MODEL QUESTION PAPER B.E. Aeronautical Engineering Semester V AE334 - PROPULSION I Time: 3 Hours Answer All Questions PART – A (10 x 2 = 20 Marks) 1. Bring out any two essential difference between aircraft piston engines and jet engines from operating principle point of view. 2. 3. Mention any two advantages and two limitations of a turbojet powered airplane? What is the effect of increase in air temperature during compression process on the overall jet engine performance? 4. 5. Sketch typical flow pattern over a supersonic inlet of a jet engine? Distinguish between primary zone and secondary zone of a gas turbine combustion chamber? 6. 7. 8. 9. What is the function of a swirler in a can type gas turbine combustion chamber? Sketch a typical flame stability curve of a gas turbine combustion chamber? What is the function of impeller in a centrifugal air compressor? Suggest any two methods to improve compression efficiency of an axial flow compressor. 10 Explain the phenomenon ‘surging’ of compressor. PART – B (5 x 16 = 80 Marks) 11.i) Sketch thrust vs air speed, TSFC vs air speed curves for turboprop, turbofan and turbojet engines. Also compare propulsive efficiency vs flight speed curves of the above three engines? (8) Sketch the performance characteristic curves of centrifugal compressor and axial flow compressor. What conclusions can be made from these curves? (8) Maximum Marks : 100
12.a)i) Classify gas turbine combustion chambers. Bring out the advantages and limitations of any three types of combustion chambers from structural design and combustion performance point of view? (8)
ii) What is the need for flame stabilization in a gas turbine combustion chamber? How is flame stability achieved in a jet turbine combustion chamber? (8) 12.b)i) Sketch the typical flow pattern in the flame tube of a typical gas turbine combustion chamber and mark all the regions in the flow pattern. Explain the salient features of these regions. (8) ii) List the...