Janardan Rai Nagar Rajasthan Vidyapeeth 2006 B.Tech Aeronautical Engineering INTRODUCTION TO PROPULSION SYSTEM - Question Paper

Model Question Paper

BSAE10- INTRODUCTION TO PROPULSION SYSTEM

Time : 3 hrs Maximum marks : 75

 

Instruction:

1. Question paper is divided into Group A, Group B and Group C

2. Each Group is 25 Marks

3. Figure to the right in bracket indicates marks.

4. Good Handwriting is expected

5. Assume suitable data if necessary.

 

Group A (25 Marks)

 

Answer any three questions (Question 1 is compulsory)

	(5)

 

Q.1 Explain what recycle and bypassing involve by mean of words and also by a diagram

(10)

Q.2 What are the dimensions of T, p, V, n and R? Calculate the pressure of 4.00 g mol

(10)

CO2 contained in a 6.2510-3 m3 fire extinguisher at 25c.

(10)

Q.3 What is the ideal critical volume? What is the advantage of using Vcj ?

(10)

Q.4 Drive the expression for Atkinson cycle?

Q.5 Give the comparison between Gas turbine and I.C. Engines?

Group B (25 Marks)

Answer any three questions (Questions 6 is compulsory)

	(5)

 

Q.6 A tank holds 10,000 kg of a saturated solution of Na2Co3 at 30C. you want to

crystallize from this solution 3000 kg of Na2Co3.H2O without any accompanying

water. To what temperature must the solution be cooled?

(10)

Q.7 Given a diabatic flow system of dry air which at some station is having M=3 and

total heat temperature as 295 ^oK while the static pressure is 0.49 bar for some other

station Where M = 1.5

(a)    Find the total temperature.

(b)    Find the stagnation pressure.

(c)    Find the static pressure.

(d)   

(10)

Find the amount of heat transfer which caused reduction in M. Is this positive or negative ?

 

(10)

Q.8 Give the comparison between radial and axial flow compressor ?

 

Q.9 Air is supplied t a convergent divergent nozzle at 5.1 bar and 815^O C and expands to 1 bar.

What is the mass flow per sq.cm of throat area and the exit velocity from the nozzle.

Assume isentropic flow with an initial velocity of 60 m / sec and that air behaves as a

(10)

perfect gas with C_P=1 kJ/^oK. What is the mach number at inlet, throat and exist of the nozzle ?

 

 

Q.10. A centrifugal compressor is desired to have a total pressure ratio of 4:1 . Eye is 30 cms

diameter. Axial velocity at inlet is 130 m / sec and the mass flow is 10 kgs / s. Velocity of flow

is 115 m / sec. The tip speed is 450 m / sec. and rpm is 16000 . Total head isentropic

efficiency is 78% and pressure coefficient is 0.72 . The ambient conditions are 1 bar and 15^O C.

Calculate.

(i)                 Static pressure ratio.

(ii)               Static pressure and of temp. at inlet and exit of compressor.

(iii)            

(10)

Work of compression per kg of air.

(iv) Theoretical power required to drive the compressor.

 

Group C (25 Marks)

 

All Questions are Compulsory.

Q.11 Fill in the blanks ( each question carry 2 marks)

(i) Pressure ratio for a Rayleight process

(ii) Prandtl Meyer relation for normal shock is ___________ .

(iii) If the flow is accelerated, the section is called _____________ .

(iv) For a divergent section with M² < 1 velocity _____________

(v) If the receivers pressure is greater than the design pressure the nozzle is said to be _________ .

 

Q.11 Multiple choice question. (Each question carry 2 marks)

 

(i) The Rayleigh line equation is

(a)

(ii) The fanning equation is

(a)dpt

 

(iii) Constant volume cycle is also known as ..

(a) Bryton cycle (b) Atkinson cycle (c) Joule cycle (d) None of the above.

 

(iv) Pressure loss factor is .

(a) (b) (c) (d) None of the above.

 

(v) When the shock waves are at right angles to the flow they are called

(a) Normal shocks (b) Oblique shocks (c) Compression Wave (d) None of the above.

 

 

 

 

 

 

 

 

Q.11 True or false (each question carry 1 marks).

 

(i) If the combustion in the chamber takes place at const. pressure and letting the volume

increase then it is called the constant pressure cycle.

 

(ii) In closed gas turbine cycle the combustion of the fuel is carried out internally no harmful

exhaust gases pass through the plant.

 

(iii) In practical gas turbine cycle the compression in the compressor and expansion the

turbine are isentropic.

 

(iv) Mechanical efficiency of gas turbine is considerably higher than that of the best I.C.

Engine.

 

(v) The overall efficiency of the turbine is much less then that of the reciprocating I.C.

Engine.

 

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