A closed type injector has a nozzle orifice diameter of 0.949 mm and themaximum cross sectional area of the passageand the seat is 1.75 mm2. The discharge coefficient fsve orifice is 0.85and for the passage is 0.80. The injection pressur eaverage press ure of charge durilacticiection is 25 bar when the needlecone is fully lifted up. Calculat efuel through the injector and the velocity of jet at that instant. Densityof fuel is 850 kg/m.bet werneed leCone075 bar and thevolume rate of flow per second of3

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Answered: A closed type injector has a nozzle…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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TThe venturi of a simple carburetor has a throat diar the coefficient of flow is 0.8. The fuel orifice has a and the coefflicient of fuel flow is 0.65. The gasolin surface is 5 mm below the throat, calculate * of 20 mm and er of 1.14 mm when the nozzle (i) the air-fuel ratio for a pressure drop of 0.0. tip is ne arted (ii) the aiaeDW atio when the nozzle tip is taken into account (iii) the minimum velocity of air or critical air velocity requi red to start the fuel flow when the nozzle tip is provided. Assume the density of air and fuel as 1.20 and 750 kg/m respectively.
outlet and the flow Velocity to be constent. Find B. An inward flow reaction turbine Ŝ supplying weter at a rete G00 litre/seconde with a relocity of flow 6m/s.The relocity lf mls restecfilely. Assuming the discharge to the Fedi radiat at l MIN LTE 1/1 at the Periphery and the wheel Welocity at intet are 24mls cand 4:20 AM O 17% C Ine loane engple at inlet. he head of water over the Lekeed.
What is specific speed of Kaplan turbine?
I need the answer as soon as possible
The Venturi of a simple carburetor has a throat diameter of 25 mm and the coefficient of air flow is 0.87. The fuel orifice has a diameter of 1.35 mm and the coefficient of the fuel flow is 0.66. The petrol surface is 6 mm below the throat. Find (a) The air-fue ratio for a pressure drops of 0.07 N/m² when the nozzle tip is neglected. (b) The air-fuel ratio when the nozzle tip is taken into account (c) the minimum velocity of air or critical air velocity required to start the fuel flow when nozzle tip is provided. Take the density of air and fuel as 1.2 and 750 kg/m³ respectively.
Problem-5: In a CD nozzle with a throat area of 0.75 m² of a rocket engine, gas at 7.5 MPa and temperature of 3200 K is in combustion chamber, is expanded fully to (nozzle exit pressure) 10.5 kPa for producing thrust. Assuming flow to be frozen and isentropic, Also, Assume, gamma, y 1.2 and molecular weight, MW = 24 kg/kmol, Assume, universal gas = constant = 8314 J/Kg K mol Determine: (1) the exit Mach number, (2) the maximum exit mass flow rate passing through this nozzle, and (3) the exit area (4) If ambient pressure, i.e. pressure outside nozzle = 10.5 kPa, What is the thrust developed? Fuel Oxidant Combustion zone Mixture of Hot gas at high pressure and Temprature Expansion Through Nozzle High velocity exhaust Liquid Propellant Rocket
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True or false
How tall would the jet of water be from the top of the nozzle? PR 16.5 kPa Jet 1.8 m 0.2 m 0.2 m Height
Need asap in 30 min i will give like
Solve it correctly please. I
= Determine the change of air-fuel ratio in when it takes off from sea level to a height of 5000 m. Carretor is adjusted for 15:1 ratio at sea level where air temperature (, C and e-engine carburetor pressure 1 bar. Assume the variation of temperature ofnire cvith altitude at t = t,- 0.0065 h where h is in m and t is in °C. The airle vsure decreases with altitude as per the relation h variation of air-fuel ratio with respect to altitude in steps of 1000 m on the trend. Show the variation on a graph and discuss. 19200 log10(1/p), where p is in bar. Evaluate the

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