Title A simple, constant pressure gas turbine is designed for a pressure ratio of 5 to 1, and a turbine... Description A simple, constant pressure gas turbine is designed for a pressure ratio of 5 to 1, and a turbine inlet temperature of 550°C. The adiabatic efficiency of compressing is 80% and that of expansion 85%, and there is a pressure loss of 0.0343bar through the combustion chamber.   Calculate (a) the power per kg of air per sec. (b) the overall efficiency. Assuming the air to enter at 15°C and 1.01 bar. Take k = 1.4 and Cn = 1.047 for both air and combustion gases. Neglect the additional mass flow due to the fuel

In a C.I. engine working on the dual combustion cycle the compression ratio is 12.5:1. Air at 101.3kPa and 35°C is compressed adiabatically. Fuel is then added until the pressure reaches 4000kPa, then at constant pressure to a temperature of 1425°C. After adiabatic expansion to the initial volume exhaust takes place. Calculate: (a). work done/kg air (b). thermal efficiency

Just want to compare against my answers

5. (a) If the compression ratio of an engine working on Otto cycle isIncreased from 5 to 7, find the percentage increase in thermalefficiency. (b) Derive an expression for thermal efficiency of ideal Brayton cycle.(c) In an engine working on the ideal Otto cycle, the pressure and temperature at the beginning of compression are 100 kPa and 40 °C respectively. The ratio of specific heat capacities is 1.4. If the airstandard efficiency of the engine is 50%, determine(i) The compression ratio. (ii) The pressure and temperature at the end of adiabaticcompression.   (6a) Explain and discuss in your own words, the following three concepts incombustion: stoichiometric mixture of air and fuel, weak mixture and richmixture. Explain their importance in combustion applications.(6b) A gas fuel has the following volumetric composition:Propane C3H8: 73 %Butane C4H10: 5 %Ethane, C2H6: 3%Nitrogen N2: 19%(i) Write out the complete combustion equations for all the combustible constituents individually.…