Question

Analyze a Gas turbine engine at a design speed under the following data employing a separate power turbine, heat exchanger, reheater and intercooler between two-stage compression. Efficiency of compression in each stage: 85% Isentropic efficiency of compressor turbine: 90% Isentropic efficiency of power turbine: 85% Transmission efficiency: 98% Pressure ratio in each stage of compression: 2:1 Pressure loss in intercooler: 0.07 bar Temperature after intercooling: 300 K Thermal ratio of heat exchanger: 0.75 Pressure loss in combustion chamber: 0.15bar Combustion efficiency of reheater: 98% Maximum cycle temperature: 1000 K Temperature after reheating: 1000 K Air mass flow: 25 kg/s Ambient air temperature: 15 °C Ambient air pressure: 1 barTake the calorific value of fuel as 42 MJ/kg and pressure loss in each side of heat exchanger as 0.1 bar. Find the net power output overall thermal efficiency, specific fuel consumption. Neglect the kinetic energy of the gases leaving the system

Answer #1

It is desired to an alyze the performacne of a gas turbine
engine operating on a Bratyon cycle with a free power turbine. The
engine is under test at static conditions with an ambient
temperature of 20'C and pressure of 1atm. The pressure ratio of the
compressor is 5. The engine burnsmethane fuel with a heat of
combustion of 50MJ/kg. The air to fuel ratio (AF) is 45. Assume the
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NO INTERPOLATION REQUIRED
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