two stage compressor with intercooling between the stages is used to compress air from 1 bar...
two stage compressor with intercooling between the stages is used to compress air from 1 bar and 15C to 9 bar in a Gas-Turbine cycle . The high pressure turbine drives the compressor whereas low pressure turbine is coupled with an electrical generator. The compressor and turbine efficiencies are 85%; 75%, respectively. Heat is added to the compressed air after leaving the compressor till its temperature reaches 900C. The air then expands in HPT to an intermediate pressure and reheat to the 900C before expanding another time in LPT to 1 bar. Find the intermediate pressure, the turbine work, the back work ratio, and the cycle thermal efficiency. Assume 15 kg/s air flow rate.
be neat and solve with the all steps show your all works and explain how you got the numbers im struggleing to understand please solve it clearly
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two stage compressor with intercooling between the stages is
used to compress air from 1 bar...
Thermodynamics 2 Brayton Cycle neering History Watch Gotham (201 Watch The walking Watch House ofCar 01Cabral.p...
Thermodynamics 2
Brayton Cycle
neering History Watch Gotham (201 Watch The walking Watch House ofCar 01Cabral.p 錯 °Keeffe-and-Phan Group Solving Problem A two stage compressor with intercooling between the stages is used to compress air from 1 bar and 150C to 9 bar in a Gas-Turbine cycle . The high pressure turbine drives the compressor whereas low pressure turbine is coupled with an electrical generator. The compresson and turbine efficiencies are 85%; 75%, respectively Heat is added to the compressed...
Problem 1 A Brayton-cycle power plant takes in air at 100 kPa and 26.7°C. Compression in two stag...
please solve by exact analysis
Problem 1 A Brayton-cycle power plant takes in air at 100 kPa and 26.7°C. Compression in two stages with intercooling, and each stage has a pressure ratio of 2.38 and an efficiency of 84%, with intercooling to 26.7°C The maximum temperature of the cycle is 676.7°C Turbine efficiency is 82%. The turbine and compressor are assumed adiabatic. A regenerator heats the compressed air to 326.7°C before sending it to the combustor. Calculate (a) the back...
Question 10 10 pts A gas turbine operates with a two stage air compressor incorporating intercooling,...
Question 10 10 pts A gas turbine operates with a two stage air compressor incorporating intercooling, the pressure ratio and the air inlet temperature of 20°C is the same for both stages. The overall compression ratio is 10:1. The isentropic efficiency of both stages is 89.0% For air take y=1.4 and Co=1.005 KJ/kg.k Determine the specific work required to drive both compressors, your answer should be in KJ/kg to 1 decimal place. DO NOT INCLUDE UNITS IN YOUR ANSWER 5...
In an aircraft cooling system, air enters the compressor at 1 bar and 4°C and is...
In an aircraft cooling system, air enters the compressor at 1 bar and 4°C and is compressed to 3 bar with an isentropic efficiency of 72%. The compressed air is cooled in a heat exchanger at constant pressure to 55°C and expands in an expander to 1 bar with an isentropic efficiency of 78%. The low temperature air absorbs heat load of 3 tonnes of refrigeration at constant pressure before re- entering the compressor. The compressor is driven by the...
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 =...
4. A regenerative two-stage gas turbine with reheat operating on the standard-air Brayton cycle i...
4. A regenerative two-stage gas turbine with reheat operating on
the standard-air Brayton cycle is illustrated in Figure 3. In an
ideal Brayton cycle, the processes in the turbines and compressor
are adiabatic and isentropic, and the air flows through the
combustor and heat exchangers at constant pressure.
a) Show that the maximum total work output is
developed when the pressure ratio is the same across each stage, if
the temperature at the inlet to each turbine stage is the...
A single acting compressor is required to deliver air at 60 bar from an induction pressure...
A single acting compressor is required to deliver air at 60 bar from an induction pressure of 1 bar, at the rate of 3 m3/min measured at free air conditions of 1.013 bar and 15oC. The compression is carried out in two stages with an ideal intermediate pressure and complete intercooling. The clearance volume is 3% of the swept volume in each cylinder and the compressor speed 750 rev/min. The index of compression and re-expansion is 1.3 for both cylinders...
a,b,c Air enters the compressor of a gas turbine at 1 bar, 20°C with a volumetric...
a,b,c
Air enters the compressor of a gas turbine at 1 bar, 20°C with a volumetric flow ies of 90%. The plant incorporates a regeneraar of 75% effectiveness. determine: s. The pressure ratio across the compressor is 10. The turbine inlet is 1427°C and the turbine and compressor each have isentropic temperatu Using the air-standard Brayton cycle as the model for this system. a.) b) c.) the net work output, MW the back work ratio the cycle's thermal efficiency pthe...
Thermodynamics 2
Brayton Cycle
neering History Watch Gotham (201 Watch The walking Watch House ofCar 01Cabral.p 錯 °Keeffe-and-Phan Group Solving Problem A two stage compressor with intercooling between the stages is used to compress air from 1 bar and 150C to 9 bar in a Gas-Turbine cycle . The high pressure turbine drives the compressor whereas low pressure turbine is coupled with an electrical generator. The compresson and turbine efficiencies are 85%; 75%, respectively Heat is added to the compressed...
please solve by exact analysis
Problem 1 A Brayton-cycle power plant takes in air at 100 kPa and 26.7°C. Compression in two stages with intercooling, and each stage has a pressure ratio of 2.38 and an efficiency of 84%, with intercooling to 26.7°C The maximum temperature of the cycle is 676.7°C Turbine efficiency is 82%. The turbine and compressor are assumed adiabatic. A regenerator heats the compressed air to 326.7°C before sending it to the combustor. Calculate (a) the back...
Question 10 10 pts A gas turbine operates with a two stage air compressor incorporating intercooling, the pressure ratio and the air inlet temperature of 20°C is the same for both stages. The overall compression ratio is 10:1. The isentropic efficiency of both stages is 89.0% For air take y=1.4 and Co=1.005 KJ/kg.k Determine the specific work required to drive both compressors, your answer should be in KJ/kg to 1 decimal place. DO NOT INCLUDE UNITS IN YOUR ANSWER 5...
In an aircraft cooling system, air enters the compressor at 1 bar and 4°C and is compressed to 3 bar with an isentropic efficiency of 72%. The compressed air is cooled in a heat exchanger at constant pressure to 55°C and expands in an expander to 1 bar with an isentropic efficiency of 78%. The low temperature air absorbs heat load of 3 tonnes of refrigeration at constant pressure before re- entering the compressor. The compressor is driven by the...
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 =...
4. A regenerative two-stage gas turbine with reheat operating on
the standard-air Brayton cycle is illustrated in Figure 3. In an
ideal Brayton cycle, the processes in the turbines and compressor
are adiabatic and isentropic, and the air flows through the
combustor and heat exchangers at constant pressure.
a) Show that the maximum total work output is
developed when the pressure ratio is the same across each stage, if
the temperature at the inlet to each turbine stage is the...
a,b,c
Air enters the compressor of a gas turbine at 1 bar, 20°C with a volumetric flow ies of 90%. The plant incorporates a regeneraar of 75% effectiveness. determine: s. The pressure ratio across the compressor is 10. The turbine inlet is 1427°C and the turbine and compressor each have isentropic temperatu Using the air-standard Brayton cycle as the model for this system. a.) b) c.) the net work output, MW the back work ratio the cycle's thermal efficiency pthe...
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