ExampledulmalekAir enters the compressor of an ideal air-standard Brayton cycle at 300K. the compressor ratio is 8and the turbine inlet temperature is 1300K. Determine:a) The gas temperature at the exit of the compressor and the turbine.b) The back work ratio.c) c) The thermal efficiency. Assume the compressor efficiency of 80 percent and the turbineefficiency of 85 percent.d) The thermal efficiency of the gas-turbine power plant if generation having an effectivenessof 80 percent is installed.Shay

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Answered: Example dulmalek Air enters the…

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 the air enters the compressor at 0.1 MPa, 25 ∘C. The pressure leaving the compressor is 1 MPa. and the maximum temperature in the cycle is 1200 ∘C. Assume a compressor efficiency of 80%, a turbine efficiency of 85%, and a pressure drop between the compressor and turbine of 30 kPa. Use the PG model. a) Determine compressor work (w_C), b) Determine the turbine work (w_T), c) Determine the cycle efficiency (n_th,Brayton).
Thermodynamics 1 Pls help me asap
A turbojet aircraft moving with a velocity of 790 ft/s at a runway where the pressure& temperature is found to be 14.7psi & 546R. The axial flow compressor provides apressure ratio of 14 to 1. Temperature at the turbine inlet is 2000R. The mass flowrate of airinside the engine is 133 lbm/s. Determine the following:a. T-S diagramb. Pressure & temperature at each statec. Thrust force (lbf)d. Propulsive power developed (BTU/min)e. Propulsive Efficiency
Performance of a compressor needs to be analyzed. Air enters the compressor of an air- standard Brayton cycle at 100 kPa, 300 K, with a volumetric flow rate of 5 m/s. The turbine inlet temperature is 1400 K. The efficiency of the compressor is 70%. For compressor pressure ratios of 8, (draw layout and T-s diagram) analyze: a The themal efficiency of the cycle. b. Outline and compare the effect on cycle efficiency, if compression ratio is increased beyond 8? Dodecane (C1H26) burns completely with 150% of theoretical air. Analyze its performance on the basis of Air-fuel ratio on a molar and mass basis.
Air enters the compressor at 80 kPa, 280 K and 60 m^3/s in a Brayton cycle with a regenerator with an efficiency of 0.85. The cycle maximum temperature is 2000 K, the pressure ratio is 18. Since turbine and compressor isentropic efficiencies are 93%: a) Net power (NW) b) The heat taken into the system in the combustion chamber (MW) c) Find the thermal efficiency of the cycle. Features for air: k=1,4, R=0,287 kJ/kg K, cp= 1,005 kJ/kg K
Please Provide correct solution, correct Method. No Missing steps / calculations. No Handwriting please
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Example-1 A Brayton cycle operates with air entering the compressor at 100 kPa, 25 °C, a pressure ratio of 6, and a turbine inlet temperature of 800 °C. Determine the compressor work input, the turbine work, the work ratio, the heat rejection and the cycle thermal efficiency for equal turbine and compressor efficiency of 100%; 80%; 70%; and 60%. T
FINAL DISCUSSION IN ME 3215 COMBUSTION ENGINEERING PROBLEM: 1. (a) Find the optimum pressure ratio for maximum specific work a non- ideal air Gas Turbine cycle. Initial Temperature and pressure at 27 °C and 104 kPa, respectively. Turbine inlet Temperature is 1,800 °C. n7 = 90 %, nc = 85 %. Take č, = 1.005 and k = 1.4 for air. kg k (b) Evaluate this maximum specific work for the cycle. (c) Prove that this specific cycle work is a maximum.
Air enters the compressor of an ideal air-standard Brayton cycle at 100 kPa, 300 K, with a mass flow rate of 5.81 kg/s. The compressor pressure ratio is 10. The turbine inlet temperature is 1400 K . a) the thermal efficiency of the cycle and b) the back work ratio
REFERENCE: FROM BOOK - ENGINEERING THERMOFLUIDS, M. MASSOUD
COMBUSTIONMENGINEERING PROBLEM: Rdirat www A regenerative-reheat gas turbine with intercooling between turbine stages is shown in figure. Air enters at 100 kPa, 300 K with a mass flow rate of 5.807 . The pressure ratio across the two-stage sec compressor is 10. The pressure ratio across the two-stage turbine is 10. The intercooler and reheater each operate at 300 kPa. At the inlets to the Turbine stages, the temperature is 1400 K. The temperature inlet to the second compressor stage is 300 K. The polytropic efficiency of each compressor and turbine stage is 80 %. The regenerator effectiveness is 80 %. č, = 1.005 , k = 1.4 Determine a. The Compressor work, in kg air k/ b. The Turbine work, in- kg air c. The Net cycle work, in- kg air d. The thermal efficiency, in percent e. The work ratio f. The The net power developed, in kW E- Draw the corresponding cycle diagram on the pv plane.

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