Academic/26 Refer/WI/ACAD/18

SHRI RAMSWAROOP MEMORIAL COLLEGE OF ENGG. & MANAGEMENT

B.Tech. [SEM IV (ME)]

QUIZ TEST-1

(Session : 2010-11)

APPLIED THERMODYNAMICS

(EME-401)

Roll No.

(To be filled by the Student)

Note: All questions are compulsory.

Part – A

(Questions from Tutorial Sheet) [10 Marks]

Q1) A gas turbine power plant operating on Brayton cycle has a pressure ratio of 8. The gas

temperature is 300K at the compressor inlet and 1300K at the turbine inlet. Utilizing the air

standard assumptions, Determine (i) The gas temperature at the exits of the compressor

and the turbine (ii) The back work ratio, and (iii) the thermal efficiency. (Q.No.1) [5]

Q2) In an air standard Brayton cycle the minimum and maximum temperature are 300K and

1200K respectively. The pressure ratio is that which maximizes the net work developed by

the cycle per unit mass of air flow. Calculate the compressor and turbine work, each in

kJ/kg air, and thermal efficiency of the cycle.(Q.No.9) [5]

Part – B [20 Marks]

Q.3) Write the difference between Turbo-prop and Turbo-fan. Also mention the By-pass ratio for

both. [4+2]

Q.4) What is the effect of inter-cooling and re-heating on the efficiency and net work output of the

gas turbine plant? [3+3]

Q.5) In a Jet propulsion unit, the total pressure and the total temperature at intake to the compressor

are 0.6bar and 0°C. The speed of propulsion unit is 190m/s. the total temperature and the total

pressure of the gases after the combustion entering the turbine are 750°C and 3.1 bar. The

isentropic efficiencies of the compressor and the turbine are 85% and 80% respectively. The static

back pressure of the propulsion nozzle is 0.52bar and the efficiency of the nozzle based on total

pressure drop available is 90%. Determine (a) power consumed by the compressor per kg of air

(b) the air-fuel ratio if the calorific value of fuel is 41840kJ/kg of fuel (c) the total pressure of gas

leaving the turbine (d) thrust per kg of air per second. [2+2+2+2]

Assume:- Cp of gases=1.1296kJ/kg-K, γ for the gases=1.33 and Cp of the air=1.005kJ/kg-K, γ for

air =1.4.

________X__________

Academic/26 Refer/WI/ACAD/18

SHRI RAMSWAROOP MEMORIAL COLLEGE OF ENGG. & MANAGEMENT

B.Tech. [SEM IV (ME)]

QUIZ TEST-1

(Session : 2010-11)

APPLIED THERMODYNAMICS

(EME-401)

Roll No.

(To be filled by the Student)

Note: All questions are compulsory.

Part – A

(Questions from Tutorial Sheet) [10 Marks]

Q.1) A simple closed gas turbine plant receives air at 1 bar and 15°C and compresses it to 5 bar

and then heats it to 800°C in the heating chamber. The hot air expands in a turbine back to

1bar. Calculate the power developed per kg of air supplied per second. Take Cp of air as

1kJ/kg K. (Q.No.2) [5]

Q.2) In a gas turbine plant the air is compressed in a single stage compressor from 1bar to 9bar

and from an initial temperature of 300K. The same air is then heated to a temperature of

800K and then expanded in the turbine. The air is then reheated to a temperature of 800K

and then expanded in the second turbine. Find the maximum power that can be obtained

from the installation, if the mass of air circulated per second is 2kg. Take Cp=1kJ/kg K. [5]

(Q.No.5)

Part – B [20 Marks]

Q.3) State the fundamental difference between the jet propulsion and rocket propulsion. [6]

Q.4) What is the effect of regeneration on the efficiencies and net work output of the gas turbine? [3+3]

Q.5) A jet propelled unit travels at 180m/s in air at 0.65bar and -6°C. Air first enters diffuser in which

it is brought to rest relative to the unit and it is then compressed in a compressor through a

pressure ratio of 5.8 and fed to a turbine at 925°C. The gas expands through the turbine and then

through the nozzle to the atmospheric pressure (0.65bar). The efficiency of diffuser and nozzle

are 0.9. The compressor and turbine efficiencies are 0.8. Pressure drop in the combustion

chamber is 0.14bar. Find the air-fuel ratio and the specific thrust of the unit. If the cross section

of the diffuser is 0.1m2,calculate the total thrust. Assume calorific value of the fuel is

