The Taurus 60 gas turbine in the West Campus Steam Plant has a compressor pressure ratio of 12.2 and a mass flow rate of 21.5 kg/s. The combustor adds 18 MW of heat to the cycle, and the isentropic efficiency of the compressor and turbine are 0.85 and 0.9, respectively. Assuming an inlet condition of T1-278 K and P1-95,900 Pa to do an air- standard cycle analysis to calculate the following. Use cp-1001 J/kg-K and y=1.4. a) Temperature and pressure at all four state points b) Power produced by the engine c) Engine thermal efficiency

The Taurus 60 gas turbine in the West Campus Steam Plant has a compressor pressure ratio of 12.2 and a mass flow rate of 21.5 kg/s. The combustor adds 18 MW of heat to the cycle, and the isentropic efficiency of the compressor and turbine are 0.85 and 0.9, respectively. Assuming an inlet condition of T1-278 K and P1-95,900 Pa to do an air- standard cycle analysis to calculate the following. Use cp-1001 J/kg-K and y=1.4. a) Temperature and pressure at all four state points b) Power produced by the engine c) Engine thermal efficiency

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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In an air standard brayton cycle, air enters the compressor at 27 degree C and 100 kPa. The pressure ratio is 10, and the maximum allowable temperature is 1350 K. the compressor and turbine efficiencies are 85%, and pressure drops 27 kPa between the compressor discharge and turbine inlet. Determine the pressure and temperature at each state in the cycle, the compressor and turbine work, and the cycle thermal efficiency. Please show the PV and TS diagram. Please show complete formulas and solutions.
https://docs.google.com/forms/d/e/1FAlpQLSetVOr_5EjfFBSr Q1/Calculate the power in kilowatts of the gas turbine power plant has a greatest temperature of 700°C and a pressure ratio of 10. The isentropic efficiencies of the turbine and compressor are 0.85 and 0.82 respectively. The mass flow rate of the air that inlet to the compressor is 15 kg/s at 15 °C. At the expansion process take C,= 1.11 kJ/kg-K, y=1.333, and at the compression process take c,= 1.005 kJ/kg-K, and y =1.4 1025.73 kW O 2085.71 kW 1095.72 kW O 2045.74 kW Activate Windo Go to Settings to a earch 立

