List of top Propulsion Questions on Axial Turbines asked in GATE AE

A gas mixture at a pressure of \(800\) kPa and a density of \(5\) kg/m\(^3\) enters a turbine stage. The temperature of the gas at the nozzle exit and the stage exit are \(790\) K and \(750\) K, respectively. Assume the specific heats are constant for the gas mixture in the range of temperatures considered. The specific heat at constant pressure is \(0.72\) kJ/kg-K and the ratio of specific heats is \(1.33\). The value of the degree of reaction of the turbine stage is _______ (rounded off to 2 decimal places).
A single-stage axial turbine has a mean blade speed of 340 m/s. Rotor inlet and exit blade angles are 21° and 55°, respectively. Density at rotor inlet is 0.9 kg/m³, annulus area = 0.08 m², degree of reaction = 0.4. Find the mass flow rate (round off to 2 decimals).