44141kJ/kg. [3+3+2]

Assume:- Cp of the gases=1.1296kJ/kg-K, γ =1.33 and Cp of the air=1.005 and γ =1.4

__________X__________

Academic/26 Refer/WI/ACAD/18

SHRI RAMSWAROOP MEMORIAL COLLEGE OF ENGG. & MANAGEMENT

B.Tech. [SEM IV (ME)]

QUIZ TEST-1

(Session : 2010-11)

APPLIED THERMODYNAMICS

(EME-401)

Roll No.

(To be filled by the Student)

Note: All questions are compulsory.

Part – A

(Questions from Tutorial Sheet) [10 Marks]

Q1) In an oil gas turbine installation, it is taken at pressure of 1bar and 27°C and compress it to

a pressure of 4 bar. The oil with a calorific value of 42000kJ/kg is burnt in the combustion

chamber to raise the temperature of air to 550°C. If the air flows at the rate of 1.2kg/s. Find

the net power of the installation. Also find air fuel ratio. Take Cp=1.05kJ/kg K. ( Q. No.3) [5]

.

Q2) Air enters the compressor of the gas turbine plant operating on Brayton cycle at 1bar and

27°C. The pressure ratio in the cycle is 6. Calculate the maximum temperature in the cycle

and the cycle efficiency. Assume the turbine work as 2.5 times the compressor work. Take

γ=1.4. (Q. No.7) [5]

Part – B [20 Marks]

Q.3) Write the difference between Turbo-prop and Turbo-fan. Also mention the By-pass ratio for

both. [4+2]

Q.4) What is the effect of inter-cooling and re-heating on the efficiency and net work output of the

gas turbine plant? [3+3]

Q.5) In a Jet propulsion unit, the total pressure and the total temperature at intake to the compressor

are 0.6bar and 0°C. The speed of propulsion unit is 190m/s. the total temperature and the total

pressure of the gases after the combustion entering the turbine are 750°C and 3.1 bar. The

isentropic efficiencies of the compressor and the turbine are 85% and 80% respectively. The static

back pressure of the propulsion nozzle is 0.52bar and the efficiency of the nozzle based on total

pressure drop available is 90%. Determine (a) power consumed by the compressor per kg of air

(b) the air-fuel ratio if the calorific value of fuel is 41840kJ/kg of fuel (c) the total pressure of gas

leaving the turbine (d) thrust per kg of air per second.

Assume- Cp of gases=1.1296kJ/kg-K, γ for the gases=1.33 and Cp of the air=1.005kJ/kg-K, γ for

air =1.4 [2+2+2+2]

__________X__________

Academic/26 Refer/WI/ACAD/18

SHRI RAMSWAROOP MEMORIAL COLLEGE OF ENGG. & MANAGEMENT

B.Tech. [SEM IV (ME)]

QUIZ TEST-1

(Session : 2010-11)

APPLIED THERMODYNAMICS

(EME-401)

Roll No.

(To be filled by the Student)

Note: All questions are compulsory.

Part – A

(Questions from Tutorial Sheet) [10 Marks]

Q1) A gas turbine consists of two stage compressor with perfect intercooler and a single stage

turbine. If the plants works between the temperature limits of 300K and 1000K and 1bar

and 16bar. Find the net power of the plant per kg of air. Take specific heat at constant

pressure as 1kJ/kg K. (Q.No.4) [5]

Q2) A gas turbine plant with a pressure ratio of 1:5 takes in air at15°C. The maximum

temperature is 600°C and develops 2200kW. The turbine and compressor efficiencies are

equal to 0.85. Taking Cp=1kJ/kg K and Cv=0.714kJ/kg K. Determine (i) Actual overall

efficiency of the turbine; and (ii) mass of air circulated by the turbine. (Q.No.8) [5]

Part – B [20 Marks]

Q.3) State the fundamental difference between the jet propulsion and rocket propulsion. [6]

Q.4) What is the effect of regeneration on the efficiencies and net work output of the gas turbine? [3+3]

