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- Assuming the clearance is negligible for a single stage compressor with the following data : Atmospheric pressure = 90 kPa, Atmospheric temperature = 17 degrees, Delivery pressure = 7 bar, Free air delivery flow rate = 0,2 m³/min. Take n= 1,3, Cp=1,005 KJ/Kg K, Cv=0,718 KJ/Kg K Determine the following : A) Which formula is used to evaluate the delivery temperature for an isentropic? B) the delivery temperature of air for a polytropic compression process with n=1,25 in Kelvin to 1 decimal place? C) the mass flow rate of air inside the compressor operating isentropically in kg/min to 3 decimal places? D) the power input to the compressor in kW to 2 decimal places if the compression is polytropic compression process with n=1,25? E) the power input to the compressor in kW to 3 decimal places if the compression reversible isothermal? F) the power input to the compressor if the compression is isentropic in kW to 3 decimal places? G) the delivery temperature of air for an isentropic…In a steam turbine system, suppose the value of ∆mH is constant (meaning, inlet and outlet conditions are maintained). From the energy balance equation, Qnet + Wnet = ∆mH + ∆KE + ∆PE or −0.1209 kW − 70 kW = ??̇? + 8.75 kW − 0.0068kW 1. What will happen to Wnet if there was no increase in kinetic energy, will the magnitude of Wnet increase or decrease? What should be the sign of potential energy so that Wnet will increase in magnitude?2. For a turbine system, what should happen to Qnet, ∆KE, and ∆PE to maximize the work done by the turbine? Which factor is the most significant?With a flow rate of 50 kmol/hour, air is compressed from P 1 = 1.2 bar pressure to P 2 = 6 bar pressure. The power required for this process is 98.8 kW. Temperature and speed data are given below. T1 = 300 K ,T 2 = 520 K ,v1 = 10 m/s, v2 = 3.5 m/s What is the heat rate transferred to the compressor (kJ/s)? Assume that air has Cp = (7/2)R and enthalpy is independent of pressure. (Gpt/Ai wrong ans not allowed)
- Air passes through a narrow section during horizontal flow. The initial air temperature is 21 [℃], flow rate 91.5 [m / s], pressure 10.56 [Kg / cm2 abs], later flow rate 152 [m/s], pressure 7.05 [Kg/cm2. abs], what is the temperature of the air at the outlet if there is no outside or heat coming in? The average specific heat of air is 7 [kcal / kg mol. ℃] and calculate as an ideal gas.The following data are given for a certain rocket unit: Thrust, 8000 N Propellant weight flow rate, 36 N/sec Speed of rocket, 800 m/s internal efficiency32%combustion efficiency 97 % Determine (a) the effective velocity; (b) total kinetic energy per second (c) calorific value of propellant (d) the propulsive efficiency (e) the overall efficiency (f) the specific impulse (g) the specific propellant consumption ????? =1/3 ?(?^2) hV cylinder = ?(?^2) h V frustrum = 1/3 ?ℎ(?^2 +?^2 +? ×?)Air flows steadily through an engine at constant temperature, 127 deg C. Assuming that the Kinetic and Potential energies are negligible and if the exit pressure is one-fourth of the initial pressure, in which the initial pressure is 702 kPa, the work per mass is Answer kJ (nearest whole number).
- Students did an experiment on Swansea University jet engine. They measured ambient temperature 16 deg C and ambient pressure 1.02 bar, engine RPM 64,664, thrust 17.5781 N, air flow 42.0557 l/s, fuel flow 8.6914 l/h, gauge combustion pressure 0.2942 bar. The temperature values (deg C) at compressor exit, turbine inlet and exhaust were recorded as 39.84, 869.53, 585.93. Assume density of fuel as 0.8 kg/L. The heating value of fuel is 42580 kJ/kg. The idea gas constant R is 0.287 kJ/kg K, the Cp value for air is 1.005 kJ/kg K and the value of specific heat ratio k is 1.4 Estimate the thrust specific fuel consumption value under ideal conditions (g/N-s) Enter your answer to four decimal places in the box below. answer ASAP would be appreciatedDetermine nozzle angle, blade angles at inlet and exit for a single stage impulse steam turbine developing 132 kW, speed of 3340 rpm, mean rotor diameter of 1 m, steam flow rate of 2 kg/s, blade velocity coefficient of 0.9, steam leaving nozzle at 400 m/s and steam discharges axially from turbine.The following particular refer to a two row velocity compounded Impulse steam turbine (wheel). Steam velocity at Nozzle exit-600 m/sec, Nozzle angle - 16°, Mean Blade velocity = 120 m/sec. Exit angles; first row of moving blades - 18° Fixed guide blades = 22⁰ Second row of moving blades 36° Steam flow rate=5kg/sec. Blade friction coefficient=0.85 Determine (1) Tangential thrust
- Students did an experiment on Swansea University jet engine. They measured ambient temperature 16 deg C and ambient pressure 1.02 bar, engine RPM 49,042, thrust 11.1328 N, air flow 23.2031 l/s, fuel flow 6.7383 l/h, gauge combustion pressure 0.1599 bar. The temperature values (deg C) at compressor exit, turbine inlet and exhaust were recorded as 31.64, 901.75, 568.35. Assume density of fuel as 0.8 kg/L. The heating value of fuel is 42,580 kJ/kg. The idea gas constant R is 0.287 kJ/kg K, the Cp value for air is 1.005 kJ/kg K and the value of specific heat ratio k is 1.4. What is the maximum fuel (thermal) efficiency for any engine operating between the measured maximum and minimum temperature limits can achieve?A water vapor turbine operates between 30 bar, 400 ° C input conditions. 160 m / s and an output corresponding to saturated steam at 0.7 bar and a speed of 100 m / s. The mass flow is 1,200 kg / min. And the output power is 10,800 kW. Deter- Men the magnitude and sense of heat transferred in KJ / min, if the variation of potential energy is negligible.A thermodynamic steady flow system receives 11 lbm/s of a viscous fluid where P1 = 40 psi, ρ1 = 70 lbm/ft^3, V1 = 350 ft/s, and u1 = 227 lbf/lbm. The elevation of the inflow is at zero-elevation. The fluid leaves the system at 100-foot elevation at a boundary where P2 = 18 psi, ρ2 = 80 lbm/ft^3, V2 = 400 ft/s, and u2 = 150 ft-lbf/lbm. During passage through the system, the work done by the fluid is 90 ft-lbf/lbm. Determine the heat added/rejected to/by the system. Assume g = 31.20 ft/s^2.