Q1/ A turbojet engine powers an aircraft that is flying at a speed of 240 m/s, has an exhaustspeed of 560 m/s, and a specific thrust of 325 N s/kg. Using the three different formulae,.calculate the propulsive efficiency. What are your comments?(Neglect the fuel-to-air ratio).Tgale efflux

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Answered: Q1/ A turbojet engine powers an…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

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A turbojet engine is travelling at 500 mph with an altitude of 8 km. The jet velocity is 1900 ft/s. The pressure and temperature at the jet exhaust is 4,000 Psf and 800 R. The mass flow is 9300 slugs/hr. a. Calculate the Thrust horsepower. b. What is the propulsive efficiency? c. Calculate the TSFC if the turbojet consumes 15 lb of fuel per hour.
A turbojet produces a net thrust of 4,500 lbs with a fuel mass flow rate of 2825 lbm/hr. Compute for the specific fuel consumption.
Conceptualize, model and simulate a turbofan engine using any software package
A turbojet produces a net thrust of 4,000 lbs with a fuel mass flow rate of 2000lbm/hr. Compute for the specific fuel consumption.
Part (a) Find the efficiency of an ideal engine operating between these reservoirs. Remember the efficiency is unit-less, therefore so should your number be as well. ( Party a was incorrect can you try again ) Part (d) What if the actual work done (more realistically) is W = 290 J during a single cycle; what is the efficiency of this engine if the energy input is the same (again, the number should be unit-less)? Part (e) What is equation for the new power output per cycle (in Watts) of this new (and more realistic) engine?
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Q3/ Answer the following question: A turbocharged, 4 cylinders and 2 liters engine operates with stoichiometric gasoline, 2000 rpm, and overall volumetric efficiency of 150%. The turbocharger has an isentropic efficiency of 80% for each of its parts. Exhaust enters the turbocharger at 400° C and 150 kPa. Reduction or increase of the pressure inside any part of the turbocharger is 25 kPa. Calculate the power losses of the turbocharger. Assume that the ambient conditions are 28° C and 100 kPa, C, and y for the exhaust are 1.107 kJ/kg.K and 1.35, respectively.
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In an engine working on the Diesel eycle the ratios of the weights of air and fuel supplied is 50: 1. The temperature of air at the beginning of the compression is 60 °C and the compression ratio used is 14: 1. What is the ideal efficiency of the engine, Calorifie value of fuel used is 42000 k.J/kg. Assume C, - 1.004 kJ/kg K and C, = 0.717 kJ/kg K for air.

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Q1/ A turbojet engine powers an aircraft that is flying at a speed of 240 m/s, has an exhaust speed of 560 m/s, and a specific thrust of 525 N s/kg. Using the three different formulae, calculate the propulsive efficiency. What are your comments? (Neglect the fuel-to-air ratio). . mni afflux