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B.Tech. 6'h Semester, April- May 20L3 SUBJECT:- Conversion System ( NET SCHEME) BRANCH: - MECHANICAL ENGINEERING b4ffieces DURATION: - 3 HRS Total marks: - 70 Note: - Solve anv two parts from each Question. Eoch part havina 7 marks, Question:-L (A) Explain La-Mont Boiler with the help of diagram & also write its advantages. 4'(B) Define boiler mountings & accessories. Explain any one boiler accessories with the help of diagram (C) Explain the condition for maximum discharge through chimney & also derive its expression. Question: -2 ;-fA) ln a test, the following observations were made- Vacuum = 70 cm of Hg, = 76 cm of Hg, Mean temp of condensation = 35oC, Hot-well temperature = 29oC, mass of cooling water = 45500 kglh, lnlet water temperature = l-6 50C, Outlet water temperatuie = 310C, Mass of condensate = 1,2OOkg/h, Partial prbssure of steam at 350C =0.05622 bar. Find (i)The mass of air present per unit condenser volume, (ii) Vacuum efficiency (iii) The condensate undercooling & (iv) Condenser efficiency. (B)Explain the Daltons law of partial pressure & also write down the effect of air leakage & removal in conde nser (C) Explain the surface condenser with Principle & neat sketch. Question; - 3 (A) A tidal power plant of the single basin type has a basin area of 30 x 106 mt. The tide has a range of 1-2 m .The turbine stops operating when the head on its falls below 3 m Calculate the energy generated in 1 filling process, in KWH if turbine generator efficiency is73%. Assume water density is 1025 kg/m3 & time period is 6h, 1 2.5 min. r(B) Explain Claude cycle OTEC system with neat sketch lC) Explain Thermo-electric power generation with its principle & neat sketch. Question: -4 z-(A) An aircraft flies at 960 kmph. One of its turbojet engines takes in 40 kg/s of air & expands the gases to the ambient pressure The air fuel ratio is 50 & the lower calorific value is a3 MJ/kg. For maximum thrust power determine: (i) jet velocity (ii) Thrust (iii) Specific thrust (iv) Thrust power (v) propulsive, thermal & overall efficiency (vi) Thrust specific fuel consumption. ,.'(BI Aramjet engine operates at M = 1.5, T1 =245.9 K, Pr = 0.440 bar & air density 0 624 kg/m3 The of at entry is 50 cm & the stagnation temperature at the nozzle entry is 1600 K. The calorific value of the fuel used is 40 MJ/kg. The velocity of air the diffuser exit is negligible. Stagnation pressure loss in combustion chamber is2%.Calculate (a) efficiency of the idealcycle (b)flight speed (c) air flow rate (d) diffuser pressure ratio (e) fuel-air ratio (f) nozzle pressure ratio. Assume R = 287 kj/kgk, diffuser efficiency =90To, combustion chamber efficiency =98%. (C) Explain the construction & working of turboprop engine with the help of neat sketch.
