Calculate the maximum net power output and optimum pressure ratio for an air standard Brayton cycle with a compressor intake air mass flux of 4.5 kg/s at 1 atm and 21°C and turbine inlet air at 500 kPa and 900°C.

Calculate the maximum net power output and optimum pressure ratio for an air standard Brayton cycle with a compressor intake air mass flux of 4.5 kg/s at 1 atm and 21°C and turbine inlet air at 500 kPa and 900°C.

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

See similar textbooks

Similar questions

The standard Brayton air cycle has a compressor pressure ratio of 10. Air entering the compressor at p1 = 14.7 lbf/in., T1 = 70oF with a mass flow rate of 90,000 lb/hour. The entrance temperature of the turbine is 2200oR. Calculate the thermal efficiency and clean power generated, in horsepower (HP), if.
An air standard Carnot Cycle, is executed in a close system between the temperature limits of 350K and 1250K. The pressure before and after the isothermal compression are 150kPaa and 300kPa respectively. If the net work output per cycle is 0.80kJ, determine the following: (a) mass of air (kg), (b) thermal efficiency of the cycle (%), (c) Work of compression (kJ), (d) Work of Expansion (kJ), (e) heat added in the system (kJ) and (f) heat rejected by the system (kJ).
For an ideal cold air-standard Brayton cycle with a compressor inlet temperature of 300 K and a maximum cycle temperature of 1700 K, use Eq. in the picture to find the compressor pressure ratio that maximizes the net power output per unit mass flow. Assume k = 1.4
H.W2: An air-standard Carnot cycle is executed in a closed system between the temperature limits of 350 and 1200 K. The pressures before and after the isothermal compression are 150 and 300 kPa, respectively. If the net work output per cycle is 0.5 kJ, determine (a) the maximum pressure in the cycle, (b) the heat transfer to air, and (c) the mass of air. Assume variable specific heats for air. Answers: (a) 30,013 kPa, (b) 0.706 kJ, (c) 0.00296 kg
A turbojet-powered aircraft is flying at 220 m/s and 8000-m altitude, where the ambient temperature and pressure are 236K and 35kPa, respectively.The pressure ratio of the compressor is 6 and the turbine inlet temperaturer is 970k. Estimate the thrust developed by the engine when the air flow rate is 55kg/s. employ an air standard-cycle analysis using the constant-pressurree specific heat c_p and specific heat ratio γ for air and neglecting the fuel properties.
Provide the diagram, given, and step by step solution for below problem. An Otto cycle has an initial condition of 102 kPa and 32°C with compression ratio of 8.The maximum temperature of the cycle is 1400°C. Find the mean effective pressure in Kpa per kilogram of air. ANSWER: 524.66 kpa
A four-cylinder petrol engine has swept volume 1600 cm3 and Clearance volume for each cylinder is 50 cm3. Inlet condition are 24oC and 1 bar and the maximum cycle temperature is 1400oC, calculate the air standard cycle efficiency ( γγair= 1.4).
A gas turbine power plant operates on a simple thermodynamic cycle. The ambient conditionsare 100 kPa and 24 °C. The air at this condition enters the engine at 150 m/s whose diameteris 0.5 m. The pressure ratio across the compressor is 18 k and the temperature at the turbineinlet is 1400 K. Assuming ideal operation for all components and specific heats for air andproducts separately. In addition, neglect the mass of fuel burned. Do the followings:a. Choose the suitable thermodynamic cycleb.Draw pv and Ts diagram and label itCalculate the power required by the compressordDetermine the pressure and the temperature at the turbine exit,Compute the power produced by the turbinef.Available specific workg.The thermal efficiency
A gas turbine power plant operates on a simple thermodynamic cycle. The ambient conditionsare 100 kPa and 24 °C. The air at this condition enters the engine at 150 m/s whose diameteris 0.5 m. The pressure ratio across the compressor is 15, and the temperature at the turbineinlet is 1400 K. Assuming ideal operation for all components and specific heats for air andproducts separately. In addition, neglect the mass of fuel burned. Do the followings:a. Choose the suitable thermodynamic cycleb. Draw pv and Ts diagram and label itc. Calculate the power required by the compressord. Determine the pressure and the temperature at the turbine exit,e. Compute the power produced by the turbinef. Available specific workg. The thermal efficiency.
The pressure and temperature at the beginning of compression of an air-standard Diesel cycle are 90 kPa and 300 K, respectively. At the end of the heat addition, the pressure is 6821 kPa and the temperature is 1950 K. Determine the thermal efficiency of the cycle in %.
A gas turbine power plant operates on a simple thermodynamic cycle. The ambient conditionsare 100 kPa and 24 °C. The air at this condition enters the engine at 150 m/s whose diameteris 0.5 m. The pressure ratio across the compressor is 11, and the temperature at the turbineinlet is 1400 K. Assuming ideal operation for all components and specific heats for air andproducts separately. In addition, neglect the mass of fuel burned. Do the followings:a. Compute the power produced by the turbineb Available specific workc. The thermal efficiency.
A gas turbine power plant operates on a simple thermodynamic cycle. The ambient conditionsare 100 kPa and 24 °C. The air at this condition enters the engine at 150 m/s whose diameteris 0.5 m. The pressure ratio across the compressor is 11, and the temperature at the turbineinlet is 1400 K. Assuming ideal operation for all components and specific heats for air andproducts separately. In addition, neglect the mass of fuel burned. Do the followings:a. Choose the suitable thermodynamic cycleb. Draw pv and Ts diagram and label itc. Calculate the power required by the compressord. Determine the pressure and the temperature at the turbine exit,e. Compute the power produced by the turbinef. Available specific workg. The thermal efficiency. Explain with clear writing and units and diagram Also if you use tables and equation mention it with explanation