Required information Problem 09.015 - 3-Step Air-Standard Cycle with Constant Specific Heats - DEPENDENT MULTI-PART PROBLEM - ASSIGN ALL PARTS An air-standard cycle with constant specific heats at room temperature is executed in a closed system with 0.003 kg of air and consists of the following three processes: 1-2 v= Constant heat addition from 95 kPa and 17°C to 380 kPa 2-3 Isentropic expansion to 95 kPa 3-1 P=Constant heat rejection to initial state The properties of air at room temperature are cp=1.005 kJ/kg-K, cv=0.718 kJ/kg-K, and k=1.4. Problem 09.015.c - Cycle Efficiency for Constant Heat Capacity Air-Standard Cycle Determine the thermal efficiency. The thermal efficiency is %.
Required information Problem 09.015 - 3-Step Air-Standard Cycle with Constant Specific Heats - DEPENDENT MULTI-PART PROBLEM - ASSIGN ALL PARTS An air-standard cycle with constant specific heats at room temperature is executed in a closed system with 0.003 kg of air and consists of the following three processes: 1-2 v= Constant heat addition from 95 kPa and 17°C to 380 kPa 2-3 Isentropic expansion to 95 kPa 3-1 P = Constant heat rejection to initial state The properties of air at room temperature are cp = 1.005 kJ/kg-K, cy= 0.718 kJ/kg-K, and k = 1.4. Problem 09.015.b - Net Work for Constant Heat Capacity Air-Standard Cycle Calculate the net work per cycle, in kJ. (You must provide an answer before moving on to the next part.) The net work per cycle is kJ.
28. In a marine gas turbine unit a high-pressure stage turbine drives the compressor, and a low-pressure stage turbine drives the propeller through suitable gearing. The overall pressure ratio is 4: 1, and the maximum temperature is 650°C. The isentropic efficiencies of the compressor, H.P. turbine, and L.P. turbine are 0.8, 0.83, and 0.85 respectively, and the mechanical efficiency of both shafts is 98%. Calculate the pressure between turbine stages when the air intake conditions are 1.01 bar and 25°C. Calculate also the thermal efficiency and the shaft power when the mass flow is 60 kg/s. Neglect kinetic energy changes, and pressure [Ans. 1.57 bar; 14.9% ; 4560 kW) loss in combustion.
! Required information Problem 09.034 - Ideal Otto Cycle with Variable Specific Heats - DEPENDENT MULTI-PART PROBLEM - ASSIGN ALL PARTS An ideal Otto cycle has a compression ratio of 8. At the beginning of the compression process, air is at 95 kPa and 27°C, and 760 kJ/kg of heat is transferred to air during the constant-volume heat-addition process. Take into account the variation of specific heats with temperature. The gas constant of air is R = 0.287 kJ/kg-K. Problem 09.034.a - State After Heat Addition in Variable Heat Capacity Ideal Otto Cycle Determine the pressure and temperature at the end of the heat-addition process. (You must provide an answer before moving on to the next part.) The pressure at the end of the heat-addition process is 3915.8 kPa. The temperature at the end of the heat-addition process is 1647.7 K.
! Required information Problem 09.034 - Ideal Otto Cycle with Variable Specific Heats - DEPENDENT MULTI-PART PROBLEM - ASSIGN ALL PARTS An ideal Otto cycle has a compression ratio of 8. At the beginning of the compression process, air is at 95 kPa and 27°C, and 760 kJ/kg of heat is transferred to air during the constant-volume heat-addition process. Take into account the variation of specific heats with temperature. The gas constant of air is R = 0.287 kJ/kg-K. Problem 09.034.c - Thermal Efficiency in Variable Heat Capacity Ideal Otto Cycle Determine the thermal efficiency. (You must provide an answer before moving on to the next part.) The thermal efficiency is 54.3 %.
Air is used as the working fluid in a Brayton cycle with a regenerator. The pressure ratio of the cycle is 8, the compressor inlet temperature is 300 K, the turbine inlet temperature is 1800 K. The efficiency of the regenerator is 75 percent. If the isentropic efficiency of the compressor and turbine is 80 percent, since 60 MW net power is obtained from the cycle, determine the thermal efficiency of the cycle and the required air mass flow rate. only hand written please no chat GPT
The adiabatic efficiencies of the compressor and turbine used in an air-standard Brayton cycle are 85% and 90%, respectively. If the cycle operates between 14.7 and 55 psia and if the maximum and minimum temperatures are 1500 F and 80 F, respectively, compute the thermal efficiency of the cycle. Assume constant specific heats.
Consider an air-standard Otto cycle that has a compression ratio of 8 and a heat addition of 1330 kJ/kg. If the pressure and temperature at the beginning of the compression process are 0.1 MPa and 70 °C, determine Match each item to a choice: Q the maximum pressure for the cycle, the net work output, in kJ/kg, the maximum temperature for the cycle the mean effective pressure,
a turbojet aircraft is travelling at a speed of 925 kilometres per hour in atmospheric conditions of 0.45 bars and -26 degree centigrade. the compression ratio used is 8 and the air mass flow rate is 45 kg/sec and the allowable maximum cycle temperature is 827 degree centigrade. the entry duct, compressor, gas turbine and jet pipe stagnation isentropic efficiency are 0.9, 0.85, 0.89 and 0.9. the mechanical efficiency of the drive is 0.98 and the combustion efficiency is 0.99. assuming a convergent propeller nozzle a loss of stagnation pressure in the combustion chamber is 0.2 bars and fuel of cv 43.3 mj/kg is used. calculate:- i) required nozzle area ii) net thrust developed iii) specific fuel consumption for gases in turbine and nozzle take υ = 1.333, cp = 1.15 kj/kg-k and for combustion process take equivalent cp = 1.15 kj/kg-k.
QUESTION 4 In an air-standard Brayton cycle air enters the compressor at 101.325 kPa and 27°C. Determine the network if the maximum temperature is 1000-C and the pressure ratio is 9. O 331.47 kj/kg O 456.88 kJ/kg O 421.56 k/kg O 301.74 kj/kg