Thermo 2 H.W

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Engineering

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Provide a schematic diagram (sketch) of the problem configuration (if applicable). Include a schematic P-v (or T-s) diagram of the cycle for each problem. Every numerical calculation must be preceded by the appropriate equation. Do not forget units/dimensions. Incorrect units/dimensions WILL result in reduced points (during grading) for the solution.

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EGR 432 : Engineering Thermo-Fluids II Fall 2018 Homework 2 Due date: 9/27/2018 (Thursday) (To be submitted at the beginning of the class meeting) 1) A four-cylinder, four-stroke spark ignition engine operating on the ideal Otto cycle takes in air at 110 kPa and 20 oC at the beginning of the compression stroke. For each cylinder, the clearance volume is 180 cm3 and the displacement volume is 1530 cm3. Operating conditions dictate that the maximum temperature during the cycle does not exceed 1150 oC. Using cold-air standard assumptions, calculate the a) b) c) d) e) f) Pressure, temperature and specific volume at the end of each process Heat added during each cycle (kJ) Net work output for each cycle (kJ) Thermal efficiency of the cycle Mean effective pressure (kPa) Total power output when the engine is operating at 3600 RPM. 2) An ideal Diesel cycle is operating with a compression ratio of 18 and a cutoff ratio of 2.1. At the beginning of the compression stroke, the flow conditions are 16 psia and 80 oF. Using variable specific heats, calculate the a) b) c) d) e) f) Pressure, temperature and specific volume at the end of each process Heat added during the heating process (Btu/lbm) Heat removed during the heat rejection process (Btu/lbm) Net work output from the cycle (Btu/lbm) Mean effective pressure (psia) Thermal efficiency of the cycle 3) A gas turbine power plant operating on an ideal Brayton cycle has a pressure ratio of 14.5. At the compressor inlet, the gas pressure and temperature are 105 kPa and 24 oC, respectively. The gas temperature at the turbine inlet is 1250 oC. The isentropic efficiency of the compressor is 88% and the isentropic turbine efficiency is 91%. Use cold air-standard assumptions. If the mass flow rate is 3.6 kg/sec, calculate the a) b) c) d) e) Temperatures at the compressor exit and turbine exit Heat addition and removal rates during the cycle (kW) Back work ratio Net power output (kW) Thermal efficiency of the cycle 4) A pure jet engine propels an aircraft at 480 mph at an altitude where the pressure and temperature of atmospheric air are 6.2 psia and -38 oF, respectively. The compressor pressure ratio is 11.8. The engine inlet has a diameter of 54 inches. Operational considerations dictate that the maximum temperature of the working fluid entering the turbine be restricted to 2400 oF. Use cold air-standard assumptions. Calculate the a) Velocity of gas flow at the nozzle exit b) Thrust produced by the engine (lbf) c) Propulsive efficiency of the cycle Note: Provide a schematic diagram (sketch) of the problem configuration (if applicable). Include a schematic P-v (or T-s) diagram of the cycle for each problem. Every numerical calculation must be preceded by the appropriate equation. Do not forget units/dimensions. Incorrect units/dimensions WILL result in reduced points (during grading) for the solution.
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hello, kindly find the attached documents. You can use either the pdf or the word document.

Running Head: ENGINEERING THERMO-FLUIDS 11

Engineering Thermo-Fluids 11
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Anonymous
Excellent! Definitely coming back for more study materials.

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