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Gas Turbine & Jet Propulsion (October 2009)

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Total No. of Questions : 12] [Total No. of Pages : 4 [3664] - 125 P970 B.E. (Mechanical) GAS TURBINE & JET PROPULSION (2003 Course) (402044) Time : 3 Hours] [Max. Marks : 100 Instructions to the candidates: 1) Answer three questions from Section I and three questions from Section II. 2) Answers to the two sections should be written in separate books. 3) Neat diagrams must be drawn wherever necessary. 4) Figures to the right indicate full marks. 5) Use of logarithmic tables, slide rule, Mollier charts, electronic pocket calculator and steam tables is allowed. 6) Assume suitable data, if necessary. SECTION - I UNIT - I Q1) a) What do you understand by the term stagnation state? Give its practical importance. Hence define stagnation enthalpy, pressure & temp. Prove that stagnation temp., T 0 = T + b) C2 . 2.C p [8] Air enters diffuser at velocity of 150 m/sec at static condition of 1 bar & 15oC. The diffuser efficiency is 95%. Determine the exit stagnation conditions. Assume Cp = 1.005 kJ/kg K. A = 1.4 & R = 287 Nm/kg K. [8] OR Q2) a) b) c) Explain the following terms related to nozzles [4] i) Velocity coefficient. ii) Dischange coefficient. What do the states on fanno line & Rayleigh line represent? What do the intersection points of these two curves represent? [4] A convergent nozzle is to discharge 1 kg/s of gas. The gas enters a nozzle at stagnation conditions of 5 bar & 727oC & it leaves at speed of 500 m/sec. Assuming the flow to be isentropic, determine the pressure & nozzle area at the exit. [8] UNIT - II Q3) a) Give comparison between centrifugal compressor & axial flow compressor. [5] P.T.O.

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Additional Info : 2003 Course
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