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.
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Combustion gases enter an adiabatic gas turbine at 800oC and 900
kPa and leave at 100...
Combustion gases enter an adiabatic gas turbine at 1540 F degrees and 120 psia and leave...
Combustion gases enter an adiabatic gas turbine at 1540 F degrees and 120 psia and leave at 60 psia with a low velocity. Treating the combustion gases as air and assumming an isentropic efficiency of 82 percent, determine the work output of the turbine. Assume that combustion gases can be treated as an ideal gas with variable specific heats.
In a combustion turbine using natural gas as the fuel, air enters the compressor at 98...
In a combustion turbine using natural gas as the fuel, air enters the compressor at 98 kPa and 300 "K. The pressure ratio in the compressor is 8 and the isentropic efficiency of the compressor is 85%. The outlet temperature of the combustion chamber is 1200 K. The pressure drops by 4 percent in the combustion chamber. The exit pressure of the turbine is 102 kPa and the isentropic efficiency of the turbine is 90%. Find: a) The exit temperature...
7-132 Hot combustion gases enter the nozzle of a turbojet engine at 260 kPa, 7478C, and...
7-132 Hot combustion gases enter the nozzle of a turbojet engine at 260 kPa, 7478C, and 80 m/s, and they exit at a pressure of 85 kPa. Assuming an isentropic efficiency of 92 percent and treating the combustion gases as air, determine (a) the exit velocity and (b) the exit temperature.
Problem 1 (Marks 3) Smithfield power station in NSW, Australia operates on 4 gas turbines. Each of the gas turbine unit...
Problem 1 (Marks 3) Smithfield power station in NSW, Australia operates on 4 gas turbines. Each of the gas turbine unit operates on the regenerative Brayton Cycle between the pressure limits of 100 kPa and 700 kPa. Air enters the compressor at 30°C at a rate of 12.6 kg/s and leaves at 260°C. It is then heated in a regenerator to 400°C by hot combustion gases leaving the turbine. Diesel fuel with heating value of 42,000 kJ/kg is burned in...
WGTC η.cn = 95% Gas turbine cycle (GTc) e,I = 100 kW Compressor Turbine Generator 께,- Combustor ...
wGTC η.cn = 95% Gas turbine cycle (GTc) e,I = 100 kW Compressor Turbine Generator 께,- Combustor Pi 100 kPa Regenerator Evaporator Turbine Generator Vapor turbine cycde (VTC) T, = T, + 20 K Condenser 10 Pump Saturated liquid A combined cycle plant operates with a topping gas turbine and a bottoming vapor turbine cycle. The working fluid in the vapor turbine cycle is water. The gas turbine cycle (GTC) electric generator produces 100kW of electric power For air use...
Q A power plant located at Penang has been generated by Brayton cycle to operate gas...
Q A power plant located at Penang has been generated by Brayton cycle to operate gas turbine involved air as the working fluid of the plant. Fresh air has been supplied to the compressor at 35°C and 100 kPa, while entered the combustion chamber at 350°C and 0.8 MPa with flow rate of 1200 kg/min and leaves the chamber at 1127°C. However, the power output for the plant has been measured during the experiment is 70000 kW Assume constant properties...
A jet engine propels an aircraft at 254 m/s through air at 39 kPa and 273 K. The compressor pressure ratio is 9 and the temperature at the turbine inlet is 873 K. b) Taking the pressure in the combust...
A jet engine propels an aircraft at 254 m/s through air at 39 kPa and 273 K. The compressor pressure ratio is 9 and the temperature at the turbine inlet is 873 K. b) Taking the pressure in the combustion chamber as 843.5 kPa and the temperature at the turbine exit to be 518 K, determine the velocity of the exhaust gases. Give your answer in m/s to 2 decimal places. Assume ideal operation for all components and constant specific...
Gas enters an adiabatic turbine with enthalpy 3456 kJ/kg and velocity 100 m/s. It leaves the...
