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100 kPa 50°C 350°C Turbine 130 kPa Exhaust gases 470C 120 kPa Aftercooler Cold air 30°C...
Combustion gases enter an adiabatic gas turbine at 800oC and 900 kPa and leave at 100...
Combustion gases enter an adiabatic gas turbine at 800oC and 900 kPa and leave at 100 kPa with a low velocity. Treating the combustion gases as air (R = 0.2870 kPa*m3/kg, cp = 1.005 kJ/kg*K, k = 1.4) and assuming an isentropic efficiency of 82 percent, determine the work output of the turbine and the exit temperature.
J. An adiabatie gas turbine espands air at 1300 kPa and 500P C to 100 kPa and 127"C Au ers turbine through a 02-...
J. An adiabatie gas turbine espands air at 1300 kPa and 500P C to 100 kPa and 127"C Au ers turbine through a 02-m opening with an average velocity of 40 m/s, and exhausts through a 1-m opening Detormine (a) the mass fnow rate of air through the turbine and (b) the power produced by the turbine For air, take the ideal gas constant and specific heat value at constant pressure as o Yue Determine (a) the mass flow rate...
P, = 1.3 MPa T,-527℃ V1 = 40 m/s 4,=0.2 m 2 3. Hot exhaust gases...
P, = 1.3 MPa T,-527℃ V1 = 40 m/s 4,=0.2 m 2 3. Hot exhaust gases flow steadily through a turbine with inlet and outlet states as shown. Heat is lost to the surroundings at a rate of 500 kW. Treat the exhaust gases as air and using Table A-17, find the following: a) The mass flow rate through the turbine, [kg/s] b) The Power output of the turbine, Wout [MW] Turbine Wout owE P,-100 kPa T2= 127℃ V2- 52...
Air enters the turbine stage 1 of a gas turbine with reheat at 1200 kPa, 1200...
Air enters the turbine stage 1 of a gas turbine with reheat at 1200 kPa, 1200 K, and expands to 100 kPa in two stages. Between the turbine stages, the air is reheated at a constant pressure of 350 kPa to 1200 K. ein lin Combustor Reheat combustor T. = 881.4K To = 1200 K Po = 350 kPa b 2 3 a Turbine stage 2 Turbine stage 1 T3 = 1200 K P3 = 1200 kPa Compressor h4 =...
7. An industrial turbine process requires a steady 0.5 kg/s of air at 200 kPa. This air is to be the exhaust from a...
7. An industrial turbine process requires a steady 0.5 kg/s of air at 200 kPa. This air is to be the exhaust from a specially designed turbine with inlet state 400 kPa, 400 K. The heat transfer could be obtained from a source at 500 K if necessary. This process may be assumed to be reversible and the changes in kinetic and potential energy are negligible. Air is an ideal gas, with constant specific heats, using Table A.S (a) Which...
A moist air of 25 °C and 200 kPa with relative humidity of 50% is mixed...
A moist air of 25 °C and 200 kPa with relative humidity of 50%
is mixed with nitrogen of 25 °C and 200 kPa. Then, the mixture is
expanded through a turbine to 100 kPa. Assuming the turbine is
ideal, determine the minimum nitrogen and moist air mole ratio
(kmol N2/kmol moist air) that does not induce condensation within
the turbine. Assume specific heat ratios are same for water vapor,
dry air, and nitrogen as 1.4.
3. (10 points) A...
Air enters the compressor of a cold air-standard Brayton cycle at 100 kpa, 300 k, with...
Air enters the compressor of a cold air-standard Brayton cycle at 100 kpa, 300 k, with a mass flow rate of 6 kg/s. the compressor pressure ratio is 10, and the turbine inlet temperature is 1400 K. For k = 1.4, calculate a. The thermal efficiency of the cycle b. The back work ratio c. The net power developed, in kW d. Reconsider the above with an ideal regenerator.
5-30 Air enters an adiabatic nozzle steadily at 300 kPa, 200°C, and 30 m/s and leaves...
