Download PTU (I.K.Gujral Punjab Technical University (IKGPTU)) B-Tech (Bachelor of Technology) Mechanical Engineering 2020 December 4th Sem 59132 Applied Thermodynamics Ii Previous Question Paper
Roll No.
Total No. of Pages : 02
Total No. of Questions : 18
B.Tech. (ME) (2012 Onwards) (Sem.?4)
APPLIED THERMODYNAMICS?II
Subject Code : BTME-404
M.Code : 59132
Time : 3 Hrs. Max. Marks : 60
INST RUCT IONS T O CANDIDAT ES :
1 .
SECT ION-A is COMPULSORY cons is ting of TEN questions carrying TWO marks
e ach.
2 .
SECT ION-B c ontains F IVE questions c arrying FIVE marks eac h and s tud ents
have to atte mpt any FOUR q ues tions.
3 .
SECT ION-C contains THREE questions carrying T EN marks e ach and s tudents
have to atte mpt any T WO questio ns.
SECTION-A
Answer briefly :
1.
Draw Brayton cycle.
2.
What is effect of clearance in working of reciprocating air compressor?
3.
What is surging and choking?
4.
What do you mean by degree of reaction?
5.
List merits of gas turbines over I.C engines.
6.
Name the different components of axial flow compressors.
7.
State the assumptions made in an ideal cycle's analysis of gas turbine.
8.
Define Work Ratio and Temperature Ratio.
9.
What is the principle of jet propulsion?
10. What is Turbojet?
SECTION-B
11. A simple closed cycle gas turbine plant receives air at 1 bar and 15?C and compressor it to
5 bar and then heats it to 800?C in the heating chamber. The hot air expands in a turbine
back to 1 bar. Calculate the power developed per kg of air supplied per second. Take Cp for
air as 1 kJ / kgK.
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12. Derive the-equation for work per Kg of air compressed by reciprocating air compressor
with and without clearance.
13. Describe briefly the distinction between rotary compressor and the reciprocating piston
compressor.
14. A turbojet engine flying at a speed of 800 km/hr consumes air at the rate of 45kg/s.
Calculate
(a) Jet exit velocity, the enthalpy change for the nozzle is 44.5 kcal/kg and the velocity
coefficient is 0.95.
(b) Fuel flow in kg/hr and thrust specific fuel consumption assuming that air fuel ratio is
80.
15. A multistage axial flow compressor absorbs 6000 H.P. when delivering 20 kg/s of air from
stagnation condition of 1 Kgf/cm2 and 288 K. If polytropic efficiency of compression is 0.9
and if the stage stagnation pressure ratio is constant. Calculate pressure at compressor
outlet.
SECTION-C
16. A centrifugal compressor delivers 580 m3 of free air when running at 800 rpm. Using the
following data: inlet pressure and temperature of air = 1.013 bar and 20?C, compressor
ratio = 3.5, isentropic efficiency = 83%, flow velocity throughout the compressor = 62 m/s,
the blades are radial at the outlet of the impeller tip diameter = 2 times eye diameter, blade
area coefficient = 10.94. Find :
(a) The input power required to run the compressor.
(b) Impeller diameters at inlet and outlet.
(c) Breadth of impeller at inlet.
(d) Impeller blade angle at inlet.
17. Draw T-S diagram for a single stage reciprocating air compressor and explain it.
18. Explain :
(a) Difference between adiabatic and isentropic process.
(b) Function of impeller and diffusion in centrifugal compressor.
NOTE : Disclosure of Identity by writing Mobile No. or Making of passing request on any
page of Answer Sheet will lead to UMC against the Student.
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This post was last modified on 13 February 2021