JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD
JAWAHARLAL NEHRU TECHNOLOGICAL UNIVERSITY HYDERABAD B.Tech III Year AEROSPACE PROPULSION I Previous Question Paper (May - 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.
Part A
Write the operating principle of Aircraft gas turbine.
Answer
The aircraft gas turbine operates on the Brayton cycle, which involves the continuous processes of compression of incoming air, constant-pressure combustion of fuel-air mixture, and expansion of hot gases through a turbine to produce work and thrust.
Draw the layout of jet engine with station number of components.
Answer
The standard station numbering for a jet engine is: Station 0 (Ambient), 1 (Inlet entry), 2 (Compressor entry), 3 (Compressor exit/Combustor entry), 4 (Combustor exit/Turbine entry), 5 (Turbine exit), 6 (Afterburner/Mixer), 7 (Nozzle entry), and 8/9 (Nozzle exit).
Explain the need for a variable geometry air intake.
Answer
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What are the advantages of turbojet with reheat?
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When and why choking occurs in nozzle?
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Write the Euler’s equation for turbine and pump separately and explain the terms.
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What is multi staging and multi spooling?
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What is difference between turbine and compressor?
Answer
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What is the purpose of using dimensionless and corrected parameters in component performance maps?
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Explain the relevance of operating line on a compressor map.
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Part B
Derive the expression for installed and uninstalled thrust for the aircraft.
Answer
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Explain the turbojet engine operation, advantages and disadvantages with a neat sketch.
Answer
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In a gas turbine plant, working on the brayton cycle with a regenerator of 75% effectiveness the air at the inlet to the compressor is at 0.1 MPa 300C, the pressure ratio is 6, and the maximum cycle temperature is 1500 0C. If the turbine and compressor have each an efficiency of 80%. Find the percentage increase in the cycle efficiency due to regeneration.
Answer
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Explain the steps involved in parametric analysis of turbojet.
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Explain different types of inlets with neat sketches.
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Explain the various types of thrust revering mechanisms employed in modern aircraft.
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Explain the types of cooling methods in combustion chamber.
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Write about functioning of after burner and flame holders.
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Write the limits on achievable performance of compressors and turbines.
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What are the flow losses and explain the causes of it relating to efficiency.
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Distinguish between stall, surge and rotating stall in an axial flow compressor.
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Draw the velocity triangles at the inlet and outlet of the rotor and derive an expression for the work done per stage.
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Explain the parameters that define the engine control system limits for a gas turbine engine. State the steps involved in matching the component performance of a single shaft turbo-jet Engine.
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Explain the relevance of turbine inlet temperature for the gas turbine operation. Discuss various turbine blade cooling methods used with neat sketches.
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