Required information A gas-turbine power plant operates on a modified Brayton cycle shown in the figure with an overall pressure ratio of 8. Air enters the compressor at 0°C and 108 kPa. The maximum cycle temperature is 1500 K. The compressor and the turbines are isentropic. The high-pressure turbine develops just enough power to run the compressor. Assume constant properties for air at 300 K with cy0.718 kJ/kg-K, Cp 1.005 kJ/kg-K, R 0.287 kJ/kg-K. and k-1.4. Combustion chamber Compressor High-pressure turbine Determine the temperature and pressure at state 4, the exit of the high-pressure turbine. The temperature at state 4 is The pressure at state 4 is [ K. Low-pressure kPa.

Instead, assume variable specific heat A gas-turbine power plant operates on the simpleBrayton cycle between the pressure limits of 100 and 800 kPa.Air enters the compressor at 308C and leaves at 3308C at amass flow rate of 200 kg/s. The maximum cycle temperatureis 1400 K. During operation of the cycle, the net power outputis measured experimentally to be 60 MW. Assume constantproperties for air at 300 K with cv 5 0.718 kJ/kg·K, cp 51.005 kJ/kg·K, R 5 0.287 kJ/kg·K, k 5 l.4.(a) Sketch the T-s diagram for the cycle.(b) Determine the isentropic efficiency of the turbine forthese operating conditions.(c) Determine the cycle thermal efficiency.

Air enters the compressor of a gas turbine at 100 kPa and 25°C. pressure ratio 5 and For a maximum temperature of 850°C, the back work rate and thermal efficiency of the Brayton cycle Please specify.

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The ideal air-standard Brayton cycle operates with air entering the compressor at 95 kPa, 22°C. The pressure ratio rp is 6:1 and the air leaves the heat addition process at 1100 K. Determine the compressor work and the turbine work per unit mass flow, the cycle efficiency, the back work ratio, and compare the compressor exit temperature to the turbine exit temperature. Assume constant properties.

A gas-turbine power plant operates on a modified Brayton cycle shown in the figure with an overall pressure ratio of 8. Air enters the compressor at 0°C and 100 kPa. The maximum cycle temperature is 1500 K. The compres¬sor and the turbines are isentropic. The high-pressure turbine develops just enough power to run the compressor. Assume constant properties for air at 300 K as cv = 0.718 kJ/kg·K, cp = 1.005 kJ/kg·K, R = 0.287 kJ/kg·K, k = 1.4. (a) Sketch the T-s diagram for the cycle. Label the data states. (b) Determine the temperature and pressure at state 4, the exit of the high-pressure turbine. (c) If the net power output is 200 MW, determine the mass flow rate of the air into the compressor in kg/s.

3.     Assume an Otto cycle with compression ratio of CR = 9 : 1. The intake air is at 100kPa, 20oC, and the volume of the chamber is 500cm3 prior to the compression stroke. The temperature at the end of the adiabatic expansion is T4 = 800K. If air specific heat capacity at constant pressure of air at atmospheric pressure and room temperature is cp = 1.01KJ/kgK. Specific heat capacity at constant volume of air at atmospheric pressure and room temperature: cv = 0.718KJ/kgK.                   Calculate:       (i) the mass of the intake air;                                                (ii) the temperature T3;               (iii) the pressure p3;               (iv) the amount of heat added by burning fuel-air mixture;               (v) the thermal efficiency of the cycle;               (vi) the mean effective pressure (MEP).

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Two ideal Brayton cycles (see Figure below) have the same inlet temperature and the same maximum temperature of the turbine inlet. Brayton Cycle A has a higher compression ratio than Cycle B. Which of the following statements is true about the cycles? Cycle A has a higher thermal efficiency and Cycle B has a higher work net for a given mass flow rate.   Cycle B has a higher thermal efficiency and a higher work net for a given mass flow rate.   Since the temperatures are the same the efficiencies and work net are also the same.   Cycle A has a higher work net for a given mass flow rate and Cycle B has a higher thermal efficiency.   Cycle A has a higher thermal efficiency and a higher work net for a given mass flow rate.

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