ME 6604 Gas Dynamics and Jet propulsion University question bank

ANNA UNIVERSITY-CHENNAI

REGULATION 2013

DEPARTMENT OF MECHANICAL ENGINEERING

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                   ME6604-GAS DYNAMICS AND JET PROPULSION

Unit IV- Jet propulsion

Part A (2 Marks)

1. What is thrust (or) drag?

2. What is Thrust Specific Fuel Consumption (TSFC)?

3. Define Specific impulse

4. What are the various types of air breathing engine?

5. What is scram jet?

6. How is turbofan engine different from turbo prop engine?

7. What is thrust augmentation?

8. Give the difference between Ramjet and Turbojet engine

9. What is the difference between turboprop and turbojet engine

10. What type of compressor used in turbojet? Why?

Part B (16 Marks)

1.Differentiate turbojet and turboprop propulsion engines with suitable diagrams

(AU: May2012)

2.Write the equations to calculate propulsion efficiency and thermal efficiency of an aircraft.

(AU: May 2012)

3.A turbojet engine operating at a Mach number of 0.8 and the altitude is 10Km has the following data. Calorific value of the fuel is 42,899 kJ/Kg. thrust force is 50 kN, mass flow rate of air is 45 kg/s, mass flow rate of fuel is 2.65 kg/s. determine the specific thrust, thrust specific fuel consumption, jet velocity, thermal efficiency, propulsion efficiency and overall efficiency. Assuming the exit pressure is equal to ambient pressure.

(AU: May 2012)

4.Explain the principle of operation of a turbojet engine and state its advantages and disadvantage

(AU: May 2011)

5.A turbojet aircraft flies at 875 Kmph at an attitude of 10,000 m above mean sea level. Calculate i) air flow rate through the engine, ii) thrust, iii) specific thrust, iv) specific impulse v) thrust power and TSFC from the following data: Diameter of the air at inlet section = 0.75m Diameter of jet pipe at exit = 0.5m Velocity of the gases at the exit of the jet pipe = 500m/s Pressure at the exit of the jet pipe = 0.30 bar Air to fuel ratio = 40

(AU: May 2011, May 2007)

6.Explain with a neat sketch the principle of operation of a ramjet engine and state its advantages and disadvantages. (AU: May 2010, May 2009).

7.A turbojet propels an aircraft at a speed of 900 km/hr, while taking 3000 kg of air per minute. The isentropic enthalpy drop in the nozzle is 200 kJ/kg and the nozzle efficiency is 90%. The air-fuel ratio is 85 and the combustion efficiency is 95%. The calorific value of the fuel is 42,000 kJ/Kg. Calculate: i) The propulsion power, ii) Thrust power, iii) Thermal efficiency and iv) Propulsion efficiency.(AU: Dec 2009)

8.Describe the working of supersonic ramjet engine with a neat sketch. List out its advantages and disadvantages. (AU: May 2009)

9.The diameter of the propeller of an aircraft is 2.5m; it flies at a speed of 500 km/hr at an altitude of 8000 m. For a flight to jet speed ratio of 0.75, determine: the flow rate of air through the propeller, thrust produced, specific thrust, specific impulse and thrust power. (AU: Dec 2008)

10.Explain with a neat sketch the principle of operation of a turbojet engine and state its advantages and disadvantages. 
(AU: May 2008)

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http://annaunivstudymaterials.blogspot.in/2015/11/university-questions-gas-dynamics-and.html