Examine the following open gas turbine process. The temperature of the inlet air is 296 K and pressure is 100 kPa. The polytropic efficiency of the compressor is 81.0 % and pressure ratio 7. The heat flow rate (fuel power) into process is 1.25 MW. The maximum temperature of the process (after combustion chamber) is 1440 K and the polytropic efficiency of the turbine is 87.0 %. The mass flow rate of air is 1.207 kg/s. A constant specific heat cp = 1.15 kJ/kgk can be used for the working fluid. Combustion chamber can be considered as adiabatic. Air in Calculate: C Fuel 10 CH 3 1) Temperature after compressor T₂ 2) Compressor power Pc 3) Temperature after turbine T 4) Turbine power Pt 5) Thermal efficiency of the system nt T Flue gas K (with zero decimal accuracy) MW (with three decimal accuracy) K (with zero decimal accuracy) MW (with three decimal accuracy) % (with one decimal accuracy)

Examine the following open gas turbine process. The temperature of the inlet air is 296 K and pressure is 100 kPa. The polytropic efficiency of the compressor is 81.0 % and pressure ratio 7. The heat flow rate (fuel power) into process is 1.25 MW. The maximum temperature of the process (after combustion chamber) is 1440 K and the polytropic efficiency of the turbine is 87.0 %. The mass flow rate of air is 1.207 kg/s. A constant specific heat cp = 1.15 kJ/kgk can be used for the working fluid. Combustion chamber can be considered as adiabatic. Air in Calculate: C Fuel 10 CH 3 1) Temperature after compressor T₂ 2) Compressor power Pc 3) Temperature after turbine T 4) Turbine power Pt 5) Thermal efficiency of the system nt T Flue gas K (with zero decimal accuracy) MW (with three decimal accuracy) K (with zero decimal accuracy) MW (with three decimal accuracy) % (with one decimal accuracy)

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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Question

Examine the following open gas turbine process. The temperature of the inlet air is 296 K and pressure is 100 kPa. The polytropic
efficiency of the compressor is 81.0% and pressure ratio is 7. The heat flow rate (fuel power) into process is 1.25 MW. The
maximum temperature of the process (after combustion chamber) is 1440 K and the polytropic efficiency of the turbine is 87.0 %.
The mass flow rate of air is 1.207 kg/s. A constant specific heat cp = 1.15 kJ/kgk can be used for the working fluid. Combustion
chamber can be considered as adiabatic.
Air in
Calculate:
O
Fuel
∞
CH
3
1) Temperature after compressor T2
2) Compressor power Pc
3) Temperature after turbine T4
4) Turbine power Pt
5) Thermal efficiency of the system nt
H
P
Flue
gas
K (with zero decimal accuracy)
MW (with three decimal accuracy)
K (with zero decimal accuracy)
MW (with three decimal accuracy)
% (with one decimal accuracy)

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Step 2: Determine exit temperature of compressor and compressor power

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Step 3: Determine exit temperature of turbine, turbine power, and thermal efficiency

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