5. Consider a Jet-A fuel drop that is evaporating and burning in a jet engine. We will consider different values of the surrounding air temperature Too (of air that comes from the compressor). For all of the cases the following are held constant: The initial drop diameter The liquid fuel density is do is 40 microns, gas pressure p is 30 atm, 700 kg/m³, The temperature rise due to combustion AT, is 1800 K The fuel heat of vaporization Ah, is 2000 kJ/kg. Fuel boiling temperature T is 473 K The ratio of the gas thermal conductivity to heat capacity λg/ Cp is 0.2 x 104 kg/(m-s) The heat capacity (c) of the gas mixture is 1.5 kJ/kg-K

Please show all work of a,b,&c. A supersonic converging-diverging nozzle is near the exit of a turbojet engine. Its cross-section is circular. The gas has the properties of air, and the flow is isentropic. At the throat location (the minimum area) the air flow is choked (is Mach one) and the throat has diameter of 20 cm.

Where necessary, assume air as an ideal gas and consider R = 287J/(kg.K), Cp = 1005 J/(kg.K), Cv = 718 J/(kg.K).   A nozzle is a device that is used to increase the velocity of a fluidby varying the cross-sectional area. At the last section of a jetengine (Fig Q1.a, section 5), air with a mass flow rate of 50 kg/s ata pressure of 500 kPa and a temperature of 600 K enters a nozzlewith an inlet cross-sectional area of 5 m2. The exit area of thenozzle is 20% of its inlet area. The air leaves the nozzle at avelocity of 300 m/s. The nozzle is not well-insulated and duringthis process, 5 kJ/kg heat is lost. (iv) Determine the temperature of the air as it leaves the nozzle.(v) Calculate the pressure of the air as it leaves the nozzle.

Find the air-fuel ratio of a four-stroke, single-cylinder, air-cooled engine with fuel consumptionatime for 10 cc is 20.4 s and ay ansumption time for 0.1 m3 is IS 3 Find also brabre bultfuel consumption in g/kW 4.3 3 brake thermal efficiency. Assıunhe the density of air as 1.175 kg/m³ &ck specific gravity of fuel to be 0.7. The lower heating value of fuel is 43 MJ/kg and the dynamometer constant is 5000. (imm "he load is 17 kg at the of 3000 rpm.

Ex. 4 Superheated water Vapor enters a Valve at 3 MPa . 320 c and exits at a pressure f o.5 MPa. The exp- ausion is a throttling process. Determine the speciffic Flow avaitabilityat the inlet & exit and the irevers- i bility per unit mass Eメ KJ floding, each in l). Let T.= 25°cr Po= atm.

Please answer c A supersonic converging-diverging nozzle is near the exit of a turbojet engine. Its cross-section is circular. The gas has the properties of air, and the flow is isentropic. At the throat location (the minimum area) the air flow is choked (is Mach one) and the throat has diameter of 20 cm.

The values of Cp for the consu Ammonia in air is a toxic mixture when the ammonia is 0.45% by volume. Calculate how much leakage from an ammonia compressor can be tolerated per 1000m³ of space. The pressure is 1bas and the temperature is 15 °C. The molar mass of ammonia (NH3) is 17kg/kmol, and it may assume to act as a perfect gas in this case. and 70 °C. The vessel is A perfect insulated vessel having three compartments A, B and C of volume 1.3m³, 1.2 m³ and 1.0 m² respectively are separated from each other by thin membrane. Compartment A is filled with ritrogen having a pressure 3bar, at a temperature 25 °C, compartment B is filled with hydrogen having a pressure of 20bar at a temperature -40 °C and compartment C filled with carbon (IV) oxide at a temperature 175 °C and pressure 6bar. If the thin membrane are punctured and the three gases allowed to mix freely, calculate: (i) The final temperature of the mixture The final pressure of the mixture (iii) The change in entropy of the…

Please only answer STEP 2 question. THIS IS MY 3RD TIME POSTING THE SAME QUESTION AND NOT GETTING THE ANSWER I NEED. DONT SOLVE FOR THE MAIN QUESTION, I NEED THE ANSWER TO THE SECOND PART OF THE QUESTION.

Consider steam at 500 K and 200 kPa. Estimate its speed ofsound by two different methods: (a) assuming an ideal gasfrom Table B.4, or (b) using finite differences for isentropicdensities between 210 kPa and 190 kPa.

An aircraft engine has design parameter as shown in table 1 Parameters Mo Pa Ta Compressor Pressure Ratio Turbine Entry Temperature, TET Compressor Efficiency Turbine Efficiency Low Heating Value, LHV of Jet A Combustor Pressure Loss (% of Cdp) Air Mass Flow Cp, cold Y cold Cp,Hot Yhot Value 0 101Kpa 15°C 25 1500K 0.9 0.85 42 800 kJ/Kg 5 150 kJ/s 1000 J/kg/K 1.4 1150 J/Kg/K 1.333 Unless otherwise specified, the turbomachinery efficiency is isentropic. a) Analyze the engine type by sketching a schematic diagram as well as T-s diagram of the engine. b) determine the thrust and Specific Fuel consumption (SFC) of the engine if the engine uses convergent nozzle.