JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD
JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD B.Tech III Year AIRBREATHING PROPULSION Previous Question Paper (November/December - 2018 - R16)
Note: This question paper contains two parts A and B. Part A is compulsory which carries 25 marks. Answer all questions in Part A. Part B consists of 5 Units. Answer any one full question from each unit. Each question carries 10 marks and may have a, b, c as sub questions.
Part A
What do you mean by degree of reaction?
Answer
The degree of reaction is defined as the ratio of the static enthalpy drop in the rotor to the total static enthalpy drop across the entire turbine stage.
What is limitation of Impulse turbine?
Answer
The primary limitation of an impulse turbine is the high fluid velocity required at the rotor inlet, which leads to significant friction losses and potential blade erosion. Additionally, it generally exhibits lower stage efficiency compared to reaction turbines at high pressure ratios and is prone to higher leakage losses due to the large pressure difference across the rotor.
What is the application of thrust augmentation with after burning?
Answer
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What are the different methods of Thrust vectoring?
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What is the condition for the maximum thrust in a chemical rocket?
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What are the factors influencing the burn rate of a solid propellant?
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Write the difference between rocket propulsion and air breathing propulsion.
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What is the disadvantage of a straight nozzle in a liquid rocket engine?
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Explain in brief about Ion Propulsion techniques.
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Explain preliminary concepts involved in nozzle less propulsion.
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Part B
Write a short note on typical turbine blade profiles employed in the design of an axial flow turbine.
Answer
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What are the different methods of turbine blade cooling? Explain with the help of neat diagrams.
Answer
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A gas turbine power unit consumes 30 kg of air per second. The air enters the compressor at a pressure of 1 Pa and temperature 1500C and leaves at a pressure of 35 Pa. The combustion process occurs at a constant pressure and produces a temperature rise of 4800C. The air then expands through the turbine to a pressure of 1.3 Pa. Calculate the net power output from the unit assuming that the flow through the compressor and turbine is reversible and adiabatic.
Answer
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Explain in detail about the working principle and construction of Ramjet engine.
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A rocket engine is tested on a test bed under the ideal condition of fully expanded jet. The exhaust velocity is 2 km/s through a nozzle of area 2.5m2. The mass flow rate is 200 kg/s. Calculate the specific impulse of the propellant and the thrust developed (assume g = 9.81 m/s2).
Answer
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Explain about supersonic combustion in a SCRAMJET engine.
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Discuss the mechanism of burning of various types of liquid propellants.
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What are the relative advantages and disadvantages of liquid rockets over solid rockets? Explain.
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Derive a general expression for the thrust produced by a chemical rocket and discuss the importance of the molecular weight of the propellants.
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What are the rocket performance parameters? Define them. Write the expression for each parameter? Also write the physical significance of each performance parameter.
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Classify the types of rocket nozzles. Write the advantage and limitation of rocket nozzle types.
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Draw a schematic diagram of a photon propulsion unit. Explain its working principle.
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Explain about the different types of advanced nuclear propulsion system.
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What do you mean by sustainable chain reaction? Justify your answer with suitable examples.
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Explain in brief about the working principle of electric rocket propulsion.
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