Meridional Design and Computational Analysis of Micro Gas Turbine Centrifugal Compressor
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Abstract
Centrifugal compressors provide a very high-pressure rise per stage and are commonly used in micro gas turbines up to a few kilo Newtons of thrust and small turboprop/turboshafts with less than 1200 SHP capacity. The flow paths in the centrifugal or radial flow compressors are complex and follow twisted trapezoidal passages. The primary objective of centrifugal compressor design is to produce geometry that when operated at specific rotational speeds can handle design mass flow rates without many losses and still produce the optimum pressure rise. The efficiency of a centrifugal compressor is influenced by the Coriolis force, which can cause flow separation from the blades, thereby reducing the energy transfer from the blades to the flow and diminishing the compressor's overall performance. This paper presents a comparative analysis of centrifugal compressor performance for varying exit blade angles, blade quantities and the incorporation of splitter vanes. The study methodically evaluates the impact of these variables on the compressor's performance, focusing on parameters such as pressure rise, slip factor, surge characteristics and choking limits.
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