Exam Details
| Subject | Propulsion- II | |
| Paper | ||
| Exam / Course | B.Tech in Aerospace Engineering (BTAE) | |
| Department | School of Engineering & Technology (SOET) | |
| Organization | indira gandhi national open university | |
| Position | ||
| Exam Date | December, 2016 | |
| City, State | new delhi, |
Question Paper
No. of Printed Pages: 4 IBAS-016I
B.Tech. AEROSPACE ENGINEERING
(BTAE)
Term-End Examination
December, 2016
00"24..3
BAS-O16 PROPULSION -II
Time hours Maximum Marks: 70
Note Attempt any seven questions. All questions carry equal marks. Use of scientific calculator is permitted.
1. With the help of a neat diagram, explain the working principle of Ram Jet Engines.
Draw neat diagram of the inlet and exit velocity triangle for anyone type of blades of centrifugal compressor and explain them. 5+5
2. Briefly discuss the application of gas turbines.
Explain any two of the following:
Blade Mach number
Cascade action
After burner 5+5
3. Differentiate between thrust augmentation and thrust reversal.
With the help of a neat sketch explain a by-pass engine. 5+5
4. Differentiate between centrifugal and axial flow compressors.
Draw a neat sketch of a jet engine lubrication system and explain it. 5+5
5. Explain the phenomenon of compressor surge.
Discuss the phenomenon of flow through a convergent-divergent nozzle. 5+5
6. What is the function of a compressor What are the different types of compressors?
Define the volumetric efficiency of a compressor. Enlist the factors on which it depends. 5+5
7. A turbojet engine inducts 51 kg of air per second and propels an aircraft with a uniform flight speed of 912 km1hr. The isentropic enthalpy change for the nozzle is 200 kJ/kg and its velocity coefficient is 0.96. The fuel-air ratio is 0.0119, the combustion coefficiency is 96% and the lower heating value of the fuel is 10500 kcal/kg. Assume CV 42 MJ/kg.
Calculate
the thermal efficiency of the engine,
the fuel flow rate in kg/hr and the Thrust Specific Fuel Consumption
the propulsive power in kW,
the thrust power, and
the propulsive efficiency. 10
8. A turbojet has a speed of 750 km/hr while flying at an altitude of 10000 m. The propulsive efficiency of the jet is 50% and the overall efficiency of the turbine plant is 16%. The density of air at 10000 altitude is 0'173 kglm3. The drag on the plane is 6250 N. The calorific value of the fuel is 48000 kJlkg. Calculate the following:
Absolute velocity of the jet
Volume of air compressed per minute
Diameter of the jet
Power output of the unit in kW
Air-fuel ratio
9. The mean diameter of the blades of an impulse turbine with a single row wheel is 105 em and the sPeed is 3000 rpm. The nozzle angle is 180 with respect to axial direction, the ratio of blade speed .to gas speed is 0·42 and the ratio of the relative velocity at outlet from the blades to that at inlet is 0·84. The outlet angle of the blade is to be made 30 less than the inlet angle. The mass flow rate is 8 kg/sec. 10
Calculate the following:
Tangential thrust on the blades
Axial thrust on the blades
Power produced on the blades
Blade efficiency
10. Write short notes on any five of the following: 5x2=10
Blade Cooling
Air Cooling System
Flame Stability
Diffuser in Subsonic Flow
Angularity Coefficient
Mach Number
Zero Percent Reaction Stage
Choking in Centrifugal Compressor
B.Tech. AEROSPACE ENGINEERING
(BTAE)
Term-End Examination
December, 2016
00"24..3
BAS-O16 PROPULSION -II
Time hours Maximum Marks: 70
Note Attempt any seven questions. All questions carry equal marks. Use of scientific calculator is permitted.
1. With the help of a neat diagram, explain the working principle of Ram Jet Engines.
Draw neat diagram of the inlet and exit velocity triangle for anyone type of blades of centrifugal compressor and explain them. 5+5
2. Briefly discuss the application of gas turbines.
Explain any two of the following:
Blade Mach number
Cascade action
After burner 5+5
3. Differentiate between thrust augmentation and thrust reversal.
With the help of a neat sketch explain a by-pass engine. 5+5
4. Differentiate between centrifugal and axial flow compressors.
Draw a neat sketch of a jet engine lubrication system and explain it. 5+5
5. Explain the phenomenon of compressor surge.
Discuss the phenomenon of flow through a convergent-divergent nozzle. 5+5
6. What is the function of a compressor What are the different types of compressors?
Define the volumetric efficiency of a compressor. Enlist the factors on which it depends. 5+5
7. A turbojet engine inducts 51 kg of air per second and propels an aircraft with a uniform flight speed of 912 km1hr. The isentropic enthalpy change for the nozzle is 200 kJ/kg and its velocity coefficient is 0.96. The fuel-air ratio is 0.0119, the combustion coefficiency is 96% and the lower heating value of the fuel is 10500 kcal/kg. Assume CV 42 MJ/kg.
Calculate
the thermal efficiency of the engine,
the fuel flow rate in kg/hr and the Thrust Specific Fuel Consumption
the propulsive power in kW,
the thrust power, and
the propulsive efficiency. 10
8. A turbojet has a speed of 750 km/hr while flying at an altitude of 10000 m. The propulsive efficiency of the jet is 50% and the overall efficiency of the turbine plant is 16%. The density of air at 10000 altitude is 0'173 kglm3. The drag on the plane is 6250 N. The calorific value of the fuel is 48000 kJlkg. Calculate the following:
Absolute velocity of the jet
Volume of air compressed per minute
Diameter of the jet
Power output of the unit in kW
Air-fuel ratio
9. The mean diameter of the blades of an impulse turbine with a single row wheel is 105 em and the sPeed is 3000 rpm. The nozzle angle is 180 with respect to axial direction, the ratio of blade speed .to gas speed is 0·42 and the ratio of the relative velocity at outlet from the blades to that at inlet is 0·84. The outlet angle of the blade is to be made 30 less than the inlet angle. The mass flow rate is 8 kg/sec. 10
Calculate the following:
Tangential thrust on the blades
Axial thrust on the blades
Power produced on the blades
Blade efficiency
10. Write short notes on any five of the following: 5x2=10
Blade Cooling
Air Cooling System
Flame Stability
Diffuser in Subsonic Flow
Angularity Coefficient
Mach Number
Zero Percent Reaction Stage
Choking in Centrifugal Compressor
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