Question

A turbine produces shaft power from a gas that enters the turbine with a (static) temperature of 628 K, a velocity of 143 m/s and a stagnation pressure of 14 atm. The gas exits the turbine with a stagnation temperature of 275 K and a stagnation pressure of 0.95 atm. The gas passing through the turbine has a molecular weight of 16 and a specific heat ratio of 1.45. What is the stagnation temperature of the gas entering the turbine? Assuming the turbine is adiabatic, is it also reversible?

Answer 1

Step-by-step explanation:

The detailed step by step calculation and appropriate formula is as shown in the attached file.