I need it within 30 minutes please be quick A two-stage air compressor with intercooling takes in air at 1 bar, 30°C. The first stagecompresses it to 4 bar where the intercooler cools it to 50°C after which it enters the second stage,still at 4 bar, and it is there compressed to 11 bar. The index of compression and expansion is 1.32throughout.A1: The work to compress per kg isA2: The work/kg for ideal 2-stage compression, includingideal intercooling, from 1 bar and 30°C, to 11 bar is (+5kJ/kg)a) 260kJ/kgb) 250 kJ/kgc) 240 kJ/kg(+ SkJ/kg)a) 290 kJ/kgb) 250 kJ/kg210 kJ/kgc)For an OTTO cycle, pressure and temperature at beginning of compression are 100kPa and25°C, peak temperature is 1550°C and temperature after expansion is 450°C.B1: Temperature after compression is (+5°C)B2: The peak pressure is (±10kPa)a) 6180 kPaa)1125 °Cb) 751 °Cc) 478 °Cb) 4930 kPac) 2545 kPaThar 79.0g 1 disnlacement fuel density is 838.9 g/L with

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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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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 ?…
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A generator uses a gas turbine cycle. Air enters the compressor at a pressure of 1 bar and a temperature of 30°C with a compressor efficiency of 0.85. Hot gas exits the combustion chamber at a pressure of 9 bar and a temperature of 900°C. The power generated by the turbine is 2400 kW with a turbine efficiency of 0.82. a. Draw installation diagrams and T-s cycle process diagramd b. Determine the work of the compressor and turbine and the mass rate of the air requirement c. Cycle thermal efficiency (air: Cp=1,005 kJ/kg. K dan γ=1.4; Gas hot: cp=1,005 kJ/kg K and γ=1.4)

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