Answer Happy

I need part B
Q2. (a) Gas (air) at a pressure of 7.4bar and a temperature of 285°C enters the stator of an axial flow compressor of constant mean diameter 1.7m. The mass flow rate is 340kg/s. The height of the stator blades at inlet is 80mm. The absolute flow angle at mid-blade height, measured with respect to the tangential direction, is 36° at inlet. The density of the air at the exit of the stator is 4.825kg/m². The flow can be assumed to be isentropic. i. Sketch the velocity triangle at stator inlet. [2 marks] ii. Calculate the axial, tangential and absolute air velocity at inlet to the stator. [4 marks] iii. Calculate the stagnation temperature at the exit of the stator. [1 marks] iv. Calculate the static temperature at the exit of the stator. [2 marks] v. Hence, calculate the absolute air velocity at the exit of the stator. [1 marks] (b) Flow exits the rotor of an LP compressor with an axial velocity of 180m/s and a relative flow angle of -30°. The LP turbine in the same engine rotates at 8250rpm. i. ii. Sketch the compressor rotor exit velocity triangle and calculate the absolute flow angle at this location if the mean diameter of the compressor is 0.45m. (5 marks] Sketch on a h-s (enthalpy-entropy) diagram the curves for both stagnation and static enthalpy through a single stage compressor. Label which part of the curves corresponds to the stator and which part of the curves corresponds to the rotor. [4 marks] iii. Indicate on your sketch in (ii) how the static enthalpy curves would be different if the compressor was isentropic. [1 mark]