Q.5) A jet propelled unit travels at 180m/s in air at 0.65bar and -6°C. Air first enters diffuser in which

it is brought to rest relative to the unit and it is then compressed in a compressor through a

pressure ratio of 5.8 and fed to a turbine at 925°C. The gas expands through the turbine and then

through the nozzle to the atmospheric pressure (0.65bar). The efficiency of diffuser and nozzle

are 0.9. The compressor and turbine efficiencies are 0.8. Pressure drop in the combustion

chamber is 0.14bar. Find the air-fuel ratio and the specific thrust of the unit. If the cross section

of the diffuser is 0.1m2,calculate the total thrust. Assume calorific value of the fuel is

44141kJ/kg. [3+3+2]

Assume:- Cp of the gases=1.1296kJ/kg-K, γ =1.33 and Cp of the air=1.005 and γ =1.4

__________X__________

Academic/26 Refer/WI/ACAD/18

SHRI RAMSWAROOP MEMORIAL COLLEGE OF ENGG. & MANAGEMENT

B.Tech. [SEM IV (ME)]

QUIZ TEST-2

(Session: 2010-11)

APPLIED THERMODYNAMICS

(EME-401)

Roll No.

(To be filled by the Student)

Note: All questions are compulsory.

Part – A

(Questions from Tutorial Sheet) [10 Marks]

Q.1) The mean diameter of the blades of an impulse turbine with a single row of wheel is 105cm, and

the speed is 3000 rpm. The nozzle angle is 18°, the ratio of blade speed to steam speed is 0.42 and

the ratio of relative velocity at outlet from the blades to that at inlet is 0.84. The outlet angle of

blade is 3° less than that the inlet angle. The steam flow is 8kg/sec. Draw the velocity diagram for

the blades and find the following (a) resultant thrust on the blades (b) tangential thrust on the

blades (c) axial thrust on the blades (d) power developed in the blades, and (e) blading efficiency.

{Q. No.3} [1x5=5]

Q.2) Draw the velocity diagram for a stage in impulse turbine with two rings of moving blades for

following particulars, Nozzle angle=15°, moving blade tip discharge angle =30°, fixed blade

discharge angle=20° and the final discharge is axial. Friction loss per blade is 10% of relative

velocity. It occurs both on fixed and moving blades. Find the blade velocity for a nozzle steam exit

velocity of 500m/s and the diagram efficiency of the stage. {Q. No. 4} [2.5+2.5]

Part – B [20 Marks]

Q.1) What is “Bleeding” and what are the effects of it? And what is “Degree of Reaction” and why it

is zero for simple impulse turbine? [3+2+2]

Q.2) What is the effect of “Increasing the boiler pressure” on the efficiency of Rankine cycle? Also mention

the T-S diagram for it. [3+3]

Q.3) A single row impulse turbine develops 132.4kW at a blade speed of 175m/s using 2kg/s of

steam. Steam leaves the nozzle at a speed of 400m/s. Velocity coefficient of the blades is 0.9.

Steam leaves the turbine blade axially. Determine nozzle angle & blade angles at inlet and

outlet. Assuming no shock. [3+2+2]

__________X__________

Academic/26 Refer/WI/ACAD/18

SHRI RAMSWAROOP MEMORIAL COLLEGE OF ENGG. & MANAGEMENT

B.Tech. [SEM IV (ME)]

QUIZ TEST-2

(Session: 2010-11)

APPLIED THERMODYNAMICS

(EME-401)

Roll No.

(To be filled by the Student)

Note: All questions are compulsory.

Part – A

(Questions from Tutorial Sheet) [10 Marks]

Q.1) In a stage of an single stage impulse-reaction turbine operating with half degree reaction, the

fixed and moving blades are of identical section and outlet angle is 18°. The absolute velocity of

discharge from the moving blade is 40m/s in the direction 110° to the direction of motion of the

blades, and the change of velocity produced by the moving blades parallel to the direction. Draw

the velocity diagram and find (a) mean velocity of the blades (b) ratio of the velocity blade to the

velocity of efflux, and (c) work done per kg of steam. {Q. No.7} [2+2+1]

Q.2) In a simple impulse turbine, the nozzle angle is 16° and the blade outlet angle is 25°. Initial

velocity of steam as it issues from nozzle is 720 m/s and the blade velocity is 180m/s. The blade

velocity coefficient may be taken as 0.75. The steam flow rate is 1kg/s. Find (a) energy dissipated

in the blades due to friction (b) power developed (c) diagram efficiency, and also draw the

velocity diagram for it. {Q. No. 8} [2+2+1]

