For a specified pressure ratio, why does multistage compression with intercooling decrease the compressor work, and multistage expansion with reheating increase the turbine work?
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For a specified pressure ratio, why does multistage compression with intercooling decrease the compressor work, and multistage expansion with reheating increase the turbine work?
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- Welded ______sealed compressors are normally used in household refrigerators.2. A freezer of 20 TR capacity has evaporator and condenser temperatures of 30°C and 25°C respectively. The refrigerant R-12 is sub-cooled by 4°C before it enters the expansion valve and is superheated by 5°C before leaving the evaporator. The compression is isentropic and the valve throttling and clearance are to be neglected. If a six-cylinder, single acting compressor with stroke equal to bore running at 1000 r.p.m. is used, determine: A- C.O.P. of the refrigerating system, B- Mass of refrigerant to be circulated per min, C- Theoretical piston displacement per minute and D- Theoretical bore and stroke of the compressor.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.
- on (sat vapor) o, Py 0.14MPa @Ty Rizia (®) tig- 1340 =7 © ¥y =1 om/kg) (@ Ta= (©) Miomy ) Qo= @) BSvura =2 Comdenser) An adiabatic compressor works with R-134a as working fluid and 0.15 KW. The refrigerant enters compressor as saturated vapor at 0.14MPa. The refrigerant leaves compressor at 70°C and 1.2MPa and then enters condenser 10 be cooled at which pressure remains constant and leaves condenser at 40°C. If the surrounding temperature is 30° Find: (a) initial temperature (T1). (b) mass flow rate of R-134a, (¢) volumetric rate of R-1342 at entrance. of compressor ( ¥;). (@) T, . (¢) compressor efficiency, (1) rate of heat Tosses from condenser, and (g) fotal entropy generation in condenser and also show if the process is possible or not.28. 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°C. The isentropic efficiencies of the compressor, H.P. turbine, and L.P. turbine are 0.8, 0.83, and 0.85 respectively, and the mechanical efficiency of both shafts is 98%. Calculate the pressure between turbine stages when the air intake conditions are 1.01 bar and 25°C. Calculate also the thermal efficiency and the shaft power when the mass flow is 60 kg/s. Neglect kinetic energy changes, and pressure [Ans. 1.57 bar; 14.9% ; 4560 kW) loss in combustion.An iseal Brayton cycle has a pressure ratio of 6:1. The temperature of the air is 22 degrees celsius at the inlet to the compressor and 1080 derees celsius at the inlet to the turbine. Take specific heat at constant pressure and constant volume for air as 1,006 KJ/kg K and 0,717 KJ/kg K respectively. Calculate: 1. the compresion absolute temperature to one decimal place 2. the work ratio of the plant to three decimal places 3. the specific work output to the turbine and specific work input to the compressor , to one decimal place and SI unit 4. the thermal efficiency of the plant to one decimal place
- Task: In a gas turbine, the compressor is two-part with intercooling. The LP compressor (before cooling) has a pressure ratio of 7/1 and the HP compressor (after cooling) has a pressure ratio of 4/1. The intercooler reduces the temperature by 200°C. The air has mass m 1 =200 kg/s with pressure p 1 = p 6 =1.01 bar and temperature t 1 = 20°C. The gas turbine's fuel is natural gas with a lower calorific value H LHV =40 MJ/kg and the temperature of the gas leaving the combustion chamber t 5 =1310°C. We can neglect pressure loss in the combustion chamber and sensible heat from the natural gas. Other data are: Data for air: L = 1 .4 & c p,L = 1.005 kJ / kgK Data for the exhaust gas: AG = 1.333 & c p,AG = 1.15 kJ / kgK Isentropic efficiency LP compressor: η LPC,is = 0.84 Isentropic efficiency HP compressor: η HPC,is = 0.86 Isentropic efficiency of the expander: η E,is = 0.82 Generator efficiency (incl. mech.): η G,GT = 0.97 What is the pressure in the combustion chamber ?…Critically compare how heat transfer efficiency will affect the lifetime of the turbine.Define the Reversible Adiabatic Compression
- Describe the ideal process for an adiabatic turbine.! Required information Consider an ideal gas-turbine cycle with two stages of compression and two stages of expansion. The pressure ratio across each stage of the compressor and turbine is 3. The air enters each stage of the compressor at 300 K and each stage of the turbine at 1200 K. Use variable specific heats. Determine the back work ratio and the thermal efficiency of the cycle, assuming a regenerator with 79 percent effectiveness is used. The back work ratio is The thermal efficiency is [ %. 1%.A motor car gas turbine unit has two centrifugal compressors in series giving an overall pressure ratio of 6/1. The air leaving the HP compressor passes through a heat exchanger before entering the combustion chamber. The expansion is in two turbine stages, the first stage driving the compressors and the second stage driving the car through gearing. The gases leaving the LP turbine pass through the heat exchanger before exhausting to the atmosphere. The HP turbine inlet temperature is 800 ?C and the air inlet temperature to the unit is 15 ?C. The isentropic efficiency of the compression is 0.8, and that of each turbine is 0.85; the mechanical efficiency of each shaft is 98 %. The heat exchanger thermal ratio may be assumed to be 0.65. Neglecting pressure losses and changes in kinetic energy, calculate: (i) the overall cycle efficiency; (ii) the power developed when the air mass flow is 0.7 kg/s; (iii) the specific fuel consumption when the calorific value of the fuel used is 42 600…