JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD
JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD B.Tech III Year AIRBREATHING PROPULSION Previous Question Paper (May/June - 2019 - R16)
Note: Part A is compulsory (25 marks). Part B consists of 5 Units, answer any one full question from each unit (10 marks each).
Part A
Write a short notes on elementary theory.
Answer
Elementary theory in airbreathing propulsion, specifically regarding propellers or rotors, treats the blade as a series of independent airfoil sections. It assumes that the flow at each radial section is two-dimensional and that there is no aerodynamic interaction between adjacent blade elements, allowing for the calculation of thrust and torque by integrating the lift and drag forces acting on these individual sections.
What is a vortex theory?
Answer
Vortex theory is a more advanced method used to analyze the aerodynamic performance of propellers or rotors by accounting for the induced flow field. It models the blades as lifting lines with trailing vortex systems, which induce a downwash velocity that modifies the effective angle of attack at each section. This theory provides a more accurate prediction of thrust and power requirements by considering the interaction between the blades and the wake.
Describe about RAMJET.
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Distinguish between a RAMJET and SCRAMJET.
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Discuss combustion instability applied to Liquid Propellant Rocket (LPR) engines.
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What are the types of propellant tanks used in LPR engines?
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Write some applications of rocket propulsion.
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What is total impulse?
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Write the limitation of solar soil.
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Write a short note on electric rocket propulsion.
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Part B
Describe the overall performance of gas turbine and what the limiting factors in gas turbine design.
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Distinguish in detail the methods of blade cooling.
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What are the operating principles of Ramjet propulsion in detail with neat sketch?
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Explain about TVC mechanism with a single nozzle in detail.
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A mixture of perfect gas consists of 5 kg of carbon monoxide and 2.5 kg of nitrogen at a pressure of 0.2 MPa and a temperature of 298.15K. (a) Find the effective molar mass of a mixture, (b) Specific heat ratio, (c) Partial pressures (d) Density.
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Explain the working of hybrid rocket engine and its limitations.
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What are the relative advantages of liquid rockets over solid rockets?
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Classify rocket nozzles. Write merits and demerits of each.
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Derive a rocket equation, specific impulse of a rocket and their classifications.
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Explain the working of a nuclear rocket engine. What are the features of it?
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Describe the various advanced propulsion techniques used in rocket, which may required to improve the rocket propulsive methods.
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