Part – B [20 Marks]

Q.1) How to locate “State point locus” for the steam turbine? What is “Reheat Factor” and

“Cogeneration”? [3+2+2]

Q.2) What is the effect of “Lowering the condenser pressure” on the efficiency of the Rankine cycle? Also

mention T-S diagram for it. [3+3]

Q.3) A single impulse turbine has a mean blade speed of 200m/s. The nozzle is inclined at 20° to

the plane of rotation of the blades. The steam velocity from nozzle is 600m/s. The turbine used

3500kg/hr of steam. The absolute velocity of steam at exit is along the axis of the turbine.

Determine (1) Inlet and outlet angle of the blades (2) The power output of the turbine, and (3)

The axial thrust (per kg of steam per second). Assume blades are equiangular. [2+2+3]

__________X__________

Academic/26 Refer/WI/ACAD/18

SHRI RAMSWAROOP MEMORIAL COLLEGE OF ENGG. & MANAGEMENT

B.Tech. [SEM IV (ME)]

QUIZ TEST-2

(Session: 2010-11)

APPLIED THERMODYNAMICS

(EME-401)

Roll No.

(To be filled by the Student)

Note: All questions are compulsory.

Part – A

(Questions from Tutorial Sheet) [10 Marks]

Q.1) In a stage of an impulse turbine provided with a single row wheel, the mean row diameter of the

blade ring is 80cm and the speed of the rotation is 3000rpm. The steam issues from the nozzle

with the velocity of 300m/s and the nozzle angle is 20°. The rotor blades are equiangular and due

to the friction in the blade channels the relative velocity of steam at outlet from the blade is 0.86

times the relative velocity of the steam entering in the blades. What is the power developed in the

blades and diagram efficiency of the turbine, when axial thrust on the blade is 140N? {Q.No.9}

[2.5+2.5]

Q.2) A velocity compounded impulse wheel has two rows of moving blades with a mean diameter of

70cm. the speed of the rotation is 3000rpm, the nozzle angle is 16° and the mean velocity at the

nozzle outlet is 610m/s. The mass of steam passing through the blades per second is 6.5kg.

Assuming that the energy loss in each row of blades(moving and fixed) is 24% of the kinetic

energy of the steam entering the blades and reffered to as the relative velocity, and that the outlet

angle of the blades are ,first row of moving blade 18°,intermediate guide blades 22° , second row

of moving blades 38°. Draw the diagram of relative velocities and derive the following (a) blade

inlet angles, (b) power developed in each row of the blades, and (c) efficiency of wheel as a whole.

{Q. No.10} [2+2+1]

Part – B [20 Marks]

Q.1) What is “Bleeding” and what are the effects of it? And what is “Degree of Reaction” and why it

is zero for simple impulse turbine? [3+2+2]

Q.2) What is the effect of “Increasing the boiler pressure” on the efficiency of Rankine cycle? Also mention

the T-S diagram for it. [3+3]

Q.3) A single row impulse turbine develops 132.4kW at a blade speed of 175m/s using 2kg/s of

steam. Steam leaves the nozzle at a speed of 400m/s. Velocity coefficient of the blades is 0.9.

Steam leaves the turbine blade axially. Determine nozzle angle & blade angles at inlet and

outlet. Assuming no shock. [3+2+2]

__________X__________

Academic/26 Refer/WI/ACAD/18

SHRI RAMSWAROOP MEMORIAL COLLEGE OF ENGG. & MANAGEMENT

B.Tech. [SEM IV (ME)]

QUIZ TEST-2

(Session: 2010-11)

APPLIED THERMODYNAMICS

(EME-401)

Roll No.

(To be filled by the Student)

Note: All questions are compulsory.

