Massachusetts Institute of Technology DEPARTMENT OF MECHANICAL ENGINEERING Center for Ocean Engineering 2 611 2 612 Ship Power and Propulsion Problem Set 6 Due December 5 2006 1 Describe the advantages and disadvantages of using a Gas Turbine vs a Diesel Engine 2 Draw a T S diagram for an inter cooled regenerative Brayton Cycle Label the points and explain in words each portion of the cycle Mark on your diagram the area where heat is transferred into the system and where it leaves the system 3 A simple closed cycle Brayton engine operates with air as the working fluid The conditions at the design point are as follows compressor inlet temperature T1 25 C 300 K compressor pressure ratio p2 p1 11 compressor isentropic efficiency c 85 turbine inlet temperature T3 1425 C 1698 K turbine isentropic efficiency t 92 pressure loss p p 6 mass flow rate of air through engine 60 kg s Determine a T2 T4 using ideal gas properties b the ratio of compressor power turbine power c the net power of the Brayton Cycle kW d the heat transfer rate kW between T3 T4 e the thermal efficiency of the cycle Assume that air is an ideal gas with constant specific heats cp 1 00 kJ kg K 1 4 4 A design engineer recommends adding a regenerator with an efficiency of 90 to the Brayton engine in Question 3 Use the design conditions from 3 Determine a the heat transfer rate kW b the thermal efficiency of the cycle c Draw the T S Diagram highlighting the range which the heat transfer takes place 5 An intercooled recuperative gas turbine has the following design conditions Compressor inlet temperature T1 T3 310K Compressor pressure ratio p2 p1 p4 p3 5 1350K Turbine inlet temperature T6 Pressure Loss p p 10 Compressor polytropic efficiency pc 85 Turbine polytropic efficiency pt 90 Regenerator effectiveness T5 T4 T7 T4 0 85 92 Combustion efficiency comb Determine a the fuel air ratio mf ma b the specific power in kW kg per sec i e net power mass flow rate of air c the specific fuel consumption in kg of fuel per kW hour d Calculate the required cross sectional area for the inlet duct if the inlet duct velocity is 25 m s for the turbine Assume that the ambient air outside the ship is at 1 bar and 298K Assume that the working fluids are air a 1 4 and cpa 1 005 kJ kg K for the compressor and the combustion products p 1 33 and cpp 1 130 kJ kg K for the turbine The fuel for the combustor is at 25 C and the heating value LHV is 43 000 kJ kg 6 A simple cycle 18 MW gas turbine has a maximum turbine entry temperature of 1100 C and a max pressure after the compressor of 2 2MPa The maximum pressure in the combustion chamber is 500kPa Pressure at the intake and temperature is 110kPa and 30 C Additionally a recuperator with an effectiveness of 85 has been installed Using an isentropic index of 1 4 throughout the turbine determine a power required for compression and polytropic efficiency of the compression process b power delivered during expansion and polytropic efficiency of the expansion process c amount of heat released in combustion chamber and fuel mass flow d brake power and over all efficiency Assume gas constant 0 287 kJ kgK Specific heat at constant pressure 1 0 kJ kgK LHV of fuel 430000 kJ kg nc 1 4 irreversible loss for compression nT 1 33 irreversible loss for expansion Hint Use the example in chapter 8 and figure 8 8 of the text 7 A DC motor with a speed of 180 rpm current of 10 amps resistance of 2 ohms has 400 volts applied Determine the magnetic flux and torque Assume Ke 5 and Km 30 8 The rotor of a certain 25 hp 6 pole 60Hz induction motor has an equivalent resistance and reactance per phase is 0 1 and 0 5 respectively The blocked rotor voltage phase is 150 V If the rotor is turning at 1164 rpm determine a b c d e f synchronous speed slip rotor impedance rotor current rotor current is changing the shaft load resulted in 1 25 slip speed for condition in e