determine the total head pressure ratio and power required to drive the compressor,
if the velocity of air at inlet is axial. [16]
4. (a) What are the different flame stabilization methods used in gas turbine com-
bustion chamber?
(b) A gas turbine plant operates between temperature limits of 180C and 7800C.
The air is taken from ambient at a pressure f 1.02bar compressed to 7bar
in the compressor. The heat addition takes place in a heat exchanger and
combustion chamber. The hot gases are expanded in two stages such that
the expansion work is maximum. The air is re heated to 7800C after the first
stage. Determine work output, efficiency, work ratio if the mass flow rate of
air is 19kg/s. Take Cp = 1.005 kJ/kg.K and
= 1.4. [6+10]
5. The velocity of steam at inlet to a simple impulse turbine is 1000m/s, and the
nozzle angle is 180. The blade speed is 400m/s and the blades are symmetrical.
Determine the blade angles if the steam is to enter the blades without shock. If
the friction effects on the blade are negligible, calculate the tangential force on the
blades and the diagram power for a mass flow of 0.75kg/s. What is the axial thrust
and the diagram efficiency? [16]
6. The following data refers to a 50% reaction turbine;drum diameter : 2m, speed of
rotation : 800RPM, and steam flow rate is 15kg/s. The height blade is 15cm and
the steam has a pressure of 0.4bar and 0.95 dryness fraction. For 200 discharge
angle and assuming turbine efficiency as 80%. Estimate the power developed in
this particular ring and enthalpy drop when the steam passes through the turbine
pair. [16]
7. A Turbo-jet engine inducts 51kg/s and propels an aircraft with an uniform flight
speed of 912kg/h. The isentropic enthalpy charge for the nozzle is 200kJ/kg and its
velocity co-efficient is 0.96. The fuel-air ratio is 0.0119, th ecombustion efficiency
is 0.96 and the lower heating value of the fuel is 10,500KJ/kg. Assume CV = 42
MJ/kg. Calculate
(a) the thermal efficiency of the engine,
(b) the fuel flow rate in kg/hr and total specific fuel consumption,
(c) the propulsion power in kW,
(d) the thrust power, and
(e) the propulsive efficiency. [16]
8. Write the short notes:-
(a) Stalling
(b) Incompressible flow
(c) Slip and Slip factor
(d) Combustion chamber types
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