Chapter 4, Problem 4.77P

A modern jet engine has a temperature after combustions of about $1500\text{ K}$ at $\text{32}00\text{kPa}$ as it enters the turbine section (see state 3, Fig, P4.77). The compressor inlet is at $80\text{kPa},260\text{ K}$ (state 1) and the outlet (state 2) is at $3300\text{kPa},780\text{ K}$ ; the turbine outlet (state 4) into the nozzle is at $\text{4}00\text{kPa},\text{ 9}00\text{ K}$ and the nozzle exit (state 5) is at $\text{8}0\text{ kPa, 64}0\text{ K}$ Neglect any heat transfer and neglect kinetic energy except out of the nozzle. Find the compressor and turbine specific work terms and the nozzle exit velocity.