Q1/ A simple jet carburetor is required to supply 0.1 kg/s of air and 8.333x10-3 kg/s of fuel of density 780 kg/m³. The air is initially at 1.013 bar and 27 C. Assume the flow is an isentropic and compressible. The air flow velocity 80 m/s of the chock. The pressure drop across the fuel metering orifice is 0.75 of that at the chock. Calculate the throat diameter and orifice diameter? Take the velocity coefficient for the venture to be 0.8 and the coefficient of discharge of the main fuel jet to be 0.6.

Q1/ A simple jet carburetor is required to supply 0.1 kg/s of air and 8.333x10-3 kg/s of fuel of density 780 kg/m³. The air is initially at 1.013 bar and 27 C. Assume the flow is an isentropic and compressible. The air flow velocity 80 m/s of the chock. The pressure drop across the fuel metering orifice is 0.75 of that at the chock. Calculate the throat diameter and orifice diameter? Take the velocity coefficient for the venture to be 0.8 and the coefficient of discharge of the main fuel jet to be 0.6.

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

See similar textbooks

Similar questions

A simple jet carburetor is required to supply 5 kg of air and 0.5 kg of fuel per minute. The fuel specific gravity if 0.75. The air is initially at 1 bar and 300 K. Calculate the throat diameter of the choke for a flow velocity of 100 m/s. Velocity coefficient is 0.8. If the pressure drop across the fuel metering orifice is 0.80 of that of the choke. Calculate orifice diameter assuming Cdf=0.60 and γ = 1.4
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.
Determine the diameter of a fuel orifice for a 4-stroke engine working on diesel cycle developing 18 kw per cylinder at 2000 rpm, using 0.27 kg/kw.h. of fuel of 30° API. The duration of the crank injection is 30° of crank travel. The fuel injection pressure is 125 bar and combustion chamber pressure is 35 bar. Take velocitycoefficient = 0.9 and Pr=141.5/(131.5 + API)
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.
3 litters, 4 cylinders engine, multipoint port fuel injection, one for each cylinder. AF ratio is 14.6, the volumetric efficiency is 90%. The engine speed at idle condition is 550 rpm with stoichiometric gasoline and inlet pressure is 30 kPa. But the engine speed is 5900 rpm with stoichiometric gasoline of maximum power, the inlet pressure is 101 kPa. Calculate the following: a. mass air flow rate in one cylinder at maximum speed, b. mass fuel flow rate into one cylinder through an injector, c. mass air flow into one cylinder at idle speed, d. mass fuel flow rate into one cylinder at idle speed, e. injection pulse duration is seconds at idle conditions at idle, f. injection pulse duration is degrees of engine rotation at idle conditions.
Choose the correct opt
Q.13 An automobile carburettor having its flost chamber vented to the atmosphere is tested at sea level conditions in the factory without air cleaner. The main metering system of this carburettor is found to yield a fuel-air ratio of 0.065. The venturi throat pressure is 0.85 bar. The carburettor is now installed in an automobile and air cleaner is placed on the inlet to carburettor. The air flow rate with or without air filter is 230 kg/hr. The pressure drop through the filter is found to be 0.035 bar at sea level conditions. Issuming 7 0und orifice cocfficient to be constant calculate: The venturi throat pressure with air cleaner. (11) Air-fucl ratio with air cleaner,
An engine working with injection system having the following specifications Injection pressure = 4000 kPa. Injection duration = 15 milliseconds. Penetration length 20 cm. Discharge coefficient = 0.75. The cylinder pressure at time of injection = 2500 kPa. Fuel density = 700 kg/m3. The fuel pump had to be replaced with new one. The new pumnp pressure is 6000 kPa injecting at cylinder pressure 3000 kPa.T using new set of injectors with CD = 0.8 and fuel with density = 800 kg/m3. milliseconds. The new injection duration must be set to Keeping all other parameters constant, as fuel is changed to higher density types, the injection duration must be Keeping all other parameters constant, as Cd value increases, the injection duration must be
Question 3.) An engine has an inlet stagnation condition of 300 bar and 4000 kelvin. Methane and liquid oxygen make up the products of combustion and have a specific heat ratio k = 1.14 and a gas constant R = 383 J/kg-k. The nozzle has an exit to throat area ratio of A₂ / Ath = 34.34 and has an exit diameter of 1.3 meters. Calculate the following: (a) Mass flow rate m for choked flow (b) Critical Mach numbers (c) Critical pressures
7. An OTTO cycle operates on 0.15 lb/s of air from 15 psia and 1500F at the beginning ofcompression. The temperature at end of combustion is 50000R; compression ratio is 5:5; hot airstandard, k = 1.37.1 Solve for the volume flow rate at point 17.2 Determine the pressure at point 27.3 Calculate temperature at point 2
I need the answer quickly
A simple carburetor is adjusted for a 15.2:1 air-fuel ratio at sea level and 600F. Determine the air-fuel ratios at 10,000 feet, 16,000 feet and 20,000 feet altitudes.