Part – A

(Questions from Tutorial Sheet) [10 Marks]

Q.1) In a single stage impulse turbine, the steam velocity at nozzle mouth is 300m/s, the nozzle angle

is 18° , and the mean blade velocity is 144m/s. Draw to a suitable scale the diagram of relative

velocities for the steam assuming that the outlet angle is 3° less that inlet angle of the blade and

the relative velocity of the steam at outlet from the blade is 0.84 of the relative velocity at

entrance. If the power to be developed is 1000kW. Calculate the mass of steam that pass through

the turbine per second. Also calculate the axial thrust. Neglect friction and leakage loss. {Q.No. 2}

[2.5+2.5]

Q.2) Explain the reheat and regeneration cycle. Also mention its T-S and P-V diagram for it.

{S.Q. No. 4} [3+3]

Part – B [20 Marks]

Q.1) How to locate “State point locus” for the steam turbine? What is “Reheat Factor” and

“Cogeneration”? [3+2+2]

Q.2) What is the effect of “Lowering the condenser pressure” on the efficiency of the Rankine cycle? Also

mention T-S diagram for it. [3+3]

Q.3) A single impulse turbine has a mean blade speed of 200m/s. The nozzle is inclined at 20° to

the plane of rotation of the blades. The steam velocity from nozzle is 600m/s. The turbine used

3500kg/hr of steam. The absolute velocity of steam at exit is along the axis of the turbine.

Determine (1) Inlet and outlet angle of the blades (2) The power output of the turbine, and (3)

The axial thrust (per kg of steam per second). Assume blades are equiangular. [2+2+3]

__________X__________

Academic/26 Refer/WI/ACAD/18

SHRI RAMSWAROOP MEMORIAL COLLEGE OF ENGG. & MANAGEMENT

B.Tech. [SEM IV (ME)]

QUIZ TEST-2

(Session: 2010-11)

APPLIED THERMODYNAMICS

(EME-401)

Roll No.

(To be filled by the Student)

Note: All questions are compulsory.

Part – A

(Questions from Tutorial Sheet) [10 Marks]

Q.1) Steam flows from the nozzles of a single row impulse turbine with a velocity of 450m/s at a

direction which is inclined at an angle of 16° to the peripheral velocity. Steam flows out of the

moving blades with an absolute velocity of 100m/s in the direction at 110° with the direction of

the blade motion. The blades are equiangular and steam flow rate is 6kg/s. Determine the power

developed and the power loss due to the friction.{Q. No.1) [2.5+2.5]

Q.2) The following particulars relate to a two row velocity compounding impulse turbine, which

forms the first stage of the combination turbine:- steam velocity at the nozzle outlet=650m/s,

mean blade velocity =125m/s, nozzle angle(outlet)=16°, outlet angle( first row of moving

blades)=18°, outlet angle (fixed guide blades )=22°, outlet angle ( second row of moving

blades)=36°, steam flows per second =2.5kg/s. the ratio of the relative velocities at outlet to the

inlet is 0.84 for all the blades. Determine for each row of moving blades the following :( a) the

velocity of whirl (b) the tangential thrust on the blades (c) the axial thrust on the blades, and (d)

the power developed . What is the efficiency of the wheel as a whole? {Q. No. 5} [1x5=5]

Part – B [20 Marks]

Q.1) What is “Bleeding” and what are the effects of it? And what is “Degree of Reaction” and why it

is zero for simple impulse turbine? [3+2+2]

Q.2) What is the effect of “Increasing the boiler pressure” on the efficiency of Rankine cycle? Also mention

the T-S diagram for it. [3+3]

Q.3) A single row impulse turbine develops 132.4kW at a blade speed of 175m/s using 2kg/s of

steam. Steam leaves the nozzle at a speed of 400m/s. Velocity coefficient of the blades is 0.9.

Steam leaves the turbine blade axially. Determine nozzle angle & blade angles at inlet and

outlet. Assuming no shock. [3+2+2]

__________X__________

Academic/26 Refer/WI/ACAD/18

SHRI RAMSWAROOP MEMORIAL COLLEGE OF ENGG. & MANAGEMENT

B.Tech. [SEM IV (ME)]

QUIZ TEST-3

(Session: 2010-11)

APPLIED THERMODYNAMICS

(EME-401)

Roll No.

(To be filled by the Student)

Note: All questions are compulsory.

