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Thermodynamics and aerodynamics analysis of blading system of an aerobased gas turbine
(2002-03-01)
Abd. Rahim, Rosilawati
A two stage gas turbine is required to be designed from a standard aero-jet engine for the generation of electricity. The gas turbine in it’s is most common form is a heat engine operating by means of a series of process consist of compression of air taking from atmosphere, increase of gas temperature by the constant pressure combustion of fuel in the air, expansion of the gasses to the external atmosphere the whole being a continuous flow process. The aspect have been taken in the design as follow:  An analysis of aerodynamics aspects.  An analysis of thermodynamics aspects.  Blade and root analysis.  Disc analysis  Shaft and bearing analysis. This project consist of 4 chapters which is Chapter 1 -In this chapter consist of introduction to the gas turbine, thermodynamics cycle of Brayton with explained the ideal cases, and the component of the gas turbine which is compressor, combustor and turbine. Chapter 2 -In this chapter explained more on turbojet, turboprop and turbofan. But it is more details on turbojet which is consist of thermodynamics analysis and including the formula of the turbojet process. Chapter 3 -In this chapter consist of the calculation of the blade, root, disc, and shaft. Chapter 4 -In this chapter consist of summary and conclusion.