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Problem: Air is drawn from the atmosphere into a turbomachine as shown in the figure. At...
CHE 3315 FLUID MECHANICS PROBLEM SHEET 5: MASS CONSERVATION AND FLOW RATE 1. Determine the mass...
CHE 3315 FLUID MECHANICS PROBLEM SHEET 5: MASS CONSERVATION AND FLOW RATE 1. Determine the mass flow rate of air having a temperature of 20C and gauge pressure 80 kPa as it flows through a circular duct 400 mm in diameter with an average velocity of 3 m/s. The gas specific constant R 286.9 JK /kg 2. Determine the average velocity of the steady flow at one outlet of a T- junction if the inlet flow speed is 6 m/s...
A centrifugal air compressor used in a gas turbine receives air at 100 kPa and 300...
A centrifugal air compressor used in a gas turbine receives air at 100 kPa and 300 K and discharges it at 400 kPa and 500 K. The velocity of the compressor's outgoing air is 100 m / s. Ignoring the speed at the compressor inlet. Determine the power required to drive the compressor, in kW, if the mass flow is 15 kg / s. Take the Cp of air equal to 1 kJ / (kg K) and assume that there...
Air flows into the jet engine shown in Figure 3.2 at a rate of 130 kg/s...
Air flows into the jet engine shown in Figure 3.2 at a rate of 130 kg/s and a speed of 254 m/s. Upon landing, the engine exhaust exits through the reverse thrust mechanism with a speed of in the direction indicated. Determine the reverse thrust applied by the engine to the airplane. Assume the inlet and exit pressures are atmospheric and that the mass flowrate of fuel is negligible compared to the air flowrate through the engine. (8 marks) V3...
Air enters a turbine in steady flow at 600 kPa, 740 K, and 120 m/s. The...
Air enters a turbine in steady flow at 600 kPa, 740 K, and 120 m/s. The exit conditions are 100 kPa, 450 K, and 220 m/s. A heat loss of 15 kJ/kg occurs, and the inlet area is 4.91 cm2 . Determine (a) the kinetic-energy change, in kJ/kg, (b) the power output, in kW, and (c) the ratio of the inlet- to outletpipe diameters
4.50 Air is compressed at steady state from 1 bara, 300 K, to 6 bara with...
4.50 Air is compressed at steady state from 1 bara, 300 K, to 6 bara with a mass flow rate of 4 kg/s. Each unit of mass passing from inlet to exit undergoes a process described by pvⁿ = constant, where n = 1.2677. Heat transfer occurs at a rate of 47.009 kJ per kg of air flowing to cooling water circulating in a water jacket enclosing the compressor. Kinetic and potential energy changes of the air from inlet to...
A gas turbine receives air at temperature T1 = 827 °C and specific volume v, -0.1...
A gas turbine receives air at temperature T1 = 827 °C and specific volume v, -0.1 m®/kg. Air exits the turbine at P2 = 3 bar and T2 = 450 °C. The volumetric flow rate of air at the inlet is 0.5 m/s. The power output on the shaft is 1900 kW. Determine: The pressure of air at the inlet (pa) in kPa [2 marks] b) The mass flow rate in kg/s [1 mark] c) Find the rate of heat...
Problem 7.67 The system shown at right is the back end of a jet aircraft engine....
Problem 7.67 The system shown at right is the back end of a jet aircraft engine. Operating information about the system is shown in the table and figure. Air flows steadily through the system. Assume changes in gravitational potential energy are negligible and air can be modeled as an ideal gas with room temperature specific heats. (a) Determine the velocity of the air leaving the nozzle, in m/s. (b) Determine the cross-sectional area Ac at the nozzle outlet, in m...
Problem 4.018 SI Air enters a horizontal, constant-diameter heating duct operating at steady state at 300...
Problem 4.018 SI Air enters a horizontal, constant-diameter heating duct operating at steady state at 300 K, 1 bar, with a volumetric flow rate of 0.25 m3/s, and exits at 325 K, 0.95 bar. The flow area is 0.05 m2 Assuming the ideal gas model with k-1.4 for the air, determine: (a) the mass flow rate, in kg/s, (b) the velocity at the inlet and exit, each in m/s, and (c) the rate of heat transfer to the air, in...
