Consider a Rankine cycle with reheat using water (steam) as the working fluid. Saturated liquid at 100C exits the condenser. The fluid exits the boiler at 6500C, 20000 kPa. The cycle uses a single reheater with operating pressure 200 kPa and exit temperature 5000C. The mass flow rate of water (steam) in the cycle is 40 kg/s. The operation of the turbines and pump are adiabatic and have isentropic efficiency 0.90. As usual, neglect pressure losses in piping, boiler, reheater, and condenser. Compute: quality at the exit of the high-pressure turbine.

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A Russian rocket engine (RD-110 with LOX-kerosene) consists of four thrust chambers supplied by a single turbopump. The exhaust from the turbine of the turbopump then is ducted to four vernier nozzles (which can be rotated to provide some control of the flight path). Using the information below, determine the thrust and mass flow rate of the four vernier gas nozzles. For individual thrust chambers (vacuum): F= 73.14 kN, c = 3279 m/sec Overall engine with verniers (vacuum): F= 297.93 kN, c = 3197 m/sec.