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Gas Turbine & Jet Propulsion (April 2010)

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Total No. of Questions : 12] P1391 [Total No. of Pages :4 [3764] - 134 B.E. (Mechanical) GAS TURBINE AND JET PROPULSION (2003 Course) Time : 3 Hours] [Max. Marks:100 Instructions to the candidates: 1) Answer any three questions from each section. 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) A convergent-divergent nozzle has a throat area 500 mm2 and an exit area of 1000 mm2. Air enters the nozzle with a stagnation temperature of 360 K and stagnation pressure of 1 MPa. Determine the maximum flow rate, a static pressure, static temperature, Mach number and velocity at exit if (i) the divergent section acts as nozzle (ii) the divergent section acts as a diffuser. [10] b) Show that for an isentropic flow, the mass flow rate per unit area is maximum when Mach number is unity (Start with basic continuity equation). [6] OR Q2) a) Explain with the help of governing equation and T-S diagram, why shock waves causes supersonic flow to jump to subsonic flow. [5] b) Draw the Fanno curve on H-S diagram and discuss the effect of friction in case of subsonic and supersonic flow. [5] c) What do you mean by Rayleigh flow? What are the assumptions made in Rayleigh flow? Explain choking in Rayleigh flow. [6] P.T.O.

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Additional Info : 2003 Course
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