Draw the Brayton heat engine cycle with and without regeneration in T-s and h-s diagrams, and...
Draw the Brayton heat engine cycle with and without regeneration in T-s and h-s diagrams, and calculate properties at each state, efficiencies, work (power) output, work in and work out, heat in and heat out. Calculate properties assuming constant and variable specific heats, and for isentropic and non-isentropic compression and expansion.
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Draw the Brayton heat engine cycle with and without regeneration
in T-s and h-s diagrams, and...
An aircraft engine operates on a simple ideal Brayton cycle with a pressure ratio rp of...
An aircraft engine operates on a simple ideal Brayton cycle with
a pressure ratio rp of 9. Heat is added to the cycle at a rate of
490 kW; air passes through the engine at a rate of 1.1 kg/s; and
the air at the beginning of the compression is at P1 = 71 kPa and
T1 = 0 oC. Use constant specific heats at room temperature. The
properties of air at room temperature are cp =1.005 kJ/kg.K and k...
Ideal Brayton cycle with heat regeneration has a pressure ration rp-10.4, T1-300K. The effectiveness of the...
Ideal Brayton cycle with heat regeneration has a pressure ration rp-10.4, T1-300K. The effectiveness of the regenerator is 80%. The network output WmF350 kJ/kg and the thermal efficiency of the cycle is nth 54%. Assume that the air is an ideal gas with variable specific heats. al Draw The thermodynamic cycle Ts and Pv Calculate: b/ Turbine work (WT.out) c/ qin, apply the first law of thermodynamic to the system to calculate gout d/ qregen Heat Combustion chambet Turbine Compressor
Consider a closed Brayton cycle heat-engine. Air is compressed from 300K, 100 kPa to 580K, 700...
Consider a closed Brayton cycle heat-engine. Air is compressed from 300K, 100 kPa to 580K, 700 kPa. The air is heated at the rate of 950 kJ/kg before it enters the turbine. The isentropic efficiency of the turbine is 86%. Determine: a) the fraction of the turbine shaft power used to drive the compressor, and b) the thermal efficiency of the engine. Sketch the prooess on a T-s diagram. Do the calculation first with variable specific heats and then repeat...
An aircraft engine operates on a simple ideal Brayton cycle with a pressure ratio of 14.2....
An aircraft engine operates on a simple ideal Brayton cycle with a pressure ratio of 14.2. Heat is added to the cycle at a rate of450 kW; air passes through the engine at a rate of 1.20 kg/s; and the air at the beginning of the compression is at70 kPa and 0°C. Determine the power produced by this engine and its thermal efficiency. Use constant specific heats at room temperature. Wnet kW Round your final answer to one decimal place....
A gasoline engine operates on the air standard Otto cycle. The air intake to the engine...
A gasoline engine operates on the air standard Otto cycle. The air intake to the engine is at 300K and 95kPa (State 1). The air is compressed in the engine to an unknown pressure. Heat is then added during combustion at an amount of 1100 kJ/kg. At the end of the heat addition process, the temperature reaches 2200K. Compute the following: (a) the temperature at the end of the compression process, (b) the volumetric compression ratio of this engine, (c)...
13. Consider an air-standard Brayton cycle having 3 stages of compression with intercooling, a regenerator, and...
13. Consider an air-standard Brayton cycle having 3 stages of compression with intercooling, a regenerator, and 3 stages of expansion with reheat. Draw a T-s diagram assuming isentropic compression and expansion, perfect regeneration, inlet temperatures to the 3 compressors equal to the low temperature sink, and inlet temperatures to the 3 turbines equal to the high temperature source. Now consider the limit of infinite stages of compression with intercooling, perfect regeneration, and infinite stages of expansion with reheat. Draw a...
An aircraft engine operates on a simple ideal Brayton cycle with a pressure ratio of 12....
An aircraft engine operates on a simple ideal Brayton cycle with a pressure ratio of 12. The temperature of the air at the beginning of the compression process is 0°C. Heat is added to the cycle at a rate of 500 KW and air passes through the engine at a rate of 1 kg/s. Determine the net power produced by this engine, in kW. (Apply cold-air-standard assumptions: constant specific heat)
An ideal Brayton cycle with regeneration is shown below. Note that from 1 to 6, there...
An ideal Brayton cycle with regeneration is shown below. Note
that from 1 to 6, there is a heat rejection process. The pressure
ratio is 10 and the inlet to the compressor is at 300 K and 100
kPa. The maximum temperature is 1100 K. Use air as the working
fluid, and assume constant properties evaluated at 300
K.
(a) Find the net work output and the cycle efficiency assuming
the effectiveness of the regenerator is 100%
(b) Plot the...
Problem 9.106 using varaiable specific heat assumption (Non-Ideal Regenerative Brayton Cycle) 9-105 A gas turbine for...
Problem 9.106 using varaiable specific heat assumption
(Non-Ideal Regenerative Brayton Cycle)
9-105 A gas turbine for an automobile is designed with a regenerator. Air enters the compressor of this engine at 100 kPa and 30°C. The compressor pressure ratio is 8; the maximum cycle temperature is 800°C; and the cold airstream leaves the regenerator 10°C cooler than the hot airstream at the inlet of the regenerator. Assuming both the compressor and the tur- bine to be isentropic, determine the rates...
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...
An aircraft engine operates on a simple ideal Brayton cycle with
a pressure ratio rp of 9. Heat is added to the cycle at a rate of
490 kW; air passes through the engine at a rate of 1.1 kg/s; and
the air at the beginning of the compression is at P1 = 71 kPa and
T1 = 0 oC. Use constant specific heats at room temperature. The
properties of air at room temperature are cp =1.005 kJ/kg.K and k...
Ideal Brayton cycle with heat regeneration has a pressure ration rp-10.4, T1-300K. The effectiveness of the regenerator is 80%. The network output WmF350 kJ/kg and the thermal efficiency of the cycle is nth 54%. Assume that the air is an ideal gas with variable specific heats. al Draw The thermodynamic cycle Ts and Pv Calculate: b/ Turbine work (WT.out) c/ qin, apply the first law of thermodynamic to the system to calculate gout d/ qregen Heat Combustion chambet Turbine Compressor
Consider a closed Brayton cycle heat-engine. Air is compressed from 300K, 100 kPa to 580K, 700 kPa. The air is heated at the rate of 950 kJ/kg before it enters the turbine. The isentropic efficiency of the turbine is 86%. Determine: a) the fraction of the turbine shaft power used to drive the compressor, and b) the thermal efficiency of the engine. Sketch the prooess on a T-s diagram. Do the calculation first with variable specific heats and then repeat...
An aircraft engine operates on a simple ideal Brayton cycle with a pressure ratio of 14.2. Heat is added to the cycle at a rate of450 kW; air passes through the engine at a rate of 1.20 kg/s; and the air at the beginning of the compression is at70 kPa and 0°C. Determine the power produced by this engine and its thermal efficiency. Use constant specific heats at room temperature. Wnet kW Round your final answer to one decimal place....
A gasoline engine operates on the air standard Otto cycle. The air intake to the engine is at 300K and 95kPa (State 1). The air is compressed in the engine to an unknown pressure. Heat is then added during combustion at an amount of 1100 kJ/kg. At the end of the heat addition process, the temperature reaches 2200K. Compute the following: (a) the temperature at the end of the compression process, (b) the volumetric compression ratio of this engine, (c)...
13. Consider an air-standard Brayton cycle having 3 stages of compression with intercooling, a regenerator, and 3 stages of expansion with reheat. Draw a T-s diagram assuming isentropic compression and expansion, perfect regeneration, inlet temperatures to the 3 compressors equal to the low temperature sink, and inlet temperatures to the 3 turbines equal to the high temperature source. Now consider the limit of infinite stages of compression with intercooling, perfect regeneration, and infinite stages of expansion with reheat. Draw a...
An aircraft engine operates on a simple ideal Brayton cycle with a pressure ratio of 12. The temperature of the air at the beginning of the compression process is 0°C. Heat is added to the cycle at a rate of 500 KW and air passes through the engine at a rate of 1 kg/s. Determine the net power produced by this engine, in kW. (Apply cold-air-standard assumptions: constant specific heat)
An ideal Brayton cycle with regeneration is shown below. Note
that from 1 to 6, there is a heat rejection process. The pressure
ratio is 10 and the inlet to the compressor is at 300 K and 100
kPa. The maximum temperature is 1100 K. Use air as the working
fluid, and assume constant properties evaluated at 300
K.
(a) Find the net work output and the cycle efficiency assuming
the effectiveness of the regenerator is 100%
(b) Plot the...
Problem 9.106 using varaiable specific heat assumption
(Non-Ideal Regenerative Brayton Cycle)
9-105 A gas turbine for an automobile is designed with a regenerator. Air enters the compressor of this engine at 100 kPa and 30°C. The compressor pressure ratio is 8; the maximum cycle temperature is 800°C; and the cold airstream leaves the regenerator 10°C cooler than the hot airstream at the inlet of the regenerator. Assuming both the compressor and the tur- bine to be isentropic, determine the rates...
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