Publication: Design of a low-speed axial compressor rotor
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Date
2024-07-01
Authors
Wan Mohamad Izdiham Bin Wan Hasan
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Abstract
Axial compressor efficiencies and competencies form an integral part of most forms of contemporary technology involved in aerospace and power generation applications. Generally speaking, conventional techniques of blade design follow iterative procedures more frequently than not and, under most conditions, are usually somewhat time-consuming and may not always produce best outcomes. This FYP will investigate using techniques to give axial compressor blade optimal form design. Using and creating strategies to raise specific performance criteria including efficiency and aerodynamic stability especially takes great focus. First the desired aerodynamic parameters are specified; next, repeatedly changing the blade shape helps to reach them. Today, this application is enabled by integrating modern optimisation techniques (ANSYS) with CFD analysis to generate blade profiles fulfilling specific established performance criteria. The design inputs are the primary parameters; so, they have the option to offer a different output design with a desired alternate display. The input parameters cover several such elements, including pressure distribution, flow velocity, and efficiency with a minimum degree of aerodynamic loss, which can maximize the compressor's whole performance. Under more specific terms, this paper describes the evolution of a strong design framework combining optimisation techniques with computational fluid dynamics. This strategy is validated by means of several design instances, and notable performance parameter improvement over traditional design techniques is shown. The results show that the technique is able to produce improved blade designs, so enabling the most effective and very creative axial compressors. By providing a methodical and effective blade design methodology that lessens reliance on a conventional iterative process, this endeavour will help the field of turbomachinery and consequently advance compressor technologies.