## ME6404 Thermal Engineering question Paper April/May 2016

B.E./B.Tech. Degree Examinations April/may 2016

Question Paper code : 57556

Fourth Semester

Mechanical Engineering

ME6404-THERMAL ENGINEERING
(Regulation 2013)

Part A- (10 x 2 = 20 Marks)

1. State the assumptions made in air standard cycle analysis?
2. Define Mean effective pressure. Show that on a p-v diagram.
3. Show the valve overlapping period of a typical 4-stroke petrol engine on valve timing diagram.
4. Define the phenomenon knocking in SI engines.
5. Draw the shape of a supersonic nozzle.
6. Distinguish between impulse and reaction principles.
7. Define volumetric efficiency of an air compressor.
8. State the conditions which lower the volumetric efficiency of an air compressor.
9. Show the simple vapour compression cycle on pressure-enthalpy diagram.
10. List out the basic elements of an air conditioning system.

Part-B (5 x 16 = 80 Marks)

11.(a) The compression ratio for a single-cylinder engine operating on a dual cycle is 9. The maximum pressure in the cylinder is limited to 60 bar. The pressure and temperature of the air at the beginning of the cycle are 1 bar and 30'C. heat is added during constant pressure process upto 4 percent of the stroke. Assuming the cylinder diameter and stroke length as 250 mm and 300 mm respectively. If the number of working cycle is 3 per second.

(OR)

(b) The  swept volume of a diesel engine working on a dual cycle is 0.0053 m3 and clearnce volume is 0.00035 m3. the maximum pressure is 65 bar. Fuel injection ends at 5 percent of the stroke. the temperature and pressure at the start of the compression are 80'C and 0.9 bar. determine air standard efficiency of the cycle.

12.(a) Describe with suitable sketches the following system of a modern carburetor. (i) Main metering system (ii) Idling system (iii) Economic system (iv) Acceleration pump system (v) Choke

(OR)

(b) (i) With a neat sketch, explain the principle of work of a diesel injector.
(ii) A four stroke, four cylinder gasoline engine has a bore of 60 mm and a stroke of 100 mm. On test it develops a torque of 66.5 Nm when running at 3000 rpm. If the clearance volume in each cylinder is 60cc, the relative efficiency with respect to brake thermal efficiency is 0.5 and the calorific value of the fuel is 42 MJ/Kg, determine the fuel consumption in kg/h and the brake mean effective pressure.

13.(a) (i)Define critical pressure ratio of a nozzle and discuss why attainment of sonic velocity. Determine the maximum discharge through the nozzle.
(ii) Explain the metastable expansion of steam in a nozzle with help of h-s diagram.

(OR)

(b) A simple impulse turbine has one ring of moving blades running at 150 m/s. the absolute velocity of steam at exit from the stage is 85 m/s at an angle of 80’ from the tangential direstion. Blade velocity co-efficient is 0.82 and the rate of steam flowing through the stage is 2.5 kg/s. if the blades are equiangular, determine (i) Blade angles (ii) Nozzle angle (iii) Absolute velocity of steam issuing from the nozzle (iv) Axial thrust.

14.(a) A two stage air compressor consists of three cylinder having the same bore and stroke. The delivery pressure is 7 bar and the free air deliver is 4.3 m3/min. Air is drawn in at 1.013 bar, 150’C and an intercooler cools the air to 38’C. The index of compression is 1.3 for all three cylinders, Neglecting clearance volume. Calculate
(i) the intermediate pressure (ii) The power required to drive the compressor (iii) Isothermal efficiency.

(OR)

(b) With a neat sketch, describe the construction and working of a single-stage acting reciprocating air compressor. Also derive the equation for work done with clearance and without clearance.

15.(a) Describe the following refrigeration with layout : (i) Ammonia water system  (ii) Lithium-Bromide water system

(OR)

(b)(i) Describe the working principle of a centralized air conditioning system and enumerate the need for it.
(ii) List the loads the contribute to the overall cooling load.

## ME6604 gas Dynamics and Jet propulsion question Bank

Unit-1

Basic Concepts and Isentropic Flows

PART-A
PART A

1.     Define compressible fluid and incompressible fluid.
2.     Define nozzle and diffuser.
3.     What is meant by velocity of sound?
4.     Define mach number& Crocco Number
5.     What do you meant by stagnation pressure and stagnation temperature?
6.     Define stagnation enthalpy and stagnation density.
7.     What are the various regions of flow?
8.     Define Mach angle.
9.     What is meant by isentropic process?
10.    Define compressible fluid and incompressible fluid.
11.   What are the types of nozzles?
12.    What is meant by stagnation state?
13.      Define Mach cone and Mach wave.

PART-B

 1.     Derive an expression for the effect of mach number on compressibility. 2.     Derive the expression for an energy equation. 3.     A supersonic diffuser diffuses air in an isentropic flow from a mach number of 3 to a mach number of 1.5. The static conditions of air at inlet are 70 kpa and -7 C. If the mass flow rate of air is 125 kg/s, determine the stagnation conditions, areas at throat and exit, static conditions (pressure, temperature, velocity) of air at exit. 4.     A supersonic nozzle expands air from Po = 25 bar and T0 = 1050 K to an exit pressure of 4.35 bar: the exit are of the nozzle is 100 cm2. Determine i) throat area ii) pressure and temperature at the throat iii) temperature at exit iv) Exit velocity as fraction of the maximum attainable velocity v) mass flow rate. 5.     A conical diffuser has entry and exit area of 0.11 m2 and 0.44 m2 respectively. The pressure, temperature and velocity of air at entry are 0.18 Mpa, 37 ‘C and 267 m/s respectively.  Determine i) mass flow ratw  ii) the mach number, static temperature and static pressure of the air leaving diffuser  and iii) the net thrust acting on the diffuser 6.     Air at P1=3 bar and T1=227 C is flowing with a velocity of 200 m/s in a 0.3m diameter duct. If Cp=1050 J/KgK and ν=1.38. Determine the following (i)                Stagnation temperature and pressure (ii)             Mass flow rate of air (iii)           Mach number                 (Iv) Stagnation pressure. Assuming the flow is in compressible.

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