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Abstract
An improved streamline curvature (SLC) throughflow analysis method is presented based on the predecessor's works to simulate the flow fields of a certain transonic axial compressor. The improvements of this method are embodied centrally in minimum loss incidence angle (MIA) model and total pressure loss (TPL) model that ensure accurate and reliable performance prediction at both design and off-design conditions. The improved MIA is set up as a function of inlet Mach number, solidity, thickness, camber angle, etc. according to low-speed minimum incidence angle. Therefore, TPL is divided into two parts, the first one is the minimum loss which considers the revise of Mach number and Reynolds number, and the second one is the additional loss when real incidence angle deviates from MIA. Finally, the internal flow field of a single-stage compressor is simulated. The characteristic curves and spanwise aerodynamic parameters distribution at design and off-design points are illustrated in this article. Compared to the experiment and computational fluid dynamics (CFD) data, this improved SLC method gives reasonable performance trends and generally accurate results, also the MIA and TPL models are demonstrated in this article.
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Schedule a callMore From: Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
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