Jawaharlal Nehru Technological University Hyderabad
Jawaharlal Nehru Technological University Hyderabad B.Tech III AEROSPACE PROPULSION- I Previous Question Paper (November/December - 2018 - R13)
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 are the applications of turbine engine?
Answer
Turbine engines are primarily used for aircraft propulsion (commercial, military, and general aviation), marine propulsion for high-speed naval vessels, and industrial power generation or gas compression stations.
Write difference between installed and uninstalled thrust.
Answer
Uninstalled thrust is the ideal thrust produced by an engine in a test cell without considering external aerodynamic losses. Installed thrust is the actual net thrust produced when the engine is mounted on the aircraft, accounting for installation losses such as inlet pressure recovery, nozzle losses, and bleed air extraction.
What is optimum compressor pressure ratio?
Answer
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Write the expression for thermal efficiency of turbofan engine.
Answer
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Define Thrust Specific fuel consumption.
Answer
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Explain about optimum bypass ratio?
Answer
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What is shaft speed?
Answer
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Why do you think cooling of turbine blades is necessary?
Answer
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Define throttle ratio?
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What is theta break?
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Part B
Derive thrust equation for a jet engine.
Answer
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What is operating principle of a turbine engine? Explain with neat diagram.
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Write about an turbojet engine with reheat in detail with cycle analysis.
Answer
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Derive the relationship between compressor efficiencies?
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What are the thermodynamic processes in a turbofan engine? Explain in T-S plot.
Answer
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What do you mean by aerodynamic choking of flow?
Answer
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Compare the types of burners of a gas turbine engine.
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What are the different types of supersonic inlets? Write the applications of each.
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Air flows through an axial compressor stage. For air, use γ = 1.4 and R = 0.286 kJ/(kg.K). Determine the change in tangential velocity and the total pressure ratio of the stage from a stage efficiency of 0.88.
Answer
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Write about turbine cooling and explain any two methods in detail.
Answer
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Explain the design process of a turbine engine in detail with all the necessary steps involved.
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Write about surge and stall problem in a compressor and turbine.
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Write the relation between compressor pressure ratio and mass flow rate of efficiency and engine speed.
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Derive a set of equations to determine the pumping characteristics of a simple gas generator.
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Derive the performance equations for a single-spool turbojet engine.
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