DieselShip's Online Content Library

Q10. Air enters the compressor of a simple gas turbine plant at a pressure and temperature of 1.03 bar and 305 K respectively. It is compressed to 6.18 bar with an isentropic efficiency of 83%.

The hot gases leave the combustion chamber and enter the turbine at a pressure of 6.18 bar and a temperature of 1210 K.

The turbine exhausts at a pressure of 1.03 bar and a temperature of 805 K.

The fuel air ratio is 0.0125.

(a) Sketch the cycle on a Temperature-specific entropy diagram.

(b) Calculate EACH of the following:

(i) The isentropic efficiency of the turbine

(ii) The network output per kg of exhaust gas

(iii) The thermal efficiency of the cycle.

Note: For air: γ = 1.4 and C_p = 1.005 kJ/kgK

For the hot gas: γ = 1.33 and C_p = 1.15 kJ/kgK