This paper describes a new universal algebraic model for the estimation of flow deflection and losses in axial compressor inlet guide vane devices. The model deals with nominal flow and far-off-design operating conditions in connection with large stagger angle adjustments. The first part of the model considers deflection and losses in 2D cascades, taking into account the main cascade geometry parameters and operating conditions, such as Mach number and stagger adjustment. The second part of the model deals with additional deviation and losses due to secondary flow caused by the end wall viscous effects and by the trailing vortices. The model is developed for NACA65 airfoils, NACA63-A4K6 airfoils, and airfoils having an NACA65 thickness distribution on a circular-arc camber line. It is suitable for application in 1D or 2D through-flow calculations for design and analysis cases. The development of the method is based on systematic computational fluid dynamics (CFD) flow calculations for various cascade geometries and operating parameters. The comparison of correlation results with experimental data for several test cases shows good agreement.
A New Loss and Deviation Model for Axial Compressor Inlet Guide Vanes
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 13, 2013; final manuscript received October 15, 2013; published online January 2, 2014. Editor: Ronald Bunker.
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Banjac, M., Petrovic, M. V., and Wiedermann, A. (January 2, 2014). "A New Loss and Deviation Model for Axial Compressor Inlet Guide Vanes." ASME. J. Turbomach. July 2014; 136(7): 071011. https://doi.org/10.1115/1.4025956
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