solve by showing and explaining each step 2. The steam turbine has inlet pressure and temperature of 100 bar and 520C respectively.P₁ = 100 barT₁ = 520°CPower outTurbineP₂ = 0.08 barx2=90%-2CondenserCoolingwater in at 20°CCoolingwater out at 35°Ca.+3 P3=0.08 barSaturated liquidDetermine the mass flow rate of steam if the turbine deliver 21.8 MW power. You can ignorethe KE and PE changes. Assume well insulated turbine.b. Mass flow rate of cooling water. Assume that cooling water inlet and outlet takes place atsaturation liquid stage and at the mentioned temperatures.C.Temperature at the exit of the heat exchanger T3

First find the enthalpy of state 1,2 and 3. You can use steam tablea. Mass flow rate of…

Answered: 2. The steam turbine has inlet pressure…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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A turbine is driven by a system that enters the turbine at the ff. conditions: 500 kg/h, 44 atm, 450 deg C, 60 m/s linear speed. The steam exits at a point five meters below the inlet stream of the turbine with the following conditions: atmospheric pressure, 360 m/s speed. 70,000 W of shaft work is delivered by the turbine while 104 kilocalories/h heat is lost. Here are the questions to be answered: 1. Why is the value of Wexp 0? (Explain) 2. Given the above values, can you calculate the Wflow? (Yes/No)
In a marine gas turbine unit, a high-pressure stage turbine drives the compressor and a low-pressure stage turbine drives the propeller through suitable gearing. The overall pressure ratio is 4/1 and the maximum temperature is 650 oC. the isentropic efficiencies of the compressor, H. P. turbine, L. P. turbine are 0.8, 0.83 and 0.85 respectively and the mechanical efficiency of both shafts is 98 %. Sketch the process on the T-s diagram Calculate the pressure between turbine stages when the air intake conditions are 1.01 bar and 25 oC. Calculate also the thermal efficiency and the shaft power when the mass flow is 60 kg/s. NB: Neglect kinetic energy changes and the pressure loss in combustion.
A turbojet aircraft moving with a velocity of 790 ft/s at a runway where the pressure& temperature is found to be 14.7psi & 546R. The axial flow compressor provides apressure ratio of 14 to 1. Temperature at the turbine inlet is 2000R. The mass flowrate of airinside the engine is 133 lbm/s. Determine the following:a. T-S diagramb. Pressure & temperature at each statec. Thrust force (lbf)d. Propulsive power developed (BTU/min)e. Propulsive Efficiency
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5. A single-acting, twin-cylinder 15.25 x 15.25-cm compressor receives saturated ammonia vapor at - 18 degrees * C and discharges it at 1514.3 kPa. The system is used to produce ice at a final temperature of - 10 degrees * C from water at 27 degrees * C . The compressor runs at 450 rpm with an actual volumetric efficiency of 78%. Assume compression and mechanical efficiencies to be 82% and 88%, respectively. Calculate the following: (a) capacity of the system in tons of refrigeration, (b) brake hp required by the compressor, (c) tons of ice produced per day if compressor runs only 20 hours a day. Assume losses to be 10% of the refrigeration required to produce the ice, and (d) ideal and actual COP.
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A four-stage compressor works between limits of 1 bar and 120 bar. The indexof compression in each stage is 1.25, the temperature at the start ofcompression in each stage is 30 ˚C, and the intermediate pressure areselected such that work is divided equally among the stages. If the clearanceis negligible: Calculate: 1. the volume of free air delivered per kilowatt-hour at 1.013 bar and 20 ˚C2. isothermal work input 3. isothermal efficiency.

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