Gas enters an adiabatic turbine with enthalpy 3456 kJ/kg and velocity 100 m/s. It leaves the turbine with enthalpy 2675 kJ/kg and velocity 200 m/s. Had the flow been isentropic, the enthalpy would be 2315 k./kg at exit. Assume (V2s-V2). Determine the following: QUESTION 2 Total enthalpy at inlet in kJ/kg Enthalpy at exit in kJ/kg A 2392 B. 2695 C. 2461 D. 2335 Total isentropic enthalpy at exit in kJ/kg Total-to-total efficiency (%) The work done (in kJ/kg) E766...
3a. A gas-turbine power plant operates on the simple Brayton cycle between the pressure limits of...
3a. A gas-turbine power plant operates on the simple Brayton cycle between the pressure limits of 14.7 and 200 psia. Air enters the compressor at 77°F at a rate of 28 lbm/s and leaves at 750°F. Fuel is burned in the combustion chamber and the combustion gases enter the turbine at 2000°F. Combustion gases leave the turbine whose isentropic efficiency is 85 percent. Treating the combustion gases as air and using constant specific heats evaluated at 900°F, determine (a) the...
An adiabatic turbine operates at steady state. Air enters the turbine at a pressure and temperature...
An adiabatic turbine operates at steady state. Air enters the turbine at a pressure and temperature of 800 kPa and 1100 K, respectively, and exits at 100 kPa. A temperature sensor at the turbine exit indicates that the exit air temperature is 700 K. Kinetic and potential energy effects are negligible, and the air can be treated as an ideal gas. Determine if the exit temperature reading can be correct. If yes, determine the turbine isentropic efficiency.
In a combustion turbine using natural gas as the fuel, air enters the compressor at 98 kPa and 300 "K. The pressure ratio in the compressor is 8 and the isentropic efficiency of the compressor is 85%. The outlet temperature of the combustion chamber is 1200 K. The pressure drops by 4 percent in the combustion chamber. The exit pressure of the turbine is 102 kPa and the isentropic efficiency of the turbine is 90%. Find: a) The exit temperature...
Problem 1 (Marks 3) Smithfield power station in NSW, Australia operates on 4 gas turbines. Each of the gas turbine unit operates on the regenerative Brayton Cycle between the pressure limits of 100 kPa and 700 kPa. Air enters the compressor at 30°C at a rate of 12.6 kg/s and leaves at 260°C. It is then heated in a regenerator to 400°C by hot combustion gases leaving the turbine. Diesel fuel with heating value of 42,000 kJ/kg is burned in...
wGTC η.cn = 95% Gas turbine cycle (GTc) e,I = 100 kW Compressor Turbine Generator 께,- Combustor Pi 100 kPa Regenerator Evaporator Turbine Generator Vapor turbine cycde (VTC) T, = T, + 20 K Condenser 10 Pump Saturated liquid A combined cycle plant operates with a topping gas turbine and a bottoming vapor turbine cycle. The working fluid in the vapor turbine cycle is water. The gas turbine cycle (GTC) electric generator produces 100kW of electric power For air use...
Gas enters an adiabatic turbine with enthalpy 3456 kJ/kg and velocity 100 m/s. It leaves the turbine with enthalpy 2675 kJ/kg and velocity 200 m/s. Had the flow been isentropic, the enthalpy would be 2315 k./kg at exit. Assume (V2s-V2). Determine the following: QUESTION 2 Total enthalpy at inlet in kJ/kg Enthalpy at exit in kJ/kg A 2392 B. 2695 C. 2461 D. 2335 Total isentropic enthalpy at exit in kJ/kg Total-to-total efficiency (%) The work done (in kJ/kg) E766...
3a. A gas-turbine power plant operates on the simple Brayton cycle between the pressure limits of 14.7 and 200 psia. Air enters the compressor at 77°F at a rate of 28 lbm/s and leaves at 750°F. Fuel is burned in the combustion chamber and the combustion gases enter the turbine at 2000°F. Combustion gases leave the turbine whose isentropic efficiency is 85 percent. Treating the combustion gases as air and using constant specific heats evaluated at 900°F, determine (a) the...
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