Part – A

(Questions from Tutorial Sheet) [10 Marks]

Q.1) A nozzle expands steam from the 14bar and 300°C to 6bar. If the flow rate is 1kg/s, Find

the throat and exit area. What should be the coefficient of the velocity is 550m/s? [Q No 5]

[2.5+2.5]

Q.2) A covergent-divergent nozzle required to discharge 2kg of steam per second. The nozzle is

supplied with steam at 6.9bar and 180°C and discharge takes place against a back pressure

of 0.98bar. Expansion upto throat is isentropic and the frictional resistance between the

throat and exit equivalent to 62.76kj/kg of steam. Taking approach velocity of 75m/s and

throat pressure 3.9bar,Estimate (a)suitable areas for the throat and exit, and (b)overall

efficiency of the nozzle based on the enthalpy drop between the actual inlet pressure,and

tempreture and exit pressure. [S. Q. No 1] [2.5+2.5]

Part – B [20 Marks]

Q.1) What is the “choked flow” and what are its significances? [3+3]

Q.2) Explain the “modified rankine cycle” and also mention T-S diagram for it. [3+3]

Q.3) Dry and saturated steam enters a nozzle at a pressure of 11 bar and velocity of

80m/s. The discharge pressure is 5 bar and discharge velocity is 550m/s. The

quantity of steam flowing is 2kg/s and the heat loss from the nozzle is 8kJ/s.

Determine the heat drop and final dryness fraction of steam. [4+4]

__________X__________

Academic/26 Refer/WI/ACAD/18

SHRI RAMSWAROOP MEMORIAL COLLEGE OF ENGG. & MANAGEMENT

B.Tech. [SEM IV (ME)]

QUIZ TEST-3

(Session: 2010-11)

APPLIED THERMODYNAMICS

(EME-401)

Roll No.

(To be filled by the Student)

Note: All questions are compulsory.

Part – A

(Questions from Tutorial Sheet) [10 Marks]

Q.1) Steam is expanded in the set of the nozzles from 10bar and 200°C to 5bar. Is the nozzle

convergent or convergent-divergent? Neglecting the initial velocity, find the exit velocity

and minimum area of the nozzles to flow 3kg/s of steam under the given conditions

. Assume the expansion of the steam is isentropic. [Q.No. 4] [2.5+2.5]

Q.2) The steam nozzle is supplied steam at 15bar, 350°C and discharges steam at 1bar. If the

diverging portion of the nozzle is 80mm long and the throat diameter is 6mm. Determine

the cone angle of the divergent portion. Assume 12% of the total available enthalpy drop is

lost in friction in the divergent portion. Also determine the velocity and temperature of the

steam at throat. [Q. No. 10] [2.5+2.5]

Part – B [20 Marks]

Q.1) Describe the “over expansion” and “under expansion” in nozzle. [3+3]

Q.2) Explain the “modified rankine cycle” and also mention P-V diagram for it. [3+3]

Q.3) Air is expanded reversibly and adiabatically in a nozzle from 13 bar and 150°C to

a pressure of 6 bar. The inlet velocity of air is very small and the process occurs

under steady flow condition. Calculate the exit velocity of the nozzle. Is there any

concept of “variation in dryness fraction” of the air. [4+4]

__________X__________.

Academic/26 Refer/WI/ACAD/18

SHRI RAMSWAROOP MEMORIAL COLLEGE OF ENGG. & MANAGEMENT

B.Tech. [SEM IV (ME)]

QUIZ TEST-3

(Session: 2010-11)

APPLIED THERMODYNAMICS

(EME-401)

Roll No.

(To be filled by the Student)

Note: All questions are compulsory.

Part – A

(Questions from Tutorial Sheet) [10 Marks]

Q.1) Show that, when critical pressure ratio occurs, the velocity of a compressible fluid at the

exit of a convergent nozzle is given by; C2 = , where α1=sonic velocity

corresponding to the initial condition. Assume critical pressure ratio= , where γ is

the adiabatic index. Also state the factors on which nozzle efficiency depends.[Q No. 1]

[3+2]

Q.2) . A Delaval type impulse turbine is to develops 150kW with a probable consumption of

7.5kg of steam per kWh with initial pressure being 12bar and the exhaust 0.15bar. Taking

the diameter of the throat of each nozzle as 6mm. Find the number of the nozzles required.

Assuming the 10% of total drop is lost in diverging part of the nozzle; Find the diameter at

the exit of the nozzle and the quality of steam which is to be fully expanded as it leaves

the nozzle.[Q No 9] [2.5+2.5]

.

