A gas turbine unit has a pressure ratio of 6/1 and a maximum cycle temperature of 600°C. The isentropic efficiencies of the compressor and turbine are 0.85 and 0.82 respectively. Calculate the power output in KW of an electric generator geared to the turbine when air enters the compressor at 15°C and a rate of 15 kg/s. For the compression process cp 1.0005 KJ/kg-K and k = 1.4, for the expansion process cp = 1.11 KJ/kg-K and k = 1.333. %3D

A gas turbine unit has a pressure ratio of 6/1 and a maximum cycle temperature of 600°C. The isentropic efficiencies of the compressor and turbine are 0.85 and 0.82 respectively. Calculate the power output in KW of an electric generator geared to the turbine when air enters the compressor at 15°C and a rate of 15 kg/s. For the compression process cp 1.0005 KJ/kg-K and k = 1.4, for the expansion process cp = 1.11 KJ/kg-K and k = 1.333. %3D

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

Air is used as the working fluid in a simple ideal Brayton cycle that has a pressure ratio of 12, a compressor inlet temperature of 300 K, and a turbine inlet temperature of 1000 K. Determine the required mass flow rate of air for a net power output of 70 MW, assuming both the compressor and the turbine have an isentropic efficiency of 100 percent.
The temperature of air at the beginning of compression in an Otto cycle is 310 K and maximum temperature in the cycle is 2200 K. If the pressure at the end of adiabatic compression is 15 times that at the start, determine the compression ratio, thermal efficiency, and work done. Take k for air = 1.4.
In an air standard gas turbine cycle, air at 14.5 psia and 70 F is first compressed to 80 psia in a compressor of 82 percent efficiency. The hot air leaving the combustion chamber at 1250 F is expanded back to 14.5 psia in a turbine of 85 percent efficiency. If a regenerator is inserted into the cycle to heat the air leaving the compressor to 650 F, determine the thermal efficiency of the cycle and the effectiveness of the regenerator.
Consider a regenerative gas-turbine power plant with two stages of compression and two stages of expansion. The overall pressure ratio of the cycle is 9. The air enters each stage of the compressor at 300 K and each stage of the turbine at 1200 K. Accounting for the variation of specific heats with temperature, determine the minimum mass flow rate of air needed to develop a net power output of 110 MW.
Air is used as the working fluid in a simple ideal Brayton cycle that has a pressure ratio of 12, a compressor inlet temperature of 300 K, and a turbine inlet temperature of 1000 K. Determine the required mass flow rate of air for a net power output of 70 MW, assuming both the compressor and the turbine have an isentropic efficiency of 85 percent. Assume constant specific heats at room temperature.
Consider an ideal gas-turbine cycle with two stages of compression and two stages of expansion. The pressure ratio across each stage of the compressor and turbine is 3. The air enters each stage of the compressor at 300 K and each stage of the turbine at 1200 K. Determine the back work ratio and the thermal efficiency of the cycle, assuming no regenerator is used.
A gas-turbine-powered Plymouth car built in 1960 had a turbine inlet temperature of 1700°F, a pressure ratio of 4, and a regenerator effectiveness of 0.9. Using isentropic efficiencies of 80 percent for both the compressor and the turbine, determine the thermal efficiency of this car. Also, determine the mass flow rate of air for a net power output of 130 hp. Assume the ambient air to be at 510 R and 14.5 psia.
How do the inefficiencies of the turbine and the compressor affect the thermal efficiency of a gas-turbine engine?
A Diesel cycle has a compression ratio of 22 and begins its compression at 83 kPa and 15°C. The maximum cycle temperature is 1200°C. Utilize air-standard assumptions. The properties of air at room temperature are R = 0.287 kPa·m3/kg·K, cp = 1.005 kJ/kg·K, cv = 0.718 kJ/kg·K, and k = 1.4. Determine the thermal efficiency of this cycle using constant specific heats at room temperature. The thermal efficiency of this cycle (in decimal fraction)
An ideal diesel engine has a compression ratio of 20 and uses air as the working fluid. The state of air at the beginning of the compression process is 95 kPa and 20°C. If the maximum temperature in the cycle is not to exceed 2200 K, determine the net work of the system as a function of compression ratio, r.
A spark-ignition engine has a compression ratio of 10, an isentropic compression efficiency of 85 percent, and an isentropic expansion efficiency of 90 percent. At the beginning of the compression, the air in the cylinder is at 13 psia and 60°F. The maximum gas temperature is found to be 2300°F by measurement. Determine the heat supplied per unit mass, the thermal efficiency, and the mean effective pressure of this engine when modeled with the Otto cycle. Use constant specific heats at room temperature. The properties of air at room temperature are R = 0.3704 psia·ft3/lbm·R, cp = 0.240 Btu/lbm·R, cv = 0.171 Btu/lbm·R, and k = 1.4. Question: The heat supplied per unit mass is ___________.Btu/lbm. The thermal efficiency is_________________%. The mean effective pressure is________________.psia.
The initial pressure and temperature of air in an Otto cycle engine during compression are 90 kPa and 12oC. Determine the maximum pressure occurring in the cycle if the initial and final temperature during heat addition process are 350 oC and 1250 oC, and the compression ratio is 6.