5-30 Air enters an adiabatic nozzle steadily at 300 kPa, 200°C, and 30 m/s and leaves at 100 kPa and 180 m/s. The inlet area of the nozzle is 80 cm². Determine (a) the mass flow rate through the nozzle, (b) the exit temperature of the air, and (c) the exit area of the nozzle. Answers: (a) 0.5304 kg/s, (b) 184.6°C, (c) 38.7 cm P = 300 kPa T, = 200°C Vi = 30 m/s A = 80 cm AIR...
Air enters the compressor of a cold air-standard Brayton cycle with regeneration at 100 kPa, 300...
Air enters the compressor of a cold air-standard Brayton cycle with regeneration at 100 kPa, 300 K, with a volume flow rate of 5 m3/s. The compressor pressure ratio is 8, and the turbine inlet temperature is 1400 K. The turbine and compressor each have isentropic efficiencies of 80% and the regenerator effectiveness is 80%. For the air, k = 1.4 and the ambient temperature is T0 = 300 K. -Determine the thermal efficiency of the cycle. -determine the back...
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
J. An adiabatie gas turbine espands air at 1300 kPa and 500P C to 100 kPa and 127"C Au ers turbine through a 02-m opening with an average velocity of 40 m/s, and exhausts through a 1-m opening Detormine (a) the mass fnow rate of air through the turbine and (b) the power produced by the turbine For air, take the ideal gas constant and specific heat value at constant pressure as o Yue Determine (a) the mass flow rate...
P, = 1.3 MPa T,-527℃ V1 = 40 m/s 4,=0.2 m 2 3. Hot exhaust gases flow steadily through a turbine with inlet and outlet states as shown. Heat is lost to the surroundings at a rate of 500 kW. Treat the exhaust gases as air and using Table A-17, find the following: a) The mass flow rate through the turbine, [kg/s] b) The Power output of the turbine, Wout [MW] Turbine Wout owE P,-100 kPa T2= 127℃ V2- 52...
Air enters the turbine stage 1 of a gas turbine with reheat at 1200 kPa, 1200 K, and expands to 100 kPa in two stages. Between the turbine stages, the air is reheated at a constant pressure of 350 kPa to 1200 K. ein lin Combustor Reheat combustor T. = 881.4K To = 1200 K Po = 350 kPa b 2 3 a Turbine stage 2 Turbine stage 1 T3 = 1200 K P3 = 1200 kPa Compressor h4 =...
7. An industrial turbine process requires a steady 0.5 kg/s of air at 200 kPa. This air is to be the exhaust from a specially designed turbine with inlet state 400 kPa, 400 K. The heat transfer could be obtained from a source at 500 K if necessary. This process may be assumed to be reversible and the changes in kinetic and potential energy are negligible. Air is an ideal gas, with constant specific heats, using Table A.S (a) Which...
A moist air of 25 °C and 200 kPa with relative humidity of 50%
is mixed with nitrogen of 25 °C and 200 kPa. Then, the mixture is
expanded through a turbine to 100 kPa. Assuming the turbine is
ideal, determine the minimum nitrogen and moist air mole ratio
(kmol N2/kmol moist air) that does not induce condensation within
the turbine. Assume specific heat ratios are same for water vapor,
dry air, and nitrogen as 1.4.
3. (10 points) A...
Air enters the compressor of a cold air-standard Brayton cycle at 100 kpa, 300 k, with a mass flow rate of 6 kg/s. the compressor pressure ratio is 10, and the turbine inlet temperature is 1400 K. For k = 1.4, calculate a. The thermal efficiency of the cycle b. The back work ratio c. The net power developed, in kW d. Reconsider the above with an ideal regenerator.
5-30 Air enters an adiabatic nozzle steadily at 300 kPa, 200°C, and 30 m/s and leaves at 100 kPa and 180 m/s. The inlet area of the nozzle is 80 cm². Determine (a) the mass flow rate through the nozzle, (b) the exit temperature of the air, and (c) the exit area of the nozzle. Answers: (a) 0.5304 kg/s, (b) 184.6°C, (c) 38.7 cm P = 300 kPa T, = 200°C Vi = 30 m/s A = 80 cm AIR...
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