Part – B [20 Marks]

Q.1) What is the “choked flow” and what are its significances? [3+3]

Q.2) Explain the “modified rankine cycle” and also mention T-S diagram for it. [3+3]

Q.3) Dry and saturated steam enters a nozzle at a pressure of 11 bar and velocity of

80m/s. The discharge pressure is 5 bar and discharge velocity is 550m/s. The

quantity of steam flowing is 2kg/s and the heat loss from the nozzle is 8kJ/s.

Determine the heat drop and final dryness fraction of steam. [4+4]

__________X__________

Academic/26 Refer/WI/ACAD/18

SHRI RAMSWAROOP MEMORIAL COLLEGE OF ENGG. & MANAGEMENT

B.Tech. [SEM IV (ME)]

QUIZ TEST-2

(Session: 2010-11)

APPLIED THERMODYNAMICS

(EME-401)

Roll No.

(To be filled by the Student)

Note: All questions are compulsory.

Part – A

(Questions from Tutorial Sheet) [10 Marks]

Q.1) In a single stage impulse turbine, the steam velocity at nozzle mouth is 300m/s, the nozzle angle

is 18° , and the mean blade velocity is 144m/s. Draw to a suitable scale the diagram of relative

velocities for the steam assuming that the outlet angle is 3° less that inlet angle of the blade and

the relative velocity of the steam at outlet from the blade is 0.84 of the relative velocity at

entrance. If the power to be developed is 1000kW. Calculate the mass of steam that pass through

the turbine per second. Also calculate the axial thrust. Neglect friction and leakage loss. {Q.No. 2}

[2.5+2.5]

Q.2) Explain the reheat and regeneration cycle. Also mention its T-S and P-V diagram for it.

{S.Q. No. 4} [3+3]

Part – B [20 Marks]

Q.1) How to locate “State point locus” for the steam turbine? What is “Reheat Factor” and

“Cogeneration”? [3+2+2]

Q.2) What is the effect of “Lowering the condenser pressure” on the efficiency of the Rankine cycle? Also

mention T-S diagram for it. [3+3]

Q.3) A single impulse turbine has a mean blade speed of 200m/s. The nozzle is inclined at 20° to

the plane of rotation of the blades. The steam velocity from nozzle is 600m/s. The turbine used

3500kg/hr of steam. The absolute velocity of steam at exit is along the axis of the turbine.

Determine (1) Inlet and outlet angle of the blades (2) The power output of the turbine, and (3)

The axial thrust (per kg of steam per second). Assume blades are equiangular. [2+2+3]

__________X__________

Academic/26 Refer/WI/ACAD/18

SHRI RAMSWAROOP MEMORIAL COLLEGE OF ENGG. & MANAGEMENT

B.Tech. [SEM IV (ME)]

QUIZ TEST-2

(Session: 2010-11)

APPLIED THERMODYNAMICS

(EME-401)

Roll No.

(To be filled by the Student)

Note: All questions are compulsory.

Part – A

(Questions from Tutorial Sheet) [10 Marks]

Q.1) In a single stage impulse turbine, the steam velocity at nozzle mouth is 300m/s, the nozzle angle

is 18° , and the mean blade velocity is 144m/s. Draw to a suitable scale the diagram of relative

velocities for the steam assuming that the outlet angle is 3° less that inlet angle of the blade and

the relative velocity of the steam at outlet from the blade is 0.84 of the relative velocity at

entrance. If the power to be developed is 1000kW. Calculate the mass of steam that pass through

the turbine per second. Also calculate the axial thrust. Neglect friction and leakage loss. {Q.No. 2}

[2.5+2.5]

Q.2) Explain the reheat and regeneration cycle. Also mention its T-S and P-V diagram for it.

{S.Q. No. 4} [3+3]

Part – B [20 Marks]

Q.1) How to locate “State point locus” for the steam turbine? What is “Reheat Factor” and

“Cogeneration”? [3+2+2]

Q.2) What is the effect of “Lowering the condenser pressure” on the efficiency of the Rankine cycle? Also

mention T-S diagram for it. [3+3]

Q.3) A single impulse turbine has a mean blade speed of 200m/s. The nozzle is inclined at 20° to

the plane of rotation of the blades. The steam velocity from nozzle is 600m/s. The turbine used

3500kg/hr of steam. The absolute velocity of steam at exit is along the axis of the turbine.

