Abstract
A general thermodynamic analysis of a compressor and a turbine is carried out and the details of the energy transfer between a fluid and the rotor through which it passes are derived. The operation and performance of a centrifugal compressor is developed. The application of centrifugal compressors and radial turbines to jet engines is covered. The operation of the axial flow compressor, which is the most widely used for aerospace propulsion, is analyzed in detail. The velocity diagram for, and pressure rise in, an axial flow compressor stage is derived and the benefits of using multiple stages are detailed. The axial flow turbine is treated in equivalent detail. The characteristic axial flow compressor and turbine performance maps are developed in depth and three-dimensional considerations in axial flow turbomachines are discussed.
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