Problem 2. Consider an ideal gas-turbine cycle with two stages of compression and two stages of expansion. The pressure ratio Regenerator across each stage of the compressor and turbine is 4, total pressure ratio is 14. The working fluid is air. The air enters the both stages of the Combustion Reheater chamber Compressor Compressor Turbine I Turbine II compressor at 300 K and the both stages of the turbine at 1400 K. Assume both the compressor have an isentropic efficiency of 85 percent and both the turbine have an isentropic efficiency of 90 percent. The temperature of entering air to the combustion chamber is T5 = 869 K. Assuming constant specific heats, Intercooler Show the cycle on T-s diagram. b. Determine the regenerator effectiveness. Determine the back work of the cycle. d. Determine the thermal efficiency. e. Calculate the mass flow rate of the air circulating in the cycle for the power plant to produce 16 MW of net power. a. с.

Problem 2. Consider an ideal gas-turbine cycle with two stages of compression and two stages of expansion. The pressure ratio Regenerator across each stage of the compressor and turbine is 4, total pressure ratio is 14. The working fluid is air. The air enters the both stages of the Combustion Reheater chamber Compressor Compressor Turbine I Turbine II compressor at 300 K and the both stages of the turbine at 1400 K. Assume both the compressor have an isentropic efficiency of 85 percent and both the turbine have an isentropic efficiency of 90 percent. The temperature of entering air to the combustion chamber is T5 = 869 K. Assuming constant specific heats, Intercooler Show the cycle on T-s diagram. b. Determine the regenerator effectiveness. Determine the back work of the cycle. d. Determine the thermal efficiency. e. Calculate the mass flow rate of the air circulating in the cycle for the power plant to produce 16 MW of net power. a. с.

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

8.. Nitrogen gas is compressed . Pressure rises from 100 kPa to 1500 kPa. Initial temperature of 25 deg C. The required mass flow is 1000 kg/hr. Would you recommend single stage or multi-stage compression? Justify your recommendation with appropriate calculations. For Nitrogen, R = 0.297 kJ/ kg K, g = 1.4, r = 1.25kg/m3, µ = 17.4 µPa s, cp = 1.039 kJ/kg K
Combustion gases with k=1.35, Cp =1107 J/(kg.K) and R= 287 J/(kg.K) flow at stagnation pressure and stagnation temperature of 390kPa and 1150 K respectively, flow through a 90o IFR turbine to an exit static pressure of 100 kPa. The total to static efficiency is 80% and the flow leaves the stator choked (Mach Number=1). The relative velocity at the inlet to the rotor is radial and the flow leaves the turbine without a swirl. Find (a) the work delivered per unit flow rate, (b) the impeller tip velocity and (c) the flow angle at the inlet to the rotor.
Draw schematic diagrams of a gas turbine system used for i. generating electricity with irreversible (actual) single stage compression, ii. two stages of irreversible expansion with reheat, and iii. a regenerator. Specify the relevant corner points of the process.
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.
3. Steam enters the turbine at the rate of 1.5 kg/s with enthalpy of 2300 kJ/kg and exhaust enthalpy of 1200 kJ/kg. Steam is extracted from the turbine at a rate of 0.87 kg/s for heating purposes with enthalpy of 2570 kJ/kg. What is the turbine work, in HP? draw a diagram and show full solution
Helium gas is used as the intermediate fluid in an ideal Brayton cycle with a regenerator. Helium emerges from the turbine at a temperature of 800 K and a pressure of 100 kPa. At the compressor outlet, the pressure of helium is 500 kPa and its temperature is 450 K. Since the efficiency of the regenerator is 80 percent; a) Compressor and turbine inlet temperatures, b) qg and q of the amount
at a stage in a reaction turbine, the mean blade ring diameter is 1 m. the turbine runs at 3000 rpm. the blades are designed for a degree of reaction of 50% with exit angles of 30° and inlet angles of 50°. the turbine is supplied with a steam at 10000 kglh and the stage efficiency is 85%. determine (a) power output of the stage, (b) specific enthalpy drop in kj/kg, (c) percentage increase in relative velocity of steam over moving blades, (d) the specific steam consumption
A turbine is driven by a system that enters the turbine at the ff. conditions: 500 kg/h, 44 atm, 450 deg C, 60 m/s linear speed. The steam exits at a point five meters below the inlet stream of the turbine with the following conditions: atmospheric pressure, 360 m/s speed. 70,000 W of shaft work is delivered by the turbine while 104 kilocalories/h heat is lost. Why is expansion work 0 and why cannot the flow work be calculated?
Water Vapor pressure 8 MPa and 350 in an adiabatic turbineIt enters at a temperature of oC and at a pressure of 750 kPacomes out. Reversible The amount of work done by the unit mass of steam for the processcalculate.
A turbine is driven by a system that enters the turbine at the ff. conditions: 500 kg/h, 44 atm, 450 deg C, 60 m/s linear speed. The steam exits at a point five meters below the inlet stream of the turbine with the following conditions: atmospheric pressure, 360 m/s speed. 70,000 W of shaft work is delivered by the turbine while 104 kilocalories/h heat is lost. Here are the questions to be answered: 1. Why is the value of Wexp 0? (Explain) 2. Given the above values, can you calculate the Wflow? (Yes/No)
For an adiabatic flow of Argon (k=1.667) as a perfect gas, the maximum to critical velocity ratio will be ______.
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 o the isentropic efficiencies of the compressor, H. P. turbine, L. P. turbine are 0.8, 0.83 and 0.85 respectively and the mechanical efficiency of both shafts is 98 %. Sketch the process on the T-s diagram i. Calculate the pressure between turbine stages when the air intake conditions are 1.01 bar and 25 oC. ii. Calculate also the thermal efficiency and the shaft power when the mass flow is 60 kg/s. NB: Neglect kinetic energy changes and the pressure loss in combustion.