Determine (1) Inlet and outlet angle of the blades (2) The power output of the turbine, and (3)

The axial thrust (per kg of steam per second). Assume blades are equiangular. [2+2+3]

__________X__________

Academic/26 Refer/WI/ACAD/18

SHRI RAMSWAROOP MEMORIAL COLLEGE OF ENGG. & MANAGEMENT

B.Tech. [SEM IV (ME)]

QUIZ TEST-2

(Session: 2010-11)

APPLIED THERMODYNAMICS

(EME-401)

Roll No.

(To be filled by the Student)

Note: All questions are compulsory.

Part – A

(Questions from Tutorial Sheet) [10 Marks]

Q.1) In a single stage impulse turbine, the steam velocity at nozzle mouth is 300m/s, the nozzle angle

is 18° , and the mean blade velocity is 144m/s. Draw to a suitable scale the diagram of relative

velocities for the steam assuming that the outlet angle is 3° less that inlet angle of the blade and

the relative velocity of the steam at outlet from the blade is 0.84 of the relative velocity at

entrance. If the power to be developed is 1000kW. Calculate the mass of steam that pass through

the turbine per second. Also calculate the axial thrust. Neglect friction and leakage loss. {Q.No. 2}

[2.5+2.5]

Q.2) Explain the reheat and regeneration cycle. Also mention its T-S and P-V diagram for it.

{S.Q. No. 4} [3+3]

Part – B [20 Marks]

Q.1) How to locate “State point locus” for the steam turbine? What is “Reheat Factor” and

“Cogeneration”? [3+2+2]

Q.2) What is the effect of “Lowering the condenser pressure” on the efficiency of the Rankine cycle? Also

mention T-S diagram for it. [3+3]

Q.3) A single impulse turbine has a mean blade speed of 200m/s. The nozzle is inclined at 20° to

the plane of rotation of the blades. The steam velocity from nozzle is 600m/s. The turbine used

3500kg/hr of steam. The absolute velocity of steam at exit is along the axis of the turbine.

Determine (1) Inlet and outlet angle of the blades (2) The power output of the turbine, and (3)

The axial thrust (per kg of steam per second). Assume blades are equiangular. [2+2+3]

__________X__________

Academic/26 Refer/WI/ACAD/18

SHRI RAMSWAROOP MEMORIAL COLLEGE OF ENGG. & MANAGEMENT

B.Tech. [SEM IV (ME)]

QUIZ TEST-2

(Session: 2010-11)

APPLIED THERMODYNAMICS

(EME-401)

Roll No.

(To be filled by the Student)

Note: All questions are compulsory.

Part – A

(Questions from Tutorial Sheet) [10 Marks]

Q.1) In a single stage impulse turbine, the steam velocity at nozzle mouth is 300m/s, the nozzle angle

is 18° , and the mean blade velocity is 144m/s. Draw to a suitable scale the diagram of relative

velocities for the steam assuming that the outlet angle is 3° less that inlet angle of the blade and

the relative velocity of the steam at outlet from the blade is 0.84 of the relative velocity at

entrance. If the power to be developed is 1000kW. Calculate the mass of steam that pass through

the turbine per second. Also calculate the axial thrust. Neglect friction and leakage loss. {Q.No. 2}

[2.5+2.5]

Q.2) Explain the reheat and regeneration cycle. Also mention its T-S and P-V diagram for it.

{S.Q. No. 4} [3+3]

Part – B [20 Marks]

Q.1) How to locate “State point locus” for the steam turbine? What is “Reheat Factor” and

“Cogeneration”? [3+2+2]

Q.2) What is the effect of “Lowering the condenser pressure” on the efficiency of the Rankine cycle? Also

mention T-S diagram for it. [3+3]

Q.3) A single impulse turbine has a mean blade speed of 200m/s. The nozzle is inclined at 20° to

the plane of rotation of the blades. The steam velocity from nozzle is 600m/s. The turbine used

3500kg/hr of steam. The absolute velocity of steam at exit is along the axis of the turbine.

Determine (1) Inlet and outlet angle of the blades (2) The power output of the turbine, and (3)

The axial thrust (per kg of steam per second). Assume blades are equiangular. [2+2+3]

__________X__________