At steady state, air at 200 kPa, 325 K, and mass flow rate of 1.0 kg/s...
At steady state, air at 200 kPa, 325 K, and mass flow rate of 1.0 kg/s enters an insulated duct having differing inlet and exit cross-sectional areas. The inlet cross-sectional area is 6 cm2. At the duct exit, the pressure of the air is 100 kPa and the velocity is 300 m/s. Neglecting potential energy effects and modeling air as an ideal gas, determine a. the velocity of the air at the inlet, in m/s. b. the temperature of the...
Mutah University Faculty of Eng mies I Prof. M. Abu-Zaid Exam. 2 Date: 20-12-2018 Problem ()...
Mutah University Faculty of Eng mies I Prof. M. Abu-Zaid Exam. 2 Date: 20-12-2018 Problem () Steam enters a turbine with a mass flow rate o turbine develops a power of 1000 KW. At the inlet the pr MPa, the temperature is 400 °C, and the veloeity is exit, the pressure is 10 KPa, the quality is 0.9, and the velocity is (8 marks) pressure is 6 At the 10 m/s. m/s. Determine the rate of heat transfer to the...
CHE 3315 FLUID MECHANICS PROBLEM SHEET 5: MASS CONSERVATION AND FLOW RATE 1. Determine the mass flow rate of air having a temperature of 20C and gauge pressure 80 kPa as it flows through a circular duct 400 mm in diameter with an average velocity of 3 m/s. The gas specific constant R 286.9 JK /kg 2. Determine the average velocity of the steady flow at one outlet of a T- junction if the inlet flow speed is 6 m/s...
Air flows into the jet engine shown in Figure 3.2 at a rate of 130 kg/s and a speed of 254 m/s. Upon landing, the engine exhaust exits through the reverse thrust mechanism with a speed of in the direction indicated. Determine the reverse thrust applied by the engine to the airplane. Assume the inlet and exit pressures are atmospheric and that the mass flowrate of fuel is negligible compared to the air flowrate through the engine. (8 marks) V3...
A gas turbine receives air at temperature T1 = 827 °C and specific volume v, -0.1 m®/kg. Air exits the turbine at P2 = 3 bar and T2 = 450 °C. The volumetric flow rate of air at the inlet is 0.5 m/s. The power output on the shaft is 1900 kW. Determine: The pressure of air at the inlet (pa) in kPa [2 marks] b) The mass flow rate in kg/s [1 mark] c) Find the rate of heat...
Problem 7.67 The system shown at right is the back end of a jet aircraft engine. Operating information about the system is shown in the table and figure. Air flows steadily through the system. Assume changes in gravitational potential energy are negligible and air can be modeled as an ideal gas with room temperature specific heats. (a) Determine the velocity of the air leaving the nozzle, in m/s. (b) Determine the cross-sectional area Ac at the nozzle outlet, in m...
Problem 4.018 SI Air enters a horizontal, constant-diameter heating duct operating at steady state at 300 K, 1 bar, with a volumetric flow rate of 0.25 m3/s, and exits at 325 K, 0.95 bar. The flow area is 0.05 m2 Assuming the ideal gas model with k-1.4 for the air, determine: (a) the mass flow rate, in kg/s, (b) the velocity at the inlet and exit, each in m/s, and (c) the rate of heat transfer to the air, in...
Mutah University Faculty of Eng mies I Prof. M. Abu-Zaid Exam. 2 Date: 20-12-2018 Problem () Steam enters a turbine with a mass flow rate o turbine develops a power of 1000 KW. At the inlet the pr MPa, the temperature is 400 °C, and the veloeity is exit, the pressure is 10 KPa, the quality is 0.9, and the velocity is (8 marks) pressure is 6 At the 10 m/s. m/s. Determine the rate of heat transfer to the...
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