B.TECH - Semester 8 propulsion engineering Question Paper 2019 (nov)
Practice authentic previous year university questions for better exam preparation.
Sample Questions
- Explain the working of a Pulsejet engine with a neat figure. Plot the thermodynamic processes in a $\mathrm{p}-\mathrm{v}$ diagram.
- Derive an expression for the propulsive efficiency of a jet engine.
- Explain the Starting problem in Supersonic Intakes with the help of neat figures.
- Derive an expression for the efficiency of compressor in a turbojet engine.
- Explain the working of a nuclear rocket with a neat figure.
- What are the characteristics of propellants used in liquid propellant rocket engines?
- What is meant by linear burning rate? Explain.
- Explain the working principle of hybrid rockets.
- Briefly explain the test facilities and safeguards during rocket testing.
- Explain the precaution adopted in the handling of propellants. ( $\mathbf{1 0} \boldsymbol{\times} \mathbf{2} \boldsymbol{=} \mathbf{2 0}$ Marks) Answer one full questions from each Module.
- (a) Derive the Thrust Equation for Jet Propulsion using the control volume concept.
- (b) A turbojet engine propels an aircraft at a speed of $300 \mathrm{~m} / \mathrm{s}$ at an altitude of $16,000 \mathrm{~m}(\mathrm{P}=0.1033 \mathrm{bar} . \mathrm{T}=216.7 \mathrm{~K})$. The turbojet has two air intakes of 500 mm diameter each. Th...
- (a) Differentiate between thrust power and propulsive power.
- (b) Explain the working of Turbofan engine with a neat figure. Plot the thermodynamic processes in $\mathrm{p}-\mathrm{v}$ and T-s diagrams.
- (a) Explain the different Thrust Augmentation methods employed in Jet engines.
- (b) Determine the Thrust Specific Fuel Consumption of a Turbojet engine that is being considered for flight at a Mach number of 1.5 and 15250 m altitude where the ambient pressure and temperature are 11.6 kPa and 205 K , respectively. The stagnation ...
- (a) Explain the methods adopted for turbine blade cooling in jet engines.
- (b) A military Turbojet engine with a Convergent Nozzle has the following specifications : Overall pressure ratio: 11.5 Air mass flow rate: $75 \mathrm{~kg} / \mathrm{s}$ Turbine inlet temperature: 1150 K Calorific value of fuel: $45 \mathrm{MJ} / \...
- (a) In rocket engines, prove that the propulsive efficiency is maximum when the flight velocity is equal to its exit jet velocity.
- (b) Explain the working of (i) Gas pressurized and (ii) Turbo pump propellant feed systems in a liquid propellant rocket engine with neat figures.
- (a) Explain the different grain configurations employed in solid propellant rocket motor with neat figures.
- (b) The linear burning rate of a solid propellant restricted burning grain is $20 \mathrm{~mm} / \mathrm{s}$ when the chamber pressure is 80 bar and $40 \mathrm{~mm} / \mathrm{s}$ when the chamber pressure is 200 bar. Determine (i) the chamber pressu...
- (a) Derive an expression for Burn out velocity in terms of Specific Impulse and Mass ratio of rockets.
- (b) What is meant by Combustion instability? Explain the Rayleigh criterion for the analysis of combustion instability.
- (a) Derive an expression for the altitude gained by a rocket at the end of powered flight.
- (b) Explain the different methods employed for the cooling of thrust